global flyer
TRANSCRIPT
Naca 4412Alfa CL CD CL/CD Cm-18 #DIV/0! 0.095-17 #DIV/0! 0.095-16 -0.65 0.01 -65.0000 0.095-15 -0.7 0.015 -46.6667 0.095-14 -0.75 0.02 -37.5000 0.095-13 -0.78 0.022 -35.4545 0.095-12 -0.8 0.025 -32.0000 0.095-11 -0.75 0.02 -37.5000 0.095-10 -0.68 0.01 -68.0000 0.095-9 -0.55 0.0087 -63.2184 0.095-8 -0.45 0.008 -56.2500 0.095-7 -0.35 0.0075 -46.6667 0.095-6 -0.25 0.007 -35.7143 0.095-5 -0.15 0.0068 -22.0588 0.095-4 0 0.0065 0.0000 0.095-3 0.07 0.0064 10.9375 0.095-2 0.17 0.0063 26.9841 0.095-1 0.27 0.0062 43.5484 0.0950 0.4 0.0062 64.5161 0.0951 0.5 0.0062 80.6452 0.0952 0.6 0.0062 96.7742 0.0953 0.7 0.0062 112.9032 0.0954 0.8 0.0064 125.0000 0.0955 0.9 0.0067 134.3284 0.0956 1 0.0078 128.2051 0.0957 1.1 0.0088 125.0000 0.0958 1.22 0.0109 111.9266 0.0959 1.33 0.012 110.8333 0.095
10 1.4 0.0135 103.7037 0.09511 1.5 0.0162 92.5926 0.09512 1.55 0.0172 90.1163 0.09513 1.6 0.019 84.2105 0.09514 1.62 0.019 85.2632 0.09515 1.64 0.02 82.0000 0.09516 1.59 0.025 63.6000 0.09517 1.55 0.03 51.6667 0.09518 1.47 0.035 42.0000 0.095
Desempeños 1.64 0.0062 134.3284 0.09515° 1°-3° 5°
Distribucion Eliptica
Peso del Avión 5000 Kg 49050
Velocidad de Vuelo 65 m/s 234Altitud de Vuelo 3000 m 9842.51969
Densidad 0.90926 Kg/m^3
Viscocidad 1.48E-05 Kg/(m*s)Reynolds 4.18E+06
Cuerda de Raiz 1.4 mCuerda de Punta 0.7 m
Conicidad 0.500Envergadura 36 m
Superficie Alar 37.8 m^2
Alargamiento 34.286
Torcimiento A. -2Torcimiento G. -2 °
Estación Y(m)
0 -4 0.1 5 00.1 -4 0.1 4.7 1.80.2 -4 0.1 4.4 3.60.3 -4 0.1 4.1 5.40.4 -4 0.1 3.8 7.20.5 -4 0.1 3.5 90.6 -4 0.1 3.2 10.80.7 -4 0.1 2.9 12.60.8 -4 0.1 2.6 14.4
0.85 -4 0.1 2.45 15.30.9 -4 0.1 2.3 16.2
0.95 -4 0.1 2.15 17.10.975 -4 0.1 2.075 17.55
1 -4 0.1 2 18
Variación del ángulo de 0 levantamiento
Variación de la pendiente del Perfil
Variación del ángulo de ataque
DATOS DEL EMPENAJE HORIZONTAL
CR 0.5 mCP 0.5 m
CONICIDAD 1ENVERGADURA 11.44 m
SUPERFICIE ALAR 5.72 m^2ALARGAMIENTO 22.88ÁNGULO DE A. R -ÁNGULO DE A.C. -TORCIMENTO G. 0
Eficiencia E.H 80%
Torcimiento G. ESTACIÓN Y CY0 0 0 0.50 0.2 1.144 0.50 0.4 2.288 0.50 0.6 3.432 0.50 0.8 4.576 0.50 0.9 5.148 0.50 0.95 5.434 0.50 0.975 5.577 0.50 1 5.72 0.5
Torcimiento G. ESTACIÓN Y CY0 0 0 0.50 0.2 1.144 0.50 0.4 2.288 0.50 0.6 3.432 0.50 0.8 4.576 0.50 0.9 5.148 0.50 0.95 5.434 0.50 0.975 5.577 0.50 1 5.72 0.5
ESTACIÓN ClE.H CLE.H0 0.105937557847616 0.10652931
0.2 0.105937557847616 0.11162153
0.4 0.105937557847616 0.113994470.6 0.105937557847616 0.111971080.8 0.105937557847616 0.100412040.9 0.105937557847616 0.08225897
0.95 0.105937557847616 0.064444780.975 0.105937557847616 0.0478314
1 0 0
N CL del Avión Circulación 0
Km/Hr 0.6756 29.3525ft
Cl=0 Punta
0.1 -4
Cl=0 Raíz
0.1 -4
Ángulo Ataque Raíz Valor de TAO5 0.25
2
Cuerda (m) Ángulo Efectivo CL local
29.3525 1.4 1734.78887970166 4.99372809698924 0.899372809729.2054 1.33 1726.09314133542 4.69372809698924 0.869372809728.7595 1.26 1699.73902668941 4.39372809698924 0.839372809728.0005 1.19 1654.8831185296 4.09372809698924 0.809372809726.9020 1.12 1589.9602712001 3.79372809698924 0.779372809725.4200 1.05 1502.37124002438 3.49372809698924 0.749372809723.4820 0.98 1387.83110376133 3.19372809698924 0.719372809720.9619 0.91 1238.88706230214 2.89372809698924 0.689372809717.6115 0.84 1040.873327821 2.59372809698924 0.659372809715.4624 0.805 913.8567485418 2.44372809698924 0.644372809712.7945 0.77 756.176941499768 2.29372809698924 0.62937280979.1653 0.735 541.687654069034 2.14372809698924 0.61437280976.5223 0.7175 385.478520894636 2.06872809698924 0.60687280970.0000 0.7 0 1.99372809698924 0.5993728097
DATOS DEL PERFIL
Pendiente del Perfil Punta
Pendiente del Perfil Raíz
Ángulo de Ataque Punta
Variación de la Circulación
Levantamiento a lo largo de la
semienvergadura
PERFIL RAIZ NACA 0009 0.1125 1.05PREFIL PUNTA NACA 0009 0.1125 1.05
PENDIENTE PR
Eficiencia E.H 0.8 CLE.H 0.2790218389
Cl=Clb+CL*Cla
CL1
La Lb Cla Clb -1.07 -0.25 1.07 0 -
1.069 -0.176 1.069 0 -1.065 -0.02 1.065 0 -1.046 0.1 1.046 0 -0.962 0.16 0.962 0 -0.846 0.16 0.846 0 -0.73 0.13 0.73 0 -
0.615 0.091 0.615 0 -0 0 0 0 0
La Lb Cla Clb ClE.H1.07 0 1.07 0 0.279022
1.069 0 1.069 0 0.2790221.065 0 1.065 0 0.2790221.046 0 1.046 0 0.2790220.962 0 0.962 0 0.2790220.846 0 0.846 0 0.2790220.73 0 0.73 0 0.279022
0.615 0 0.615 0 0.2790220 0 0 0 0.000000
LE.H N/m390.6995369
375.58961006
PENDIENTE DE LEVANTAMIENTO
FACTOR DE CORRECCIÓN
349.07014662308.98258561246.69268313189.64500015143.69848792104.84439033
0
CDi
0.00627190301076 0.00423703
0.1
Pendiente de ala
0.09988408404169
Levantamiento Local CDi
2418.53620470029 0.007509593567282220.96900564028 0.007016960502582031.46921593026 0.006541038706911850.03683557025 0.006081828180261676.67186456023 0.005639328922631511.37430290022 0.005213540934031354.1441505902 0.00480446421446
1204.98140763019 0.004412098763911063.88607402017 0.00403644458238996.363685721417 0.0038548842175930.858149760159 0.00367750166988867.369466136403 0.00350429693951836.381443951086 0.0034192612558
0 0.0033352700264
DATOS DEL PERFIL
Ángulo inducido de Ataque
Pendiente Promedio
0.1071428571428570.107142857142857
0.107142857142857 DATOS DEL AVIÓN
W MAX 11023 LB 5048.534VEL. C 65 m/sDENSIDAD. C 0.90926 Kg/m^3Superficie 37.8 m^2
CL tot 0.68211514
Cl=Clb+CL*Cla
CL2 CL3 CL4 CL5 CL6 CL7
- -0.9 -1 -1.3 -1.1 -0.9- -0.963 -1.07 -1.391 -1.177 -0.963- -1.029447 -1.14383 -1.486979 -1.258213 -1.029447- -1.096361055 -1.21817895 -1.58363264 -1.33999685 -1.09636106- -1.14679366353 -1.27421518 -1.65647974 -1.4016367 -1.14679366- -1.1032155043159 -1.225795 -1.59353351 -1.34837451 -1.1032155- -0.9333203166512 -1.03702257 -1.34812935 -1.14072483 -0.93332032- -0.6813238311554 -0.75702648 -0.98413442 -0.83272913 -0.68132383- -0.4190141561606 -0.46557128 -0.60524267 -0.51212841 -0.419014160 0 0 0 0 0
CLE.H LE.H N/m0.298553367571584 215.0493060.298274345732732 214.8483260.297158258377324 214.0444030.291856843439137 210.2257700.268419008975574 193.3433950.236052475668748 170.0296380.203685942361922 146.7158820.171598430893948 123.603106
0 0.000000
PENDIENTE DE LEVANTAMIENTO
CORREGIDA
0 1 2 3 4 5 60.0
50.0
100.0
150.0
200.0
250.0
Distribucion de Levantamiento del Empenaje Horizontal
Y(m)
L (N
/m)
0 1 2 3 4 5 60.0
50.0
100.0
150.0
200.0
250.0
Distribucion de Levantamiento del Empenaje Horizontal
Y(m)
L (N
/m)
KG 49526.1185
Cl=Clb+CL*Cla
CL8 CL9 CL10 CL11 CL12 CL13 CL14 CL15
-0.65 -0.4 -0.2 0 0.2 0.4 0.65 0.9-0.6955 -0.428 -0.214 0 0.214 0.428 0.6955 0.963
-0.7434895 -0.457532 -0.228766 0 0.228766 0.457532 0.7434895 1.029447-0.79181632 -0.48727158 -0.24363579 0 0.24363579 0.48727158 0.79181632 1.096361055-0.82823987 -0.50968607 -0.25484304 0 0.25484304 0.50968607 0.82823987 1.146793664-0.79676675 -0.490318 -0.245159 0 0.245159 0.490318 0.79676675 1.103215504-0.67406467 -0.41480903 -0.20740451 0 0.20740451 0.41480903 0.67406467 0.933320317-0.49206721 -0.30281059 -0.1514053 0 0.1514053 0.30281059 0.49206721 0.681323831-0.30262134 -0.18622851 -0.09311426 0 0.09311426 0.18622851 0.30262134 0.419014156
0 0 0 0 0 0 0 0
0 1 2 3 4 5 60.0
50.0
100.0
150.0
200.0
250.0
Distribucion de Levantamiento del Empenaje Horizontal
Y(m)
L (N
/m)
0 0.2 0.4 0.6 0.8 1 1.20
0.2
0.4
0.6
0.8
1
1.2
1.4
CL MAX PERFIL0.91.040.65
0 1 2 3 4 5 60.0
50.0
100.0
150.0
200.0
250.0
Distribucion de Levantamiento del Empenaje Horizontal
Y(m)
L (N
/m)
Cl=Clb+CL*Cla
CL16 CL17 CL18 CL19 CL20
1.04 1.3 1.3 1.1 1.05 1.32 ESTACIÓN1.1128 1.391 1.391 1.177 1.1235 1.32 0
1.1895832 1.486979 1.486979 1.258213 1.2010215 1.32 0.21.26690611 1.58363264 1.58363264 1.33999685 1.2790879 1.32 0.41.32518379 1.65647974 1.65647974 1.4016367 1.33792594 1.32 0.61.2748268 1.59353351 1.59353351 1.34837451 1.28708476 1.32 0.8
1.07850348 1.34812935 1.34812935 1.14072483 1.0888737 1.32 0.90.78730754 0.98413442 0.98413442 0.83272913 0.7948778 1.32 0.950.48419414 0.60524267 0.60524267 0.51212841 0.48884985 1.32 0.975
0 0 0 0 0 1.32 1
CL MAX PERFIL
0 0.2 0.4 0.6 0.8 1 1.20
0.2
0.4
0.6
0.8
1
1.2
1.4
CL MAX PERFIL0.91.040.65
Cl=Clb+CL*Cla
CL10 CL11 CL12 CL13 CL14 CL15 CL16 CL17
-0.2 0.0 0.2 0.4 0.7 0.9 1.1 1.3-0.2011 0.0 0.2 0.4022 0.6536 0.9050 1.1061 1.3073-0.2119 0.0 0.2119 0.4238 0.6887 0.9536 1.1655 1.3774-0.2280 0.0 0.2280 0.4560 0.7411 1.0261 1.2541 1.4822-0.2410 0.0 0.2410 0.4820 0.7833 1.0845 1.3256 1.5666-0.2284 0.0 0.2284 0.4569 0.7424 1.0280 1.2564 1.4849-0.1774 0.0 0.1774 0.3548 0.5765 0.7982 0.9756 1.1530-0.1079 0.0 0.1079 0.2158 0.3507 0.4856 0.5935 0.7014-0.0487 0.0 0.0487 0.0974 0.1583 0.2192 0.2680 0.31670.0000 0.0 0.0000 0.0000 0.0000 0.0000 0.0000 0.0000
Cl=Clb+CL*Cla
CL18 CL19 CL20
1.3 1.1 1.1 1.31.3073 1.1061 1.0559 1.31.3774 1.1655 1.1125 1.31.4822 1.2541 1.1971 1.31.5666 1.3256 1.2653 1.31.4849 1.2564 1.1993 1.31.1530 0.9756 0.9312 1.30.7014 0.5935 0.5665 1.30.3167 0.2680 0.2558 1.30.0000 0.0000 0.0000 1.3
CL MAX PERFIL
CRECE 0 PERFIL 0.4 CREUCE 0 DEL ALA 0.39953634CL MAX 1.65 CL MAXPENDIENTE PERFIL 0.1 PENDIENTE ALA 0.09988408ALFA CERO LEVANTAMIENTO -4 ALFA CERO LEVANTAMIENTO -4
PERFIL ALAALFA CL ALFA CL-18 -1.4000 -18 -1.39837718-17 -1.3000 -17 -1.29849309-16 -1.2000 -16 -1.19860901-15 -1.1000 -15 -1.09872492-14 -1.0000 -14 -0.99884084-13 -0.9000 -13 -0.89895676-12 -0.8000 -12 -0.79907267-11 -0.7000 -11 -0.69918859-10 -0.6000 -10 -0.5993045-9 -0.5000 -9 -0.49942042-8 -0.4000 -8 -0.39953634-7 -0.3000 -7 -0.29965225-6 -0.2000 -6 -0.19976817-5 -0.1000 -5 -0.09988408-4 0.0000 -4 0-3 0.1000 -3 0.09988408-2 0.2000 -2 0.19976817-1 0.3000 -1 0.299652250 0.4000 0 0.399536341 0.5000 1 0.499420422 0.6000 2 0.59930453 0.7000 3 0.699188594 0.8000 4 0.799072675 0.9000 5 0.898956766 1.0000 6 0.998840847 1.1000 7 1.098724928 1.2000 8 1.198609019 1.3000 9 1.29849309
10 1.4000 10 1.3983771811 1.5000 11 1.4982612612 1.6000 12 1.59814534
12.5 1.6500 13 1.5513 1.6500 14 1.514 1.6300 15.3 1.415 1.6000 16 1.316 1.5000 17 1.218 1.4000 18 1.1
-5 -4 -3 -2 -1 0 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 20-0.2
0
0.2
0.4
0.6
0.8
1
1.2
1.4
1.6
1.8
CL ALA VS ALFA CL PERFIL VS ALFA
ALFA
CL
CREUCE 0 DEL ALA 0CL MAX 1.32 CL MAX 1.04PENDIENTE PERFIL 0.107142857 PENDIENTE ALA 0.09871ALFA CERO LEVANTAMIENTO 0 ALFA CERO LEVANTAMIENTO 0
PERFIL EMPENAJE HORIZONTALALFA CL ALFA CL-17 -1.8214 -17 -1.67807-16 -1.7143 -16 -1.57936-15 -1.6071 -15 -1.48065-14 -1.5000 -14 -1.38194-13 -1.3929 -13.5 -1.332585
-12.4 -1.3286 -13 -1.28323-12 -1.2857 -12 -1.18452-11 -1.1786 -11 -1.08581-10 -1.0714 -10 -0.9871-9 -0.9643 -9 -0.88839-8 -0.8571 -8 -0.78968-7 -0.7500 -7 -0.69097-6 -0.6429 -6 -0.59226-5 -0.5357 -5 -0.49355-4 -0.4286 -4 -0.39484-3 -0.3214 -3 -0.29613-2 -0.2143 -2 -0.19742-1 -0.1071 -1 -0.098710 0.0000 0 01 0.1071 1 0.098712 0.2143 2 0.197423 0.3214 3 0.296134 0.4286 4 0.394845 0.5357 5 0.493556 0.6429 6 0.592267 0.7500 7 0.690978 0.8571 8 0.789689 0.9643 9 0.88839
10 1.0714 10 0.987111 1.1786 10.6 1.046326
12.4 1.3286 11.6 1.0413 1.3929 12.6 1.24374614 1.5000 13.5 1.33258515 1.6071 14 1.3819416 1.7143 15 1.48065 -5 -4 -3 -2 -1 0 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19
-0.2
0
0.2
0.4
0.6
0.8
1
1.2
1.4
1.6
CL PERFIL EMPENAJE VS ALFA CL EMPENAJE HORIZANTAL VS ALFA
ALFA
CL
17 1.8214 16 1.5793618 1.9286 17 1.67807
-5 -4 -3 -2 -1 0 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19-0.2
0
0.2
0.4
0.6
0.8
1
1.2
1.4
1.6
CL PERFIL EMPENAJE VS ALFA CL EMPENAJE HORIZANTAL VS ALFA
ALFA
CL
CL ALA NECESARIO 0.66ÁNGULO NECESARIO 2.60765933
-5 -4 -3 -2 -1 0 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 20-0.2
0
0.2
0.4
0.6
0.8
1
1.2
1.4
1.6
1.8
CL ALA VS ALFA CL PERFIL VS ALFA
ALFA
CL
CL EH NECESARIO 0.085ÁNGULO NECESARIO 0.8611083
-5 -4 -3 -2 -1 0 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19-0.2
0
0.2
0.4
0.6
0.8
1
1.2
1.4
1.6
CL PERFIL EMPENAJE VS ALFA CL EMPENAJE HORIZANTAL VS ALFA
ALFA
CL
-5 -4 -3 -2 -1 0 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19-0.2
0
0.2
0.4
0.6
0.8
1
1.2
1.4
1.6
CL PERFIL EMPENAJE VS ALFA CL EMPENAJE HORIZANTAL VS ALFA
ALFA
CL
-5 -4 -3 -2 -1 0 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 20-0.2
0
0.2
0.4
0.6
0.8
1
1.2
1.4
1.6
1.8
CL ALA VS ALFA CL PERFIL VS ALFA
ALFA
CL
-5 -4 -3 -2 -1 0 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19-0.2
0
0.2
0.4
0.6
0.8
1
1.2
1.4
1.6
CL PERFIL EMPENAJE VS ALFA CL EMPENAJE HORIZANTAL VS ALFA
ALFA
CL
-5 -4 -3 -2 -1 0 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19-0.2
0
0.2
0.4
0.6
0.8
1
1.2
1.4
1.6
CL PERFIL EMPENAJE VS ALFA CL EMPENAJE HORIZANTAL VS ALFA
ALFA
CL
ALAPERFIL NACA 23012
ALFA CL CD CM C/4 CM C.A. FINEZA A.-20 - - - - --18 -0.9 0.011 -81.81818182-16 -0.9 0.011 -81.81818182-14 -1.2 - --12 -1.15 - --10 -0.95 0.011 -86.36363636-8 -0.7 0.0085 -82.35294118-6 -0.5 0.008 -62.5-4 -0.3 0.0075 -40-2 -0.1 0.0075 -13.333333330 0.1 0.006 16.6666666672 0.3 0.006 504 0.55 0.0065 84.6153846156 0.75 0.0069 108.695652178 1 0.0075 133.33333333
10 1.2 0.01 12012 1.4 0.014 10014 1.55 0.0185 83.78378378416 1.7 - - - -18 1.35 0.0135 10020 - - - - -
REYNOLDS 3000m REYNOLDS 6000mVELOCIDAD 90 VELOCIDAD 84.368DENSIDAD 0.9092 DENSIDAD 0.6596
VISCOCIDAD 1.73E-05 VISCOCIDAD 1.82E-05LONGITUD 1.72E+00 LONGITUD 1.72E+00
REYNOLDS 8.11E+06 REYNOLDS 5.23E+06
ALA EMPENAJE HORIZONTALPERFIL NACA 23018 PERFIL NACA 0009
ALFA CL CD CM C/4 CM C.A. FINEZA A. ALFA-20 - - - - - -20-18 -1.3 0.015 -86.66666667 -18-16 -1.4 - - - - -16-14 -1.3 0.015 -86.66666667 -14-12 -1.15 0.0125 -92 -12-10 -0.95 0.011 -86.36363636 -10-8 -0.75 0.0095 -78.94736842 -8-6 -0.5 0.009 -55.55555556 -6-4 -0.3 0.008 -37.5 -4-2 -0.1 0.007 -14.28571429 -20 0.1 0.007 14.285714286 02 0.3 0.007 42.857142857 24 0.5 0.0075 66.666666667 46 0.7 0.0075 93.333333333 68 0.91 0.0085 107.05882353 8
10 1.15 0.01 115 1012 1.3 0.013 100 1214 1.55 0.018 86.111111111 1416 1.6 - - - - 1618 1.05 0.0095 110.52631579 1820 1 0.009 111.11111111 20
EMPENAJE HORIZONTALPERFIL NACA 0009 PERFIL NACA 4412
CL CD CM C/4 CM C.A. FINEZA A. ALFA CL- - - - - -18- - - - - -17
-0.9 0.085 -10.5882353 -16 -0.65-1 0.01 -100 -15 -0.7
-1.3 - #VALUE! -14 -0.75-1.1 0.014 -78.5714286 -13 -0.78-0.9 0.0085 -105.882353 -12 -0.8
-0.65 0.0075 -86.6666667 -11 -0.75-0.4 0.0065 -61.5384615 -10 -0.68-0.2 0.006 -33.3333333 -9 -0.55
0 0.0055 0 -8 -0.450.2 0.0055 36.3636364 -7 -0.350.4 0.006 66.6666667 -6 -0.25
0.65 0.007 92.8571429 -5 -0.150.9 0.0085 105.882353 -4 01.1 0.0105 104.761905 -3 0.071.3 0.0135 96.2962963 -2 0.171.3 0.0135 96.2962963 -1 0.271.1 0.0105 104.761905 0 0.4
1.05 0.0095 110.526316 1 0.5- - - - - 2 0.6
3 0.74 0.85 0.96 17 1.18 1.229 1.33
10 1.411 1.512 1.5513 1.614 1.6215 1.6416 1.5917 1.5518 1.47
U ALAAR
PERFIL NACA 4412 PERFIL NACA 4412 PERFIL NACA 0009 ALACD ALFA CL CD ALFA CL CD ALFA
-18 -18 0 0 -18-17 -17 0 0 -17
0.01 -16 -0.65 0.01 -16 -0.9 0.0085 -160.015 -15 -0.7 0.015 -15 -0.9 0.0085 -150.02 -14 -0.75 0.02 -14 -1.3 0.017 -14
0.022 -13 -0.78 0.022 -13 -1.3 0.017 -130.025 -12 -0.8 0.025 -12 -1.25 0.015 -120.02 -11 -0.75 0.02 -11 -1.2 0.014 -110.01 -10 -0.68 0.01 -10 -1.1 0.011 -10
0.0087 -9 -0.55 0.0087 -9 -1 0.01 -90.008 -8 -0.45 0.008 -8 -0.9 0.0087 -8
0.0075 -7 -0.35 0.0075 -7 -0.8 0.008 -70.007 -6 -0.25 0.007 -6 -0.65 0.0075 -6
0.0068 -5 -0.15 0.0068 -5 -0.55 0.007 -50.0065 -4 0 0.0065 -4 -0.4 0.0065 -40.0064 -3 0.07 0.0064 -3 -0.3 0.006 -30.0063 -2 0.17 0.0063 -2 -0.2 0.006 -20.0062 -1 0.27 0.0062 -1 -0.1 0.0055 -10.0062 0 0.4 0.0062 0 0 0.005 00.0062 1 0.5 0.0062 1 0.1 0.005 10.0062 2 0.6 0.0062 2 0.2 0.005 20.0062 3 0.7 0.0062 3 0.3 0.006 30.0064 4 0.8 0.0064 4 0.4 0.006 40.0067 5 0.9 0.0067 5 0.55 0.0065 50.0078 6 1 0.0078 6 0.65 0.007 60.0088 7 1.1 0.0088 7 0.75 0.0075 70.0109 8 1.22 0.0109 8 0.85 0.008 80.012 9 1.33 0.012 9 1 0.0095 9
0.0135 10 1.4 0.0135 10 1.1 0.0115 100.0162 11 1.5 0.0162 11 1.2 0.012 110.0172 12 1.55 0.0172 12 1.3 0.0135 120.019 13 1.6 0.019 13 1.3 0.0135 130.019 14 1.62 0.019 14 1.25 0.014 140.02 15 1.64 0.02 15 1.2 0 15
0.025 16 1.59 0.025 16 1.15 0 160.03 17 1.55 0.03 17 1.05 0 17
0.035 18 1.47 0.035 18 1 0 18
1 U EH 134.2857 Conicidad 0.5000 AR 22.8800 Conicidad 1.0000
ALA EMPENAJE HORIZONTALCL ALA CD o ALA CD i ALA CD ALA ALFA CL EH CD o EH CD i EH-1.3984 0 0.0182 0.0182 -18 -1.6781 0.0392-1.2985 0 0.0157 0.0157 -17 -1.5794 0.0347-1.1986 0.01 0.0133 0.0233 -16 -1.4807 0.0085 0.0305-1.0987 0.015 0.0112 0.0262 -15 -1.3819 0.0085 0.0266-0.9988 0.02 0.0093 0.0293 -14 -1.3326 0.017 0.0247-0.8990 0.022 0.0075 0.0295 -13 -1.2832 0.017 0.0229-0.7991 0.025 0.0059 0.0309 -12 -1.1845 0.015 0.0195-0.6992 0.02 0.0045 0.0245 -11 -1.0858 0.014 0.0164-0.5993 0.01 0.0033 0.0133 -10 -0.9871 0.011 0.0136-0.4994 0.0087 0.0023 0.0110 -9 -0.8884 0.01 0.0110-0.3995 0.008 0.0015 0.0095 -8 -0.7897 0.0087 0.0087-0.2997 0.0075 0.0008 0.0083 -7 -0.6910 0.008 0.0066-0.1998 0.007 0.0004 0.0074 -6 -0.5923 0.0075 0.0049-0.0999 0.0068 0.0001 0.0069 -5 -0.4936 0.007 0.00340.0000 0.0065 0.0000 0.0065 -4 -0.3948 0.0065 0.00220.0999 0.0064 0.0001 0.0065 -3 -0.2961 0.006 0.00120.1998 0.0063 0.0004 0.0067 -2 -0.1974 0.006 0.00050.2997 0.0062 0.0008 0.0070 -1 -0.0987 0.0055 0.00010.3995 0.0062 0.0015 0.0077 0 0.0000 0.005 0.00000.4994 0.0062 0.0023 0.0085 1 0.0987 0.005 0.00010.5993 0.0062 0.0033 0.0095 2 0.1974 0.005 0.00050.6992 0.0062 0.0045 0.0107 3 0.2961 0.006 0.00120.7991 0.0064 0.0059 0.0123 4 0.3948 0.006 0.00220.8990 0.0067 0.0075 0.0142 5 0.4936 0.0065 0.00340.9988 0.0078 0.0093 0.0171 6 0.5923 0.007 0.00491.0987 0.0088 0.0112 0.0200 7 0.6910 0.0075 0.00661.1986 0.0109 0.0133 0.0242 8 0.7897 0.008 0.00871.2985 0.012 0.0157 0.0277 9 0.8884 0.0095 0.01101.3984 0.0135 0.0182 0.0317 10 0.9871 0.0115 0.01361.4983 0.0162 0.0208 0.0370 11 1.0463 0.012 0.01521.5981 0.0172 0.0237 0.0409 12 1.0400 0.0135 0.01501.5500 0.019 0.0223 0.0413 13 1.2437 0.0135 0.02151.5000 0.019 0.0209 0.0399 14 1.3326 0.014 0.02471.4000 0.02 0.0182 0.0382 15 1.3819 0.02 0.02661.3000 0.025 0.0157 0.0990 16 1.4807 0.03 0.03051.2000 0.03 0.0134 0.1050 17 1.5794 0.04 0.03471.1000 0.035 0.0112 0.1100 18 1.6781 0.06 0.0392
EMPENAJE HORIZONTALCD EH0.03920.03470.03900.03510.04170.03990.03450.03040.02460.02100.01740.01460.01240.01040.00870.00720.00650.00560.00500.00510.00550.00720.00820.00990.01190.01410.01670.02050.02510.02720.02850.03500.03870.04660.06050.07470.0992
0.000 0.005 0.010 0.015 0.020 0.025 0.030 0.035 0.040-1.0
-0.8
-0.6
-0.4
-0.2
0.0
0.2
0.4
0.6
0.8
1.0
1.2
1.4
1.6
1.8
G. Polar Ala CL vs CD
CD Ala
CL a
la
0.000 0.005 0.010 0.015 0.020 0.025 0.030 0.035 0.040-0.1
0.1
0.3
0.5
0.7
0.9
1.1
1.3
G. Polar EH CL VS CD
CD
CL
Tren de Aterrizaje
Superficie Alar 37.8
Elemento Observaciones
1 2 llanta 0.11849 0.6 0.00376158732 2 cilindro 0.0205 0.6 0.000650793653 2 cilindro 0.06798 0.6 0.002158095244 2 cilindro 0.029659 0.6 0.000941555565 2 C. Fuselado 0.13825 0.12 0.000877777786 1 llanta 0.0707 0.6 0.001122222227 1 Placa Plana 0.04045 2 0.002140211648 1 cilindro 0.0103 0.6 0.000163492069 1 cilindro 0.01316 0.6 0.00020888889
10 1 C. Fuselado 0.055296 0.12 0.00017554286
Total 0.0122001672
Numero de Elementos
Superficie m2
Cd del elemento (superficie Frontal)
Cd' Del elemento
Densidad 0.90926 q Fl 1920.81175Velociad Ala 65 Superficie Ala 37.8
Datos del Ala
Alfa 0 del ala 2.607659332 Alfa 0 del EH 0.861108297
CREUCE 0 DEL ALA 0.399536336 CRECE 0 PERFIL 0.4
CL MAX 1.4 CL MAX 1.65
PENDIENTE ALA 0.099884084 PENDIENTE PERFIL 0.1
-4 -4
K 20U ALA 1
AR 34.2857 Conicidad 0.5000L (dist. Centro Aero) 7.262
C. Aerodinamica 1.05
0 1 2 3 4 5
CD Fus0.07 -4.00 -1.39 0.2605 0.0065 0.00060.06 -3.00 -0.39 0.3603 0.0064 0.00120.06 -2.00 0.61 0.4602 0.0063 0.00200.05 -1.00 1.61 0.5601 0.0062 0.00290.05 0.00 2.61 0.6600 0.0062 0.00400.05 1.00 3.61 0.7599 0.0062 0.00540.06 2.00 4.61 0.8598 0.0062 0.00690.06 3.00 5.61 0.9597 0.0062 0.00850.07 4.00 6.61 1.0595 0.0064 0.01040.08 5.00 7.61 1.1594 0.0067 0.01250.08 6.00 8.61 1.2593 0.0078 0.01470.09 7.00 9.61 1.3592 0.0088 0.01720.11 8.00 10.61 1.4591 0.0109 0.01980.12 9.00 11.61 1.5590 0.012 0.02260.13 10.00 12.61 1.6588 0.0135 0.02550.15 11.00 13.61 1.4000 0.0162 0.01820.16 12.00 14.61 1.3800 0.0172 0.01770.17 13.00 15.61 1.3600 0.019 0.01720.19 14.00 16.61 1.3000 0.019 0.01570.20 15.00 17.61 1.2500 0.02 0.01450.21 16.00 18.61 1.2000 0.025 0.01340.23 17.00 19.61 1.1500 0.03 0.01230.24 18.00 20.61 1.1000 0.035 0.01120.25 19.00 21.61 1.0500 0.0400 0.0102
ALFA CERO LEVANTAMIENTO
ALFA CERO LEVANTAMIENTO
aF aA CLA CDOA CDiA
0.27 20.00 22.61 1.0000 0.0450 0.0093
1 15 26 30aF CLTS/A CDTS/AyTA Fineza-4 0.220 0.024 9.1717-3 0.330 0.024 13.7705-2 0.441 0.024 18.0635-1 0.552 0.025 22.12910 0.662 0.026 25.77521 0.773 0.027 28.28242 0.884 0.029 30.34733 0.994 0.031 31.89164 1.105 0.034 32.83945 1.215 0.037 33.04436 1.326 0.041 32.63357 1.437 0.045 31.99918 1.547 0.051 30.29899 1.658 0.056 29.6189
10 1.768 0.062 28.639811 1.525 0.058 26.143112 1.517 0.060 25.202613 1.509 0.063 24.081114 1.462 0.062 23.391415 1.424 0.064 22.378716 1.387 0.069 20.133717 1.283 0.072 17.904218 1.231 0.076 16.108519 1.177 0.081 14.505320 1.121 0.086 13.0539
B max 33.0443
Densidad 0.90926 q EH 1080.456609375Velocidad EH 48.75 Superficie EH 5.72 Superficie EV
Datos del Empenaje Horizontal Datos del Empenaje Vertical
CREUCE 0 DEL ALA 0CD
CL MAX 1.32 CL MAX 1.04
PENDIENTE PERFIL 0.107142857 PENDIENTE ALA 0.09871
0 0
U EH 0.999AR 22.88 Conicidad 1
6 7 8 9 10 11
d0.0071 0.2647 -3.4036 -0.3360 -0.0407 0.00650.0076 0.3663 -2.5052 -0.2473 -0.0299 0.0060.0083 0.4678 -1.6067 -0.1586 -0.0192 0.0060.0091 0.5693 -0.7082 -0.0699 -0.0085 0.00550.0102 0.6708 0.1903 0.0188 0.0023 0.0050.0116 0.7724 1.0887 0.1075 0.0130 0.0050.0131 0.8739 1.9872 0.1962 0.0237 0.0050.0147 0.9754 2.8857 0.2848 0.0345 0.0060.0168 1.0769 3.7842 0.3735 0.0452 0.0060.0192 1.1785 4.6826 0.4622 0.0560 0.00650.0225 1.2800 5.5811 0.5509 0.0667 0.0070.0260 1.3815 6.4796 0.6396 0.0774 0.00750.0307 1.4830 7.3781 0.7283 0.0882 0.0080.0346 1.5846 8.2765 0.8170 0.0989 0.00950.0390 1.6861 9.1750 0.9057 0.1096 0.01150.0344 1.4230 10.4381 1.0303 0.1247 0.0120.0349 1.4027 11.4584 1.1311 0.1369 0.01350.0362 1.3823 12.4788 1.2318 0.1491 0.01350.0347 1.3214 13.5397 1.3365 0.1618 0.0140.0345 1.2705 14.5906 1.4402 0.1744 0.01450.0384 1.2197 15.6414 1.5440 0.1869 0.0150.0423 1.1689 16.6922 1.1000 0.1332 0.01550.0462 1.1181 17.7430 1.0800 0.1307 0.0160.0502 1.0673 18.7939 1.0500 0.1271 0.0165
ALFA CERO LEVANTAMIENTO
ALFA CERO LEVANTAMIENTO
CDA aEH CLEH CL’EH CDoEH
0.0543 1.0164 19.8447 1.0000 0.1211 0.0170
4.4975Datos del Empenaje Vertical CD BAR
0.011 0.6
SUPERFICIE BAR
0.3
12 13 14 15 16 17 18
0.0016 0.0081 0.0010 0.2198 0.0013 0.0095 0.00000.0009 0.0069 0.0008 0.3304 0.0013 0.0095 0.00000.0004 0.0064 0.0008 0.4410 0.0013 0.0095 0.00000.0001 0.0056 0.0007 0.5517 0.0013 0.0095 0.00000.0000 0.0050 0.0006 0.6623 0.0013 0.0095 0.00000.0002 0.0052 0.0006 0.7729 0.0013 0.0095 0.00000.0005 0.0055 0.0007 0.8835 0.0013 0.0095 0.00000.0011 0.0071 0.0009 0.9941 0.0013 0.0095 0.00000.0019 0.0079 0.0010 1.1048 0.0013 0.0095 0.00000.0030 0.0095 0.0011 1.2154 0.0013 0.0095 0.00000.0042 0.0112 0.0014 1.3260 0.0013 0.0095 0.00000.0057 0.0132 0.0016 1.4366 0.0013 0.0095 0.00000.0074 0.0154 0.0019 1.5472 0.0013 0.0095 0.00000.0093 0.0188 0.0023 1.6579 0.0013 0.0095 0.00000.0114 0.0229 0.0028 1.7685 0.0013 0.0095 0.00000.0148 0.0268 0.0032 1.5247 0.0013 0.0095 0.00000.0178 0.0313 0.0038 1.5169 0.0013 0.0095 0.00000.0211 0.0346 0.0042 1.5091 0.0013 0.0095 0.00000.0249 0.0389 0.0047 1.4618 0.0013 0.0095 0.00000.0289 0.0434 0.0053 1.4244 0.0013 0.0095 0.00000.0332 0.0482 0.0058 1.3869 0.0013 0.0095 0.00000.0169 0.0324 0.0039 1.2832 0.0013 0.0095 0.00000.0162 0.0322 0.0039 1.2307 0.0013 0.0095 0.00000.0154 0.0319 0.0039 1.1771 0.0013 0.0095 0.0000
CDiEH CDEH CD’EH CLTS/A CD’EV CD’BAR CD’M
0.0139 0.0309 0.0037 1.1211 0.0013 0.0095 0.0000
Cuerda AeroPendiente CD Boom 1.05
0.35 0.6 Cuerfa Flap0.453
SUPERFICIE FUS Superficie Boom Superficie Flap Grados
1.237 0.908 1.655 30
19 20 21 22 23 24
0.0122 0.0021 0.0016 0.0281 0.1313 0.00620.0122 0.0020 0.0014 0.0278 0.1313 0.00620.0122 0.0019 0.0014 0.0276 0.1313 0.00620.0122 0.0017 0.0013 0.0273 0.1313 0.00620.0122 0.0016 0.0012 0.0270 0.1313 0.00620.0122 0.0017 0.0013 0.0273 0.1313 0.00620.0122 0.0019 0.0014 0.0276 0.1313 0.00620.0122 0.0020 0.0014 0.0278 0.1313 0.00620.0122 0.0021 0.0016 0.0281 0.1313 0.00620.0122 0.0025 0.0018 0.0287 0.1313 0.00620.0122 0.0026 0.0019 0.0290 0.1313 0.00620.0122 0.0029 0.0022 0.0295 0.1313 0.00620.0122 0.0036 0.0026 0.0307 0.1313 0.00620.0122 0.0039 0.0029 0.0313 0.1313 0.00620.0122 0.0044 0.0032 0.0321 0.1313 0.00620.0122 0.0048 0.0035 0.0329 0.1313 0.00620.0122 0.0052 0.0038 0.0337 0.1313 0.00620.0122 0.0057 0.0042 0.0345 0.1313 0.00620.0122 0.0061 0.0045 0.0353 0.1313 0.00620.0122 0.0065 0.0048 0.0361 0.1313 0.00620.0122 0.0070 0.0051 0.0369 0.1313 0.00620.0122 0.0074 0.0054 0.0377 0.1313 0.00620.0122 0.0078 0.0058 0.0385 0.1313 0.00620.0122 0.0083 0.0061 0.0393 0.1313 0.0062
CD’TA CD’FUS CD’boom 1.05 CD’PAR DCL’ DCD’
0.0122 0.0087 0.0064 0.0401 0.1313 0.0062
Radianes
0.52359878
25 26 27 28 29
0.3511 0.0240 0.0423 0.0362 0.03010.4618 0.0240 0.0424 0.0362 0.03020.5724 0.0244 0.0428 0.0366 0.03060.6830 0.0249 0.0433 0.0371 0.03110.7936 0.0257 0.0441 0.0379 0.03190.9042 0.0273 0.0457 0.0395 0.03351.0149 0.0291 0.0475 0.0413 0.03531.1255 0.0312 0.0495 0.0434 0.03731.2361 0.0336 0.0520 0.0458 0.03981.3467 0.0368 0.0552 0.0490 0.04301.4573 0.0406 0.0590 0.0528 0.04681.5680 0.0449 0.0633 0.0571 0.05111.6786 0.0511 0.0694 0.0633 0.05721.7892 0.0560 0.0743 0.0682 0.06211.8998 0.0617 0.0801 0.0739 0.06791.6561 0.0583 0.0767 0.0705 0.06451.6483 0.0602 0.0786 0.0724 0.06641.6405 0.0627 0.0810 0.0749 0.06881.5931 0.0625 0.0809 0.0747 0.06871.5557 0.0636 0.0820 0.0758 0.06981.5183 0.0689 0.0873 0.0811 0.07511.4145 0.0717 0.0900 0.0839 0.07781.3621 0.0764 0.0948 0.0886 0.08261.3085 0.0812 0.0995 0.0934 0.0873
CLTC/A CDTS/AyTA CDTC/AyT CDTC/TA CDTC/A
1.2524 0.0859 0.1043 0.0981 0.0921
0.020 0.030 0.040 0.050 0.060 0.070 0.080 0.0900.0
0.2
0.4
0.6
0.8
1.0
1.2
1.4
1.6
1.8
2.0
Polar del Avión Limpio
CD
CL