glasair iii - virginia techmason/mason_f/glassairiii.pdfglasair iii anne carobine ... lycoming...
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![Page 1: Glasair III - Virginia Techmason/Mason_f/GlassairIII.pdfGlasair III Anne Carobine ... Lycoming IO-540-K Series Engine. Static Stability ... our analysis and Glasair’s posted results](https://reader033.vdocuments.us/reader033/viewer/2022050902/5aa4092e7f8b9a185d8b6c0e/html5/thumbnails/1.jpg)
Glasair III
Anne CarobineRandy FitzwaterDerek Jackson
March 30, 2005
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Basic Geometry
0°_
0.75_
6.20AR
23.3 ftb
393.81 ft2Swet
15.54 ft2Stail
81.3 ft2Swing
87.6 ft2Sref
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Weight Breakdown
0.1825Wpayload /TOGW
0.1404Wfuel /TOGW
337 lbsWpayload
438 lbsWfuel
1625 lbsWempty
2400 lbsTOGW
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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.
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Tail Scrape Angle
22°
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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
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Airfoil
t/c = 12.5%
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Propulsion System
0.125 hp/lbP/W
300 hpPower
Hartzell
80” diameter
(two-bladed)
Propeller
Lycoming IO-540-KSeries
Engine
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Static Stability Neutral Point – 0.521c Assumed CG – 0.25c Static Margin – 27.1%
c – mean aerodynamic chord (3.76 ft)
From: VLMpc
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Load Split
92% of lifton wing fortrimmedcruise
From: VLMpc
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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
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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
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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
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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)
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Cruise Conditions
0.222258 mph8000 ft
0.238290 mph17500 ft
0.254313 mph24000 ft
CLSpeedAltitude
* Assuming weight = 2400 pounds.
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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
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Band-aids
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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
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Reference
www.newglasair.com