Glasair III

Anne CarobineRandy FitzwaterDerek Jackson

March 30, 2005

Basic Geometry

0°_

0.75_

6.20AR

23.3 ftb

393.81 ft2Swet

15.54 ft2Stail

81.3 ft2Swing

87.6 ft2Sref

Weight Breakdown

0.1825Wpayload /TOGW

0.1404Wfuel /TOGW

337 lbsWpayload

438 lbsWfuel

1625 lbsWempty

2400 lbsTOGW

High Lift Devices Standard plain flaps or optional slotted flaps

2.161.80CLmax

24.5°20.4°Pitch Angle @CLmax

73 mph80 mphStall Speed

Slotted FlapPlain Flap

*Using GW = 2400 pounds, sea level standard conditions.*Pitch angle doesn’t account for changes in lift curve slope with flap deflection.

Tail Scrape Angle

22°

Control “Effectiveness” Flaps

bflaps/b = 0.475 Sflaps/S = 0.075

Elevators Total Area = 4.85 sq ft

Rudders Area = 5.35 sq ft

Ailerons Total Area = 4.79 sq ft Span = 3.3 ft baileron/b = 0.3342 Saileron/S = 0.1094

Airfoil

t/c = 12.5%

Propulsion System

0.125 hp/lbP/W

300 hpPower

Hartzell

80” diameter

(two-bladed)

Propeller

Lycoming IO-540-KSeries

Engine

Static Stability Neutral Point – 0.521c Assumed CG – 0.25c Static Margin – 27.1%

c – mean aerodynamic chord (3.76 ft)

From: VLMpc

Load Split

92% of lifton wing fortrimmedcruise

From: VLMpc

Planform Geometry

-16 -14 -12 -10 -8 -6 -4 -2 0 2 4-16

-14

-12

-10

-8

-6

-4

-2

0

x

y

Planform Geometry for VLMpc

Friction Program

0.000400.000450.000488.482VerticalTail

0.001430.001610.0017431.078HorizontalTail

0.00768 0.008510.00907232.66Fuselage

0.005650.006320.00680121.588Wing

Cdo

M=0.35alt=8000

Cdo

M=0.15 alt=0

Cdo

M=0.1 alt=0

WettedArea (ft2)

Total Cdo = 0.01809 0.01688 0.01515

Range Analysis Equations:

Inputs: Wi=2400 lbs, Wf=2000 lbs, Cbhp=0.42 lb/hp/hr, _p,e=0.8, AR=6.2

Results:

Conclusion: There is a discrepancy betweenour analysis and Glasair’s posted results

⎟⎟⎠

⎞⎜⎜⎝

⎛=

f

i

bhp

p

W

W

D

L

CR ln

550η

0

Re

2

1

DC

A

D

L π=

03873.00.101219 0 =⇒=⇒= DCD

LmiR

miRD

LCD 19490.1601515.00 =⇒=⇒=

miRD

LCD 17847.1401809.00 =⇒=⇒=

Glasair’s posted range

Our estimation

Basic Performance

327 mph (turbo)Top Speed (18000 ft)

30000+ ftCeiling (turbocharged)

24000 ftCeiling (normally aspirated)

140 °/secRoll Rate

2140 ft/minGross Weight Rate of Climb

2990 ft/minSolo Weight Rate of Climb

335 mphNever Exceed Speed

300 mphTop Speed (sea level)

Cruise Conditions

0.222258 mph8000 ft

0.238290 mph17500 ft

0.254313 mph24000 ft

CLSpeedAltitude

* Assuming weight = 2400 pounds.

0 0.1 0.2 0.3 0.4 0.5 0.6 0.7 0.8 0.9 10

0.05

0.1

0.15

0.2

0.25

0.3

0.35

0.4Glasair Spanload

η=y/(b/2)

cCL/cav

g AR=6.2λ=0.75α=4°

Planar Wing, e=0.972261° Washout e=0.99009Elliptic Spanload

Spanload

*Using Lifting Line Theory

Band-aids

Pricing Information Kit Prices

Total = $44,950

Fuselage = $11,450

Wing = $11,450

Landing Gear = $13,950

Final Assembly = $10,950

Lycoming I0-540-K1H5 = $47,447

Reference

www.newglasair.com