wing optimization (denis howe's method) - excel spreadsheet

W.Opt sample ORIGINAL

PARAMETERS REQUIREMENTSA t/c Bypass R ToL LL Va max Vd (Mn)crit (Mn)cr Sigma cr1 Sigma cr2 MaxRge9.1 0.128 4 2200 1850 72 200 0.82 0.82 0.3369 0.2971 6500

ASSUMEDM1/Mo S^-0.1 Rw Type fac ClEAS sig SS alpha SSgamma Flap Fac a Cruise N PP.Fac s Lam.Chrd Gust Sen TO Mn0.99 0.6 5.5 1.1 0.4812 2.74 0.02 1 300 3.75 0.7 0 1 0.3

INITIAL CALCULATED VALUESMl/Mo Mcr/Mo (Cl max)o (Cl us)o (Cl a)o (Cl use)o (Cdz)ls Sigma cr.0.87 0.971529 3.15 1.92 1.89 0.65 0.017161 0.3369

PRELIMINARY CALCULATIONScos delt Delta deg Wave Dr.F (Cdz)cr (Cd)co (Kv)o (Kv)cr Tau(clMn1) Tau(clMn2)0.8635 30.28587 0.12 0.017435 0.029623 0.045529 0.04719 0.3415881441 0.243729

Cl max Cl us Cl a Cl use Va calc Va (Mg/S)o ld (Mg/S)o gt Cor LL2.7201 1.657996 1.63209 0.561301 72.71473 72 5961.427 3469.0767436 1825.913

SUBSONIC FLIGHT - FAN ENGINE 1

3000 4000 5000 6000 7000 8000 9000

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

Take off Acc.Stop Sec.Seg Cruise1 Cruise2 Gust Sen. .Landing


ANALISISTake off Acc.Stop Sec Seg. Climb

(Mg/S)o 1st.app (T/Mg)o (T/Mg)o Tau co (Cd)co/(Cl)(T/Mg)o

4000 0.223737 0.224573 0.197642 0.845683 0.017867 0.2963384500 0.245923 0.24658 0.220717 0.836323 0.017867 0.2996555000 0.267745 0.268176 0.244411 0.827469 0.017867 0.3028625500 0.289261 0.289417 0.268856 0.819048 0.017867 0.305975

6000 0.310516 0.310351 0.294185 0.811002 0.017867 0.3090116500 0.331547 0.331014 0.320536 0.803284 0.017867 0.311987000 0.352384 0.351437 0.348058 0.795858 0.017867 0.3148917500 0.373053 0.371645 0.376913 0.788693 0.017867 0.3177528000 0.393575 0.391659 0.407281 0.781763 0.017867 0.3205685961.427 0.308885 0.308746 0.292197 0.81161 0.017867 0.308779

Start of cruise Landing-rev. thrust(Mg/S)o Fact.Qm (T/Mg)o-1 (T/Mg)o-2 Cl case-1 Cd-1 (L/D)-1 Mn*L/D (T/Mg)o Llength4000 0.207827 0.27764 0.283485 0.311199 0.022005 14.14197 11.59642 0.296338 1611.5074500 0.184736 0.2619 0.271302 0.350099 0.023219 15.07794 12.36391 0.299655 1609.8095000 0.166262 0.250666 0.263312 0.388999 0.024576 15.82837 12.97927 0.302862 1608.1795500 0.151147 0.24271 0.258373 0.427899 0.026076 16.40991 13.45613 0.305975 1606.6046000 0.138552 0.237212 0.255721 0.466799 0.027718 16.84098 13.80961 0.310351 1604.4086500 0.127894 0.233605 0.254829 0.505699 0.029503 17.14045 14.05517 0.331014 1594.2837000 0.118759 0.231483 0.25532 0.544599 0.031431 17.32666 14.20786 0.351437 1584.6587500 0.110841 0.23055 0.256917 0.583499 0.033502 17.41678 14.28176 0.376913 1573.151

8000 0.103914 0.230582 0.259412 0.622399 0.035716 17.42644 14.28968 0.407281 1560.1125961.427 0.139448 0.237563 0.255858 0.463798 0.027586 16.81265 13.78638 0.308779 1605.195SUMMARY (T/Mg)o(Mg/S)o Take off Acc.Stop Sec.Seg Cruise1 Cruise2 Gust Sen. .Landing .4000 0.224573 0.197642 0.296338 0.27764 0.283485

4500 0.24658 0.220717 0.299655 0.2619 0.2713025000 0.268176 0.244411 0.302862 0.250666 0.2633125500 0.289417 0.268856 0.305975 0.24271 0.2583736000 0.310351 0.294185 0.309011 0.237212 0.2557216500 0.331014 0.320536 0.31198 0.233605 0.2548297000 0.351437 0.348058 0.314891 0.231483 0.255327500 0.371645 0.376913 0.317752 0.23055 0.2569178000 0.391659 0.407281 0.320568 0.230582 0.259412

5961.427 0.308746 0.292197 0.308779 0.237563 0.255858 0.15 0.3087795961.427 0.155961.427 0.7

3469.077 0.153469.077 0.7

RESULTA t/c (Mg/S)o (T/Mg)o L/D Case Cl (Cd)z o (Cd)z cr (Kv)o (Kv)cr SP cos Delta Rev t land9.1 0.128 5961.427 0.308779 16.81265 0.463798 0.017161 0.017435 0.045529 0.04719 14.90499 0.86354 1605.195

SUMMARY OF RESULTSA t/c (Mg/S)o (T/Mg)o L/D Case Cl (Cd)z o (Cd)z cr (Kv)o (Kv)cr SP cos Delta7 0.11 6246.396 0.363563 15.54384 0.485968 0.017095 0.017369 0.056769 0.05884 12.53985 0.904819

0.13 5930.175 0.362194 15.19013 0.461367 0.017168 0.017443 0.058607 0.060745 12.66825 0.8590120.15 5622.167 0.361565 14.80155 0.437404 0.017241 0.017517 0.060688 0.062902 12.89268 0.814396

8 0.11 6246.396 0.333996 16.42123 0.485968 0.017095 0.017369 0.049944 0.051766 13.6313 0.9048190.13 5930.175 0.333308 16.00392 0.461367 0.017168 0.017443 0.051607 0.053489 13.77088 0.8590120.15 5622.167 0.333304 15.55294 0.437404 0.017241 0.017517 0.053488 0.055439 14.01485 0.814396

9 0.11 6246.396 0.310941 17.17454 0.485968 0.017095 0.017369 0.044641 0.04627 14.67262 0.9048190.13 5930.175 0.310779 16.69913 0.461367 0.017168 0.017443 0.046167 0.047851 14.82286 0.8590120.15 5622.167 0.311255 16.19169 0.437404 0.017241 0.017517 0.047893 0.04964 15.08546 0.814396

10 0.11 6246.396 0.308746 17.8283 0.485968 0.017095 0.017369 0.040402 0.041876 15.67133 0.9048190.13 5930.175 0.308746 17.29984 0.461367 0.017168 0.017443 0.041819 0.043344 15.8318 0.8590120.15 5622.167 0.308746 16.7413 0.437404 0.017241 0.017517 0.043421 0.045005 16.11228 0.814396

11 0.11 6246.396 0.308746 18.40095 0.485968 0.017095 0.017369 0.036937 0.038284 16.63322 0.9048190.13 5930.175 0.308746 17.82407 0.461367 0.017168 0.017443 0.038263 0.039659 16.80354 0.8590120.15 5622.167 0.308746 17.21918 0.437404 0.017241 0.017517 0.039764 0.041215 17.10124 0.814396

12 0.11 6246.396 0.308746 18.90669 0.485968 0.017095 0.017369 0.034051 0.035293 17.56282 0.9048190.13 5930.175 0.308746 18.28551 0.461367 0.017168 0.017443 0.035303 0.036591 17.74265 0.8590120.15 5622.167 0.308746 17.63849 0.437404 0.017241 0.017517 0.036719 0.038059 18.05699 0.814396

10.34 0.11 6246.396 0.308746 18.03131 0.485968 0.017095 0.017369 0.039149 0.040577 16.00226 0.90481910.17 0.13 5930.175 0.308746 17.39394 0.461367 0.017168 0.017443 0.041165 0.042666 15.99948 0.8590129.89 0.15 5622.167 0.308746 16.68463 0.437404 0.017241 0.017517 0.043869 0.045469 16.00128 0.814396

10.28 0.11 6246.396 0.308746 17.99614 0.485968 0.017095 0.017369 0.039364 0.0408 15.94416 0.9048199.6 0.13 5930.175 0.308746 17.06963 0.461367 0.017168 0.017443 0.043449 0.045034 15.43298 0.8590128.8 0.15 5622.167 0.315269 16.07172 0.437404 0.017241 0.017517 0.04891 0.050694 14.87506 0.814396

7 0.1196 6093.585 0.36282 15.3784 0.47408 0.01713 0.017404 0.057624 0.059726 12.58822 0.8826838 0.124 6024.179 0.333447 16.13267 0.46868 0.017146 0.01742 0.051087 0.052951 13.71708 0.8726299 0.127 5977.084 0.310764 16.7725 0.465016 0.017157 0.017432 0.045926 0.047602 14.79261 0.86580810 0.1302 5927.054 0.308746 17.29441 0.461124 0.017169 0.017443 0.041834 0.04336 15.83405 0.8585611 0.1325 5891.225 0.308746 17.74996 0.458336 0.017177 0.017452 0.038441 0.039843 16.83428 0.8533712 0.1345 5860.157 0.308746 18.14212 0.455919 0.017184 0.017459 0.035606 0.036905 17.80255 0.84887


CHART OF RESULTS

A t/c=0.11 A t/c=0.13 A t/c=0.15 SP=16 A Des Pt

7 0.363563 9 0.362194 11 0.361565 10.34 0.308746 10.9 0.3087798 0.333996 10 0.333308 12 0.333304 12.17 0.3087469 0.310941 11 0.310779 13 0.311255 13.89 0.30874610 0.308746 12 0.308746 14 0.308746

11 0.308746 13 0.308746 15 0.30874612 0.308746 14 0.308746 16 0.308746

A=7 A=8 A=9 A=10 A=11 A=127 0.363563 8 0.333996 9 0.310941 10 0.308746 11 0.308746 12 0.3087469 0.362194 10 0.333308 11 0.310779 12 0.308746 13 0.308746 14 0.30874611 0.361565 12 0.333304 13 0.311255 14 0.308746 15 0.308746 16 0.308746

7 8 9 10 11 12 13 14 15 16 17

0.25

0.27

0.29

0.31

0.33

0.35

0.37

t/c=0.11

t/c=0.13

t/c=0.15

A=7

A=8

A=9

A=10

A=11

A=12

SP=16

Des Pt

(T/M

g)o

Parameters Requirements

Aspect Ratio,A t/c Bypass Ratio Takeoff length

12 0.12 4 2000

Assumptions

W1/WTO S^-0.1 Rw Type fac ClEAS sig

0.99 0.61 5.5 1.15 0.4812

Takeoff requirements Accelerate StopW/S T/W- 1st T/W T/W ratio

4000 0.23042928 0.231306580607 0.20227842624500 0.25342393 0.254075835425 0.226063856295000 0.27606411 0.276432256267 0.250532235255500 0.29840811 0.298434799369 0.275825285036000 0.32050207 0.320129980452 0.302087326776500 0.3423833 0.341555281147 0.3294703157000 0.36408257 0.362741434443 0.35813844837500 0.38562559 0.383714011379 0.388272842958000 0.40703417 0.404494554683 0.42007665401

4352.3136010274 0.24667183 0.24739642544 0.21897361473

Results SummaryT/W

W/S Takeoff Accelerate Stop Second segment climb Cruise 14000 0.23130658 0.2022784262 0.255851765934245 0.249391768554500 0.25407584 0.226063856293 0.258598056322347 0.21331718265000 0.27643226 0.250532235248 0.261250371080274 0.197877277675500 0.2984348 0.275825285028 0.263824047874918 0.185627740196000 0.32012998 0.30208732677 0.2663309882857 0.17577097836500 0.34155528 0.329470314996 0.268780647991143 0.167754813027000 0.36274143 0.358138448301 0.271180688287978 0.161184830787500 0.38371401 0.388272842945 0.273537420514758 0.155771794998000 0.40449455 0.42007665401 0.27585611851708 0.15129877817

4352.3136010274 0.24667183 0.218973614735 0.257797456932275 0.218649001924352.3136010274

Graphs

3500 4000 4500 5000 5500 6000 6500 7000 7500 8000 85000

0.050.1

0.150.2

0.250.3

0.350.4

0.45

Takeoff

Takeoff

3500 4500 5500 6500 7500 85000

0.050.1

0.150.2

0.250.3

0.350.4

0.45

accelerate stop

accelerate stop

3500 4000 4500 5000 5500 6000 6500 7000 7500 8000 85000

0.050.1

0.150.2

0.250.3

0.350.4

0.45

Takeoff

Takeoff

3500 4500 5500 6500 7500 85000

0.050.1

0.150.2

0.250.3

0.350.4

0.45

accelerate stop

accelerate stop

3500 4000 4500 5000 5500 6000 6500 7000 7500 8000 85000

0.050.1

0.150.2

0.250.3

0.350.4

0.450.5

climb

climb

3500 4500 5500 6500 7500 85000

0.05

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cruise stage 1cruise stage 2

3500 4000 4500 5000 5500 6000 6500 7000 7500 8000 85000

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takeoffaccelerate stopsecond segment climbcruise stage 1cruise stage 2landing

Wing Optimization Stage 1 Group 2

Landing LengthVa max Vd (Mn)crit (Mn)cr Sigma(30000ft) Sigma(35000ft)

1500 72 190 0.8 0.8 0.3813 0.2971

alpha gamma Flap Factor a at Cruise N PP.Fac s Lam.Chord

2.74 0.02 1 300 3.75 0.7 0

RESULTS

Second segment climb CruiseTau (Cd)co/Clus T/W Qm fact0.8510114 0.01662711 0.255851766 0.191457242690.8419738 0.01662711 0.258598056 0.170184215720.8334257 0.01662711 0.261250371 0.153165794150.8252954 0.01662711 0.263824048 0.13924163105

0.817527 0.01662711 0.266330988 0.127638161790.8100761 0.01662711 0.268780648 0.117819841650.8029066 0.01662711 0.271180688 0.10940413868

0.795989 0.01662711 0.273537421 0.102110529430.7892983 0.01662711 0.275856119 0.095728621340.8445885 0.01662711 0.257797457 0.17595905097

Cruise 2 Landing0.25167338453 First result0.23929903069 A t/c W/S

0.2307574427 12 0.11 4352.313601030.22500332078

0.2213397984 Final results0.21928442952 A t/c W/S0.21849260982 7 0.11 5186.7953210.21871162947 0.13 4924.2160.21975195608 0.15 4668.4570.24249587089 0.1 8 0.11 5186.795

0.7 0.13 4924.2160.15 4668.457

9 0.11 5186.7950.13 4924.2160.15 4668.457

10 0.11 5186.7950.13 4924.216

3500 4500 5500 6500 7500 85000

0.050.1

0.150.2

0.250.3

0.350.4

0.45

accelerate stop

accelerate stop

0.15 4668.45711 0.11 5186.795

0.13 4924.2160.15 4668.457

12 0.11 5186.7950.13 4924.2160.15 4668.457

13 0.11 5186.7950.13 4924.2160.15 4668.457

11.18769 0.11 5186.7953212411.00656 0.13 4924.2159394210.70078 0.15 4668.4568013

3500 4500 5500 6500 7500 85000

0.050.1

0.150.2

0.250.3

0.350.4

0.45

accelerate stop

accelerate stop

3500 4500 5500 6500 7500 85000

0.05

0.1

0.15

0.2

0.25

0.3

cruise stage 1cruise stage 2

3500 4000 4500 5000 5500 6000 6500 7000 7500 8000 85000

0.1

0.2

0.3

0.4

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0.6

0.7

0.8

takeoffaccelerate stopsecond segment climbcruise stage 1cruise stage 2landing

MaxRge/km Calculations3704 Wl/Wto Mcr/Mo (Cl max)o (Cl us)o

0.92592 0.973938 3.15 1.92

Gust Sen Takeoff Mach no cos delta Delta deg Wave Dr.F (Cdz)cr

1 0.3 0.92640625 22.12026 0.0267567833 0.01687502139

Cl max Cl us Cl a Cl use

2.9181796875 1.7787 1.7509078125 0.6021640625

Reversed thrust landingT/W -1 T/W-2 Cl -1 Cd-1 L/D - 1 M * L/D T/W ratio0.2493917686 0.25167338452697 0.28959818643 0.019809325 14.61929 11.695428773 0.2558517659340.2133171826 0.23929903069352 0.325797959734 0.0205887493 15.82408 12.659261782 0.2585980563220.1978772777 0.2307574427012 0.361997733038 0.0214598707 16.86859 13.49487097 0.2764322562670.1856277402 0.22500332077513 0.398197506342 0.0224226891 17.75869 14.206949215 0.2984347993690.1757709783 0.22133979839877 0.434397279645 0.0234772044 18.50294 14.802351139 0.320129980452

0.167754813 0.21928442952217 0.470597052949 0.0246234168 19.11177 15.289415193 0.3415552811470.1611848308 0.21849260982397 0.506796826253 0.0258613261 19.59671 15.677365488 0.362741434443

0.155771795 0.21871162946847 0.542996599557 0.0271909324 19.96977 15.975814048 0.3882728429450.1512987782 0.21975195607893 0.579196372861 0.0286122357 20.24296 16.194368851 0.420076654010.2186490019 0.24249587089374 0.315105531408 0.0203489862 15.48507 12.388058161 0.257797456932

T/W L/D (Cd)z o (Cd)z cr (Kv)o (Kv)cr cos delta0.2577974569 15.4850727007918 0.018208683976 0.0168750214 0.03392 0.0349875367 0.92640625

0.285T/W L/D (Cd)z o (Cd)z cr (Kv)o (Kv)cr cos delta

0.360971367 12.56422505 0.01817 0.0185333 0.055769 0.057523 0.9506250.358876 12.07324 0.018247 0.018612 0.057434 0.059241 0.9025

0.357502 11.5738 0.018325 0.018692 0.059319 0.061185 0.8556250.331207 12.89748 0.01817 0.018533 0.04904 0.050583 0.9506250.329862 12.37177 0.018247 0.018612 0.050546 0.052136 0.90250.329182 11.84027 0.018325 0.018692 0.052251 0.053894 0.8556250.308005 13.16889 0.01817 0.018533 0.043812 0.04519 0.9506250.307238 12.61415 0.018247 0.018612 0.045194 0.046616 0.90250.307093 12.05597 0.018325 0.018692 0.046758 0.048229 0.8556250.289402 13.3942 0.01817 0.018533 0.039632 0.040879 0.9506250.289095 12.81483 0.018247 0.018612 0.040915 0.042202 0.9025

0.289374 12.23412 0.018325 0.018692 0.042367 0.0437 0.8556250.278854 13.58421 0.01817 0.018533 0.036216 0.037355 0.9506250.278854 12.98371 0.018247 0.018612 0.037417 0.038594 0.90250.278854 12.38374 0.018325 0.018692 0.038777 0.0399997 0.8556250.278854 13.74661 0.01817 0.018533 0.03337 0.03442 0.9506250.278854 13.12778 0.018247 0.018612 0.034504 0.03559 0.90250.278854 12.51116 0.018325 0.018692 0.035788 0.036913 0.8556250.278854 13.887 0.01817 0.018533 0.030964 0.031938 0.9506250.278854 13.25213 0.018247 0.018612 0.032041 0.033049 0.90250.278854 12.62098 0.018325 0.018692 0.033259 0.034306 0.855626

0.2788535687 18.0745447218026 0.018169910668 0.0168481877 0.035643 0.0367638881 0.9506250.2788535687 17.3859571743778 0.018247457284 0.0169017589 0.037396 0.0385728858 0.90250.2789057692 16.6417958444905 0.0183250039 0.0169549484 0.039781 0.0410321963 0.855625

7 8 9 10 11 12 13 14 150.25

0.27

0.29

0.31

0.33

0.35

0.37

t/c = 0.11

t/c = 0.13

t/c = 0.15

A = 7

A = 8

A = 9

A = 10

A = 11

A = 13

design point

SP=16

T/W

Aspect ratio

(Cl a)o (Cl use)o (Cdz)ls Sigma cr.

1.89 0.65 0.018209 0.3813

(Cd)co (Kv)o (Kv)cr Tau(clMn1)Tau(clMn2)

0.0295746405667 0.03392 0.034988 0.345184 0.246294

Va calc Va (W/S)o ld (W/S)o gt Cor LL

61.325270339354 61.32527 4352.314 3832.5 1499.518

Reversed thrust landingLanding length1366.02477063661364.95155389741358.1190261247

1350.003372951342.3213908529 Carpet Plot1335.02884635261328.0885867868 A t/c = 0.11 A t/c = 0.131320.0617626418 7 0.360971 9 0.3588761310.5440299452 8 0.331207 10 0.3298621365.2638270069 9 0.308005 11 0.307238

10 0.289402 12 0.28909511 0.278854 13 0.27885412 0.278854 14 0.27885413

A = 7 A = 8LL SP 7 0.360971 8 0.3312071365.2638270069 16.78445 9 0.358876 10 0.329862

11 0.357502 12 0.329182

LL SP1403.636775 11.93561

1404.402 12.057821404.906 12.271441414.795 12.97447

1415.314 13.107321415.577 13.339531423.933 13.965611424.241 14.108611424.3 14.358561431.556 14.91621431.684 15.06894

1431.568 15.33591436.002 11.935611436.002 15.993851436.002 16.27721436.002 16.716541436.002 16.887711436.002 17.1869 121436.002 17.57409 0.257797 12 0.2577971424.241 17.754041436.002 18.06858

1436.0022143136 16.000041436.0022143136 15.999811435.9799843929 15.99904

7 8 9 10 11 12 13 14 150.25

0.27

0.29

0.31

0.33

0.35

0.37

t/c = 0.11

t/c = 0.13

t/c = 0.15

A = 7

A = 8

A = 9

A = 10

A = 11

A = 13

design point

SP=16

T/W

Aspect ratio

A t/c = 0.15 SP=16

11 0.357502 10.70078 0.278906

12 0.329182 11.00656 0.278854

13 0.307093 11.18769 0.278854

14 0.28937415 0.27885416 0.278854

A = 9 A = 10 A = 11 A = 139 0.308005 10 0.289402 11 0.278854 12 0.278854

11 0.307238 12 0.289095 13 0.278854 14 0.27885413 0.307093 14 0.289374 15 0.278854 16 0.278854

Stage 1

Wing Optimisation

INPUT PARAMETERS INPUT REQUIREMENTS

A t/c Bypass R ToL LL Va max Vd (Mn)crit (Mn)cr

11.11531892 0.12 12 2000 1500 128.08 272 0.8 0.72

ASSUMEDM1/Mo S^-0.1 Rw Type fac ClEAS sig SS alpha SSgamma Flap Fac a Cruise

0.99 0.62 5.5 1.15 0.359 2.74 0.02 1 303.1

INITIAL CALCULATED VALUESMl/Mo Mcr/Mo (Cl max)o (Cl us)o (Cl a)o (Cl use)o (Cdz)ls Sigma cr.0.926 0.974 3.087 1.835 1.852 0.573 0.019 0.359

PRELIMINARY CALCULATIONScos delta Delta deg Wave Dr.F (Cdz)cr (Cd)co (Kv)o (Kv)cr Tau(clMn1) Tau(clMn2)

0.92640625 22.120259404005 0.015 0.017 0.030 0.036 0.037 0.230 0.202

ANALYSIS

Take off Accccelerated Stop 2nd Segmet Climb(Mg/S)o (T/Mg)o 1st approx (T/Mg)o (T/Mg)o Tau co (Cd)co/(Cl)us (T/Mg)o

4000 0.239042392918828 0.2398425957876 0.21106962465975 0.7834053254 0.01774985334632 0.2858254305455154500 0.262953080773369 0.263493106317 0.23622852951539 0.7702666552 0.01774985334632 0.290700840941143

5000 0.286504072736838 0.2867203405242 0.26220058455356 0.757839792 0.01774985334632 0.295467679033247

5500 0.30975549547029 0.3095850365924 0.28914886998076 0.7460202311 0.01774985334632 0.3001489169658686000 0.332754948723822 0.3321350963578 0.31724249244948 0.7347267831 0.01774985334632 0.3047624907296086500 0.355540946053092 0.3544091012582 0.34666256990205 0.7238948819 0.01774985334632 0.3093227622145117000 0.378145221815904 0.3764386709624 0.37760800844399 0.7134721778 0.01774985334632 0.3138414802695517500 0.400594331876326 0.398250100676 0.41030165113695 0.7034155272 0.01774985334632 0.3183284357056648000 0.422910796618697 0.4198655308126 0.44499730495389 0.6936888736 0.01774985334632 0.3227919214767574272.52 0.252123499134289 0.2527898284292 0.22469119899325 0.7761485747 0.01774985334632 0.288497810475655

Start of cruise Landing - reverse thrust

(Mg/S)o Fact.Qm (T/Mg)o cruise 1 (T/Mg)o cruise 2 Cl case-1 Cd-1 (L/D)-1 Mn*L/D (T/Mg)o4000 0.158274484326155 0.2794382589751 0.29403765780741 0.37199687357012 0.0223495593 16.644483612 11.9840282008453 0.2940376578074064500 0.140688430512138 0.2654090687139 0.28554658003554 0.41849648276639 0.023711411 17.649581597 12.7076987500471 0.2907008409411435000 0.126619587460924 0.2556662680983 0.28091746814019 0.46499609196265 0.0252334805 18.427742942 13.267974918556 0.2954676790332475500 0.115108715873567 0.2490408417702 0.27909705870051 0.51149570115892 0.0269157678 19.003570848 13.6825710105259 0.3095850365923916000 0.105516322884103 0.244753446158 0.27938317610257 0.55799531035518 0.028758273 19.402949178 13.9701234084903 0.3321350963577736500 0.097399682662249 0.2422645357116 0.2812896987675 0.60449491955145 0.0307609961 19.651344118 14.1489677646435 0.354409101258237000 0.090442562472089 0.2411887207529 0.28446939699613 0.65099452874771 0.032923937 19.772681779 14.2363308805817 0.3776080084439897500 0.084413058307283 0.2412433821841 0.28866763567571 0.69749413794398 0.0352470957 19.788698159 14.2478626742221 0.410301651136958000 0.079137242163078 0.2422165556822 0.29369343847169 0.74399374714024 0.0377304723 19.7186439 14.1974236081175 0.4449973049538944272.52 0.148179023507192 0.2711698304276 0.2888493116956 0.39734108068538 0.02307196 17.221817345 12.3997084885907 0.288849311695596

SUMMARY OF ANALYSIS(T/Mg)o values

(Mg/S)o Take off Acc Stop 2nd Seg climb Cruise 1 Cruise 2 Gust sen. Landing4000 0.239842595787562 0.2110696246597 0.28582543054551 0.27943825897514 0.29403765784500 0.263493106316999 0.2362285295154 0.29070084094114 0.26540906871394 0.285546585000 0.286720340524247 0.2622005845536 0.29546767903325 0.25566626809826 0.28091746815500 0.309585036592391 0.2891488699808 0.30014891696587 0.24904084177024 0.27909705876000 0.332135096357773 0.3172424924495 0.30476249072961 0.24475344615797 0.27938317616500 0.35440910125823 0.346662569902 0.30932276221451 0.24226453571165 0.28128969887000 0.376438670962391 0.377608008444 0.31384148026955 0.24118872075286 0.2844693977500 0.398250100676044 0.4103016511369 0.31832843570566 0.24124338218411 0.28866763578000 0.419865530812596 0.4449973049539 0.32279192147676 0.24221655568225 0.29369343854272.52 0.252789828429191 0.2246911989932 0.28849781047566 0.27116983042755 0.2888493117 0.1 0.2888493116955964272.52 0.54891.87 0.14891.87 0.5

PRELIMINARY RESULTA t/c (Mg/S)o (T/Mg)o L/D Case Cl (Cd)z o (Cd)z cr (Kv)o11.11531892 0.12 4272.52 0.2888493116956 17.2218173452649 0.3973410807 0.018507187 0.01722258831032 0.036440296442642

FINAL RESULTSA t/c (Mg/S)o (T/Mg)o L/D Case Cl (Cd)z o (Cd)z cr (Kv)o7 0.11 4384.2158227315 0.37929897760473 15.3211870550518 0.4077286448 0.0184677781 0.01718591478015 0.055768914140054

0.13 4162.2666982408 0.37749929059515 14.8828725410026 0.3870875497 0.0185465959 0.01725926184048 0.0574344759016830.15 3946.0824860745 0.37646777763332 14.4168772975861 0.3669825869 0.0186254138 0.01733260890082 0.059319327616605

B10

Senadheera, Sathya: Wing Aera parameter in zero lift drag term

E10

Senadheera, Sathya: Relative density at end of equivalent airspeed phase of climb. At 30000ft altitude

F10

Senadheera, Sathya: Second segment climb factor α (Eq. 7.4a)

G10

Senadheera, Sathya: given

H10

Senadheera, Sathya: Take-off flap factor (Eq. 6.15)

I10

Senadheera, Sathya: Speed of sound at initial cruise altitude in m/s

A14

Senadheera, Sathya: Ratio of design landing to take-off mass (Ch. 7 Table 7.1)

B14

Senadheera, Sathya: Ratio of initial cruise to take-off mass

C14

Senadheera, Sathya: Zero sweep Max. lift coefficient

D14

Senadheera, Sathya: Zero sweep unstick lift coefficient (Eq. 6.4)

E14

Senadheera, Sathya: Zero sweep approach lift coefficient (Eq. 6.3)

F14

Senadheera, Sathya: Zero sweep usable lift coefficient in cruise (Eq. 6.6)

G14

Senadheera, Sathya: Low speed zero lift drag coefficient (Eq. 6.13)

H14

Senadheera, Sathya: Rel. density at start of cruise

A18

Senadheera, Sathya: =IF((((0.89-B7)/H7)^2)>1,1,((0.89-B7)/H7)^2)

Stage 1

8 0.11 4384.2158227315 0.3486891260555 16.0051790842437 0.4077286448 0.0184677781 0.01718591478015 0.0490402866579510.13 4162.2666982408 0.34765283741154 15.5085734631456 0.3870875497 0.0185465959 0.01725926184048 0.050546389297310.15 3946.0824860745 0.34732694089193 14.986717791649 0.3669825869 0.0186254138 0.01733260890082 0.052250787301661

9 0.11 4384.2158227315 0.32482120441667 16.5803585470217 0.4077286448 0.0184677781 0.01718591478015 0.0438117842524270.13 4162.2666982408 0.32437324187075 16.0323392508815 0.3870875497 0.0185465959 0.01725926184048 0.0451938631300190.15 3946.0824860745 0.3245904005648 15.4616236204544 0.3669825869 0.0186254138 0.01733260890082 0.046757908248371

10 0.11 4384.2158227315 0.30567948967187 17.0707251956776 0.4077286448 0.0184677781 0.01718591478015 0.0396324853498980.13 4162.2666982408 0.30569806992393 16.4771570025594 0.3870875497 0.0185465959 0.01725926184048 0.0409153452180780.15 3946.0824860745 0.31025807340175 15.8634536179075 0.3669825869 0.0186254138 0.01733260890082 0.04236710802763

11 0.11 4384.2158227315 0.28997989734021 17.493715419442 0.4077286448 0.0184677781 0.01718591478015 0.0362156449093960.13 4162.2666982408 0.29354386302764 16.8595951862455 0.3870875497 0.0185465959 0.01725926184048 0.0374173255880560.15 3946.0824860745 0.30184659801217 16.2078428568191 0.3669825869 0.0186254138 0.01733260890082 0.038777221054045

12 0.11 4384.2158227315 0.27879117185999 17.8622994476569 0.4077286448 0.0184677781 0.01718591478015 0.0333702307643710.13 4162.2666982408 0.28634431728054 17.1918952527927 0.3870875497 0.0185465959 0.01725926184048 0.0345042621184320.15 3946.0824860745 0.29484161100721 16.5062683261902 0.3669825869 0.0186254138 0.01733260890082 0.035787601464785

13 0.11 4384.2158227315 0.27252733231255 18.1863235658508 0.4077286448 0.0184677781 0.01718591478015 0.0309640765690840.13 4162.2666982408 0.28025611086591 17.4832961417355 0.3870875497 0.0185465959 0.01725926184048 0.0320408661869450.15 3946.0824860745 0.28891783816775 16.7673437541319 0.3669825869 0.0186254138 0.01733260890082 0.033259427278221

10.34 0.11 4384.2158227315 0.30000524453491 17.2213741495203 0.4077286448 0.0184677781 0.01718591478015 0.03839632518670510.17 0.13 4162.2666982408 0.30288393555678 16.5461898370275 0.3870875497 0.0185465959 0.01725926184048 0.0402719677592849.89 0.15 3946.0824860745 0.31128756894702 15.8223058365628 0.3669825869 0.0186254138 0.01733260890082 0.042806480726965

10.28 0.11 4384.2158227315 0.30097964284602 17.1953271111231 0.4077286448 0.0184677781 0.01718591478015 0.0386085071693229.6 0.13 4162.2666982408 0.31270726763082 16.3075283804871 0.3870875497 0.0185465959 0.01725926184048 0.0425193997522628.8 0.15 3946.0824860745 0.32872966702754 15.3730817689546 0.3669825869 0.0186254138 0.01733260890082 0.04775626722677

7 0.1196 4276.9607819178 0.37834612350999 15.1143152593577 0.3977540098 0.0185056106 0.01722112136911 0.0565438492809768 0.124 4228.2461197939 0.347893690309 15.6602705212839 0.3932235843 0.0185229506 0.01723725772238 0.0500755904689379 0.127 4195.1915537537 0.32440032629766 16.1160301092066 0.3901495355 0.0185347732 0.01724825978143 0.04497586764788210 0.1302 4160.0763198031 0.30570128269279 16.4711165107862 0.3868838462 0.0185473841 0.01725999531109 0.04092896850826211 0.1325 4134.9284030773 0.29452699587914 16.7790492988578 0.3845451096 0.0185564482 0.01726843022303 0.037577986394378

12 0.1345 4113.1226222101 0.28816986661209 17.0388822215431 0.382517189 0.0185643299 0.01727576492906 0.03477888883436

Stage 1

Wing Optimisation

INPUT REQUIREMENTS

Sigma cr1 Sigma cr2 Max Range

0.359 0.2971 3706.04

ASSUMEDN PP.Fac s Lam.Chrd Gust Sen TO Mn

3.75 0.7 0 1 0.3

cos lambda 1/4 Delta TEL Delata TET Delta LET Delta LEL0.882 1.35 0.7 0.4 0.65

PRELIMINARY CALCULATIONSCl max Cl us Cl a Cl use Va calc

2.85981609375 1.69954785 1.71588965625 0.5311087031 61.33

ANALYSIS

Landing - reverse thrustLength

1351.609994149131352.82931157751351.08977972381346.028006837891338.211304192821330.797659179531323.381711064571313.424850885921303.44359350941353.50919538559

.

PRELIMINARY RESULT(Kv)cr SP cos Delta Rev t land0.0370494939616044 16.000002518506 0.92640625 1353.5091954

FINAL RESULTS(Kv)cr SP cos Delta0.0567012414657344 11.935606881845 0.9506250.0583946475698058 12.057821771902 0.90250.0603110096482664 12.27144283546 0.855625

3500 4000 4500 5000 5500 6000 6500 7000 7500 8000 85000.15

0.2

0.25

0.3

0.35

0.4

0.45

Take off

Wing loading (Mg/S)o

Thru

st to

wt l

oadi

ng (T

/Mg)

o

3500 4000 4500 5000 5500 6000 6500 7000 7500 8000 85000.27

0.28

0.29

0.3

0.31

0.32

0.33

2nd Segment Climb


Thru

st to

wt l

oadi

ng (T

/Mg)

o

J6

Senadheera, Sathya: Density ratio @ start of cruise (if below 11 km) 1J3- Sig cr 1

K6

Senadheera, Sathya: Density ratio @ start of cruise (if above 11 km) 1J3- Sig cr 1

L6

Senadheera, Sathya: 2000 nm = 3706.4km (UK)

J10

Senadheera, Sathya: Ultimate normal manoeuver factor

K10

Senadheera, Sathya: Power plant altitude dependency power, s

L10

Senadheera, Sathya: Proportion of wing laminar flow, Cl

M10

Senadheera, Sathya: Gust sensitivity switch. On =1

N10

Senadheera, Sathya: Take-off Mach number

J11

Senadheera, Sathya: another no to get form JB

Stage 1

0.0498601268864269 12.97446542486 0.9506250.0513914080803188 13.107317728153 0.90250.0531242996793151 13.339532070548 0.8556250.0445442160071993 13.965606453001 0.9506250.0459494000487294 14.108607565062 0.90250.0475395923859202 14.358561147922 0.855625

0.0402950488881361 14.916201144539 0.9506250.0415993552077768 15.068935890329 0.90250.0430753881355232 15.335903023571 0.8556250.0368210867740403 15.831740380378 0.9506250.0380428567757715 15.993849808843 0.90250.039425486550336 16.277203077053 0.8556250.0339281038821399 16.716544545758 0.9506250.0350810936189465 16.887713944518 0.90250.0363858874325262 17.186903257657 0.8556250.0314817243509165 17.574089198768 0.9506250.0325765154020177 17.754039443488 0.90250.033815448017841 18.068576916352 0.855625

0.0390382229845962 15.231180607207 0.9506250.0409452219651419 15.228536928423 0.90250.0435221061307115 15.230250128405 0.855625

0.0392539521594701 15.175881538751 0.9506250.0432302258257443 14.689334003671 0.90250.0485546416185716 14.158297175683 0.855625

0.0574891317308266 11.981647533367 0.9273690.0509127385838626 13.056112667476 0.916806250.0457277601860618 14.079822184722 0.90963906250.0416132062478802 15.071076814153 0.90202506250.0382062034593822 16.023109187858 0.896572265625

0.035360311458721 16.944719273578 0.891844140625

Stage 1

Wing Optimisation

(values obtained from howe's data tables)

PRELIMINARY CALCULATIONSVa (Mg/S)o ld (Mg/S)o gt Cor LL

61.33 4272.52 4891.87 1499.54

Chart for Carpet Plot

A t/c=0.11 A t/c=0.13 A t/c=0.15 SP=167 0.3792989776047 9 0.37749929059515 11 0.376467777633324 10.34 0.30000524453

8 0.3486891260555 10 0.34765283741154 12 0.347326940891928 12.17 0.302883935569 0.3248212044167 11 0.32437324187075 13 0.324590400564801 13.89 0.3112875689510 0.3056794896719 12 0.30569806992393 14 0.31025807340175111 0.2899798973402 13 0.29354386302764 15 0.30184659801217512 0.27879117186 14 0.28634431728054 16 0.294841611007211

3500 4000 4500 5000 5500 6000 6500 7000 7500 8000 85000.15

0.2

0.25

0.3

0.35

0.4

0.45

Take off


Thru

st to

wt l

oadi

ng (T

/Mg)

o

3500 4000 4500 5000 5500 6000 6500 7000 7500 8000 85000.15

0.2

0.25

0.3

0.35

0.4

0.45

0.5

Accelerated Stop


Thru

st to

wt l

oadi

ng (T

/Mg)

o

3500 4000 4500 5000 5500 6000 6500 7000 7500 8000 85000.27

0.28

0.29

0.3

0.31

0.32

0.33

2nd Segment Climb


Thru

st to

wt l

oadi

ng (T

/Mg)

o

3500 4000 4500 5000 5500 6000 6500 7000 7500 8000 85000.15

0.2

0.25

0.3

0.35

0.4

0.45

0.5

Crusie Conditions

cruise 1cruise 2


Thru

st to

wt l

oadi

ng (T

/Mg)

o

3000 4000 5000 6000 7000 8000 90000

0.1

0.2

0.3

0.4

0.5

0.6

Design Point graph

cruise 1cruise 2climbacc stopTake offgust sensationlanding


Thru

st to

wt l

oadi

ng (T

/Mg)

o

Stage 1

A=7 A=8 A=9 A=107 0.3792989776047 8 0.3486891260555 9 0.324821204416674 10 0.3056794897 119 0.3774992905952 10 0.34765283741154 12 0.324373241870748 12 0.3056980699 1311 0.3764677776333 12 0.34732694089193 13 0.324590400564801 14 0.3102580734 15

WING OPTIMISATION STAGE 1 - CARPET PLOT

Design PointA (T/Mg)o

11.115318922019 0.2888493116956

6 8 10 12 14 16 180.25

0.27

0.29

0.31

0.33

0.35

0.37

0.39

t/c = 0.11

t/c = 0.13

t/c = 0.15

A = 7

A = 8

A = 9

A = 10

A = 11

A = 12

design point

SP=16

T/W

Aspect ratio

Stage 1

Wing Optimisation

Chart for Carpet Plot

A (T/Mg)o11.11532 0.288849

3000 4000 5000 6000 7000 8000 90000

0.1

0.2

0.3

0.4

0.5

0.6

Design Point graph

cruise 1cruise 2climbacc stopTake offgust sensationlanding


Thru

st to

wt l

oadi

ng (T

/Mg)

o

Stage 1

A=11 A=120.28997989734 12 0.2787910.293543863028 14 0.2863440.301846598012 16 0.294842

Stage 1

Wing Optimisation

Stage 2

REQUIREMENTSRange PAX Payload (Mn)cr Initial Cr Alt Initial Cr sigma3706.04 148 14356 0.72 9.144 0.3741

PARAMETERS (From previous analysis)A t/c cos delta R (Mg/S)o (T/Mg)o8.3386854518 0.12 0.92592 12 4272.52 0.2888493116956

INPUT DATAFus.L Fus.B Fus.H c1 c2 c345.78 3.52 3.75 0.0009 0.79 1.56

CALCULATIONS(S/Mo)^.45 p bar Req(T/Mg) Av(T/Mg) Av./Req (c)des0.0649296672 0.575695988637 0.0580658812 0.0685022334 1.1797329519 0.4817400411408

ClEAS ClEAS Cl Mn1 Cl Mn1 Cl Mn2 Mcr/Mo(c)o Wf/(Mg)o (c)1 Wf/(Mg)o Wf/(Mg)o0.17197181 0.009252110683 0.52116318404 0.0118555092 0 0.9688923801278

ANALYSIS(Mo)est1 (Mo)est2 Kappa*Mo Mlift. surf. (Mo)calc error

52936.033916 61215.62662712 25671.7551953 9808.7245902 59864.614481 -2.256779163863

SUBSONIC FLIGHT -FAN ENGINE 2

SUMMARYM wing 8173.937158471 Wing Area 137.45325457

M fus 8082.134695485 Wing span 33.855272177M tail 1634.787431694 Mean chrd 4.060025093

M gear 2394.58457924 A 8.3386854518M power p 5089.677394887 Del 0.25 22.19414021

M sys 8979.692172149 Lambda 0.25M op.it 1946 t/c 0.12M oew 36300.81343193M pay 14356M fuel 8641.232429376 22729.653948

Mo 59298.045861302

OPTIMUM RESULTA t/c (Mg/S)o (T/Mg)o Mo F Mass

8.3386854518 0.12 4272.52064645 0.2888493117 59298.045861 8641.2324293765

SUMMARY OF RESULTS

Fuel Massavail.

E7

Senadheera, Sathya: in km. from spec

F7

Senadheera, Sathya: density of air at initial cruise altitude in km/m^3

Stage 2

A t/c (Mg/S)o (T/Mg)o Mo Fuel Mass7 0.11 4384.21582273 0.3792989776 64395.832217 9710.0847195545

0.13 4162.26669824 0.3774992906 63207.951491 9589.18502082470.15 3946.08248607 0.3764677776 62259.044754 9492.6075309757

8 0.11 4384.21582273 0.3486891261 65411.693204 9813.47665501870.13 4162.26669824 0.3476528374 64150.245613 9685.08949422940.15 3946.08248607 0.3473269409 63142.571953 9582.5308456295

9 0.11 4384.21582273 0.3248212044 66359.842333 9909.97703731480.13 4162.26669824 0.3243732419 65029.731451 9774.60148862160.15 3946.08248607 0.3245904006 63967.207957 9666.460353308

10 0.11 4384.21582273 0.3056794897 67251.640121 10000.742112920.13 4162.26669824 0.3056980699 65856.946812 9858.79351714310.15 3946.08248607 0.3102580734 64742.833374 9745.4016790178

11 0.11 4384.21582273 0.2899798973 68095.614361 10086.639820690.13 4162.26669824 0.293543863 66639.801922 9938.47066404370.15 3946.08248607 0.301846598 65476.865104 9820.1096972896

12 0.11 4384.21582273 0.2787911719 68898.35672 10168.3410447940.13 4162.26669824 0.2863443173 67384.411092 10014.2552292430.15 3946.08248607 0.294841611 66175.03613 9891.1678978131

10.243 0.11 4384.21582273 0.3009796428 67460.845932 10022.0345869959.586 0.13 4162.26669824 0.3127072676 65520.264956 9824.52683188668.785 0.15 3946.08248607 0.328729667 63794.340497 9648.8663109102

7 0.1196 4276.96078192 0.3783461235 63789.697036 9648.39371033268 0.124 4228.24611979 0.3478936903 64497.493683 9720.43158384329 0.1275 4189.69507016 0.3244003263 65179.255088 9789.819651757110 0.1302 4160.0763198 0.3057012827 65844.593084 9857.536183834411 0.1325 4134.92840308 0.2945269959 66480.64849 9922.272403060712 0.1345 4113.12262221 0.2881698666 67089.721535 9984.2624210856

CHART FOR CARPET PLOTA t/c=0.11 A t/c=0.13 A t/c=0.157 64395.8322167 9 63207.951491 11 62259.0447539348 65411.69320376 10 64150.245613 12 63142.5719533559 66359.84233328 11 65029.731451 13 63967.20795741410 67251.640120806 12 65856.946812 14 64742.83337437711 68095.61436124 13 66639.801922 15 65476.86510365712 68898.3567201 14 67384.411092 16 66175.036130226

A=7 A=8 A=97 64395.8322167 8 65411.693204 9 66359.8423332849 63207.95149143 10 64150.245613 11 65029.731450834

Stage 2

11 62259.04475393 12 63142.571953 13 63967.207957414

A=10 A=11 A=1210 67251.640120806 11 68095.614361 12 68898.35672010512 65856.94681161 13 66639.801922 14 67384.41109200214 64742.83337438 15 65476.865104 16 66175.036130226

b=34m10.243 67460.8459320111.586 65520.264955812.785 63794.34049733

Summary of optimized valuesAspect Ratio 8.3387Thickness to chord Ratio 0.12Maximum Takeoff weight 61215.63 kgWingspan 33.86 m

Stage 2

REQUIREMENTS CLIMB PATHFinal Cr Alt Fin Cr sig Vd N bar Cl EAS11 0.2981 272 4.13 170

PARAMETERS (From previous analysis) ASSUMEDL/D M1/Mo Delta rad SP Lambda17.221817345265 0.99 0.3873322899 16.000002519 0.25

INPUT DATAc4 c5 (Cdz)ls (Cdz)cr (Kv)o (Kv)cr0.19 1.2 0.018507187 0.0172225883 0.0364402964 0.037049494

CALCULATIONS(c)od Z Tau ClEAS (Vv)EAS Dist EAS Qm0.490398497105 1.513461379 0.538 6.2923546152 230.87335541 0.151087782

M fus c1 bar Mpp/Mo Msys/Mo M op.it M fixed

8082.1346954852 0.0521081026 0.0850197974 0.19 1946 24384.1347

ANALYSISl CG l WG APX l TL ARM S Hor Tail S Vert Tail

21.169159846874 18.098824718 20.032840153 33.428929201 20.90649942

SUBSONIC FLIGHT -FAN ENGINE 2

(Mg/S)o

SUMMARY 5186.795321 4611.92986

Wg Apex 18.098824718 4924.216

S Hor Tail 33.428929201 4668.457S Vert Tail 20.90649942

S^-0.1 0.6112016208

Stat Thr 168027.63937

OPTIMUM RESULTF Mass avail. SP WingSpan

22729.653947988 16.000002519 33.855272177

SUMMARY OF RESULTS A varying with wingspan

G7

Senadheera, Sathya: in km. from spec

H7

Senadheera, Sathya: density of air at final cruise altitude in km/m^3

L7

Senadheera, Sathya: assumed from howe's book

I16

Senadheera, Sathya: from stage 1

J16


K16


L16


Stage 2

F Mass avail. SP Wing Span t/c=0.1123951.669296064 11.935606882 31.560008849 7 0.36097136727779.503068922 12.057821772 31.362917519 8 0.33120731570.257204461 12.271442835 31.204582008 9 0.30800522763.530782626 12.974465425 33.918217994 10 0.28940226376.150299414 13.107317728 33.695615927 11 0.27885429951.887599303 13.339532071 33.516734039 12 0.27885421779.003042217 13.965606453 36.152152937 10.52 3425213.218110927 14.108607565 35.9043750328610.721392084 14.358561148 35.70520891220945.880456248 14.916201145 38.28183093424229.06200968 15.06893589 38.00917753327475.681181243 15.335903024 37.7899623220228.966960284 15.83174038 40.32238257623382.123109354 15.993849809 40.0251261526498.84947106 16.277203077 39.78607517819603.553893106 16.716544546 42.28557706922643.226248037 16.887713945 41.96396708625646.587679717 17.186903258 41.705275718

20762.064575261 15.175881539 38.78538633224617.825985589 14.689334004 37.14934155628879.681724786 14.158297176 35.244034218

25794.212766908 11.981647533 31.45959411925296.626374101 13.056112667 33.75703967824786.120679177 14.079822185 35.93231407824261.69545593 15.071076814 38.00675372123773.539571092 16.023109188 39.99249528323321.862743954 16.944719274 41.901078683

CHART FOR CARPET PLOTA Fuel Vol7.96 63789.6970369.4 64497.49368310.75 65179.25508812.02 65844.59308413.25 66480.6484914.45 67089.721535

7 8 9 10 11 12 13 14 15 1658000

60000

62000

64000

66000

68000

70000

t/c = 0.11t/c = 0.13t/c = 0.15A = 7A = 8A = 9A = 10A = 11A = 12b = 34

Aspect ratio

Max

imum

take

off w

eigh

t/kg

6 7 8 9 10 11 12 13 14 15 160.26

0.28

0.3

0.32

0.34

0.36

0.38

t/c = 0.11t/c = 0.13t/c = 0.15

Stage 2

7 8 9 10 11 12 13 14 15 1658000

60000

62000

64000

66000

68000

70000

t/c = 0.11t/c = 0.13t/c = 0.15A = 7A = 8A = 9A = 10A = 11A = 12b = 34

Aspect ratio

Max

imum

take

off w

eigh

t/kg

Stage 2

CLIMB PATHClEAS H2 ClEAS sig Clmb Mn Sig cr1 Sig cr2 End Cr 17 0.4812 0.82 0.3741 0 9.144

ASSUMED(T/Mg)eng Op It Fac AppFuel/Mo Vbar Vv bar PPFac s5.3 12 0.01 1.2 0.09 0.7

INPUT DATADel I w l Fus l Tail Del l PP l SYS l PAY0.4060025093 20.601 41.202 -3.727126889 20.601 20.601

CALCULATIONSTau Mn1 (Vv)Mn1 Dist.Mn1 Tau Mn2 (Vv)Mn2 (Dist.Mn2)0.2648806311 1.8259669557 296.1471560693 0.18899665841 0 0

Net Range Log 10 Mc1/Mc2 Mc2/Mo Mf/Mo Kappa MoMc1/Mc2

3025.0194885 0.0489313242 1.119260878599 0.86565375298 0.144346247 0.4193660444

(T/Mg)o

0.331207 0.3093218813

0.3298620.329182

Parts highlighted in gray are not considered for the LPG configuration

Fuel mass config - not relevent

R7

Senadheera, Sathya: 9.14km ie at 30000ft altitude

Stage 2

t/c=0.13 t/c=0.159 0.358876 11 0.357502 710 0.329862 12 0.329182 811 0.307238 13 0.307093 912 0.289095 14 0.289374 1013 0.278854 15 0.278854 1114 0.278854 16 0.278854 129.78 34 8.905 34

7 8 9 10 11 12 13 14 15 1658000

60000

62000

64000

66000

68000

70000

t/c = 0.11t/c = 0.13t/c = 0.15A = 7A = 8A = 9A = 10A = 11A = 12b = 34

Aspect ratio

Max

imum

take

off w

eigh

t/kg

6 7 8 9 10 11 12 130.25

0.3

0.35

0.4

0.45

0.5

0.55

t/c = 0.11t/c = 0.13t/c = 0.15

6 7 8 9 10 11 12 13 14 15 160.26

0.28

0.3

0.32

0.34

0.36

0.38

t/c = 0.11t/c = 0.13t/c = 0.15

Stage 2

7 8 9 10 11 12 13 14 15 1658000

60000

62000

64000

66000

68000

70000

t/c = 0.11t/c = 0.13t/c = 0.15A = 7A = 8A = 9A = 10A = 11A = 12b = 34

Aspect ratio

Max

imum

take

off w

eigh

t/kg

Stage 2

0 unless climb STARTS above 11km

INPUT DATAl OP IT Del l Fuel

20.601 0.4060025092969

CALCULATIONSDist .Mn2 Desc. Dist0 154

x^0.25/co X2

0.6752102728521 #DIV/0!

Parts highlighted in gray are not considered for the LPG configuration

Fuel mass config - not relevent

only for cruise STARTING above 11km (null value four this scenario)

Stage 2

t/c=0.11 t/c=0.13 t/c=o.150.4054032560123 7 0.34518922088 7 0.30068198271 0.110.4311052072163 8 0.36719117022 8 0.31993078279 0.130.4550243653534 9 0.38767766358 9 0.33786146881 0.150.477456277563 10 0.40689951238 10 0.354691904260.4986235748218 11 0.42504569057 11 0.37058626670.5186988594129 12 0.44226273763 12 0.38567188826 0.11

0.130.15

6 7 8 9 10 11 12 130.25

0.3

0.35

0.4

0.45

0.5

0.55

t/c = 0.11t/c = 0.13t/c = 0.15

0.1 0.11 0.12 0.13 0.14 0.15 0.160.25

0.3

0.35

0.4

0.45

0.5

0.55

A = 8A = 7A=9A=10A=11A=12

Fuel

req

uire

d/ F

uel A

vail-

able

t/c

Stage 2

A=7 A=8 A=90.40540325601 0.11 0.431105207 0.11 0.45502436540.34518922088 0.13 0.36719117 0.13 0.38767766360.30068198271 0.15 0.319930783 0.15 0.3378614688

A=10 A=11 A=120.47745627756 0.11 0.498623575 0.11 0.51869885940.40689951238 0.13 0.425045691 0.13 0.44226273760.35469190426 0.15 0.370586267 0.15 0.3856718883

0.1 0.11 0.12 0.13 0.14 0.15 0.160.25

0.3

0.35

0.4

0.45

0.5

0.55

A = 8A = 7A=9A=10A=11A=12

Fuel

req

uire

d/ F

uel A

vail-

able

t/c

wing optimization (denis howe's method) - excel spreadsheet

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