Glasair III - the AOE home page

Glasair IIIMarch 30, 2005Anne CarobineRandy FitzwaterDerek Jackson

Basic GeometrySrefSwingStailSwetbAR__87.6 ft 281.3 ft 215.54 ft 2393.81 ft 223.3 ft6.200.750°

Weight BreakdownTOGWW emptyW fuelW payloadW fuel /TOGWW payload /TOGW2400 lbs1625 lbs438 lbs337 lbs0.14040.1825

High Lift DevicesStandard plain flaps or optional slotted flapsStall SpeedPlain Flap80 mphSlotted Flap73 mphC Lmax24.5°1.802.16Pitch Angle @C Lmax20.4°*Using GW = 2400 pounds, sea level standard conditions.*Pitch angle doesn’t account for changes in lift curve slope with flap deflection.

Tail Scrape Angle22°

Control “Effectiveness”Flaps b flaps /b = 0.475 S flaps /S = 0.075ElevatorsTotal Area = 4.85 sq ftRuddersArea = 5.35 sq ftAilerons Total Area = 4.79 sq ft Span = 3.3 ft b aileron /b = 0.3342 S aileron /S = 0.1094

Airfoilt/c = 12.5%

Propulsion SystemEnginePropellerPowerP/WLycoming IO-540-KSeriesHartzell80” diameter(two-bladed)300 hp0.125 hp/lb

Static Stability Neutral Point – 0.521c Assumed CG – 0.25c Static Margin – 27.1%c – mean aerodynamic chord (3.76 ft)From: VLMpc

Load Split92% of lifton wing fortrimmedcruiseFrom: VLMpc

Planform Geometry0Planform Geometry for VLMpc-2-4-6x-8-10-12-14-16-16 -14 -12 -10 -8 -6 -4 -2 0 2 4y

Friction ProgramWettedArea (ft 2 )C doM=0.1 alt=0C doM=0.15 alt=0C doM=0.35alt=8000Wing121.5880.006800.006320.00565Fuselage232.660.009070.008510.00768HorizontalTail31.0780.001740.001610.00143VerticalTail8.4820.000480.000450.00040Total Cdo = 0.01809 0.01688 0.01515

Range AnalysisEquations:Inputs: W i=2400 lbs, W f=2000 lbs, C bhp=0.42 lb/hp/hr, _ p,e=0.8, AR=6.2Results:550ηR =CbhppLD⎛⎜Wln⎝WConclusion: There is a discrepancy betweenour analysis and Glasair’s posted resultsif⎞⎟⎠LD= 1219 ⇒ LR mi = 10.0 ⇒ C = D0 0.03873DLC D 0= 0.01515 ⇒ = 16.0 ⇒ R = 1949 miDLC D 0= 0.01809 ⇒ = 14.7 ⇒ R = 1784 miD=12πAReC D 0Glasair’s posted rangeOur estimation

Basic PerformanceTop Speed (sea level)Top Speed (18000 ft)Never Exceed SpeedSolo Weight Rate of ClimbGross Weight Rate of ClimbRoll RateCeiling (normally aspirated)Ceiling (turbocharged)300 mph327 mph (turbo)335 mph2990 ft/min2140 ft/min140 °/sec24000 ft30000+ ft

Cruise ConditionsAltitudeSpeedC L24000 ft313 mph0.25417500 ft290 mph0.2388000 ft258 mph0.222* Assuming weight = 2400 pounds.

Spanload0.4Glasair Spanload0.350.30.25c a vg/C Lc0.20.15AR=6.2λ=0.75α=4°0.10.05Planar Wing, e=0.972261° Washout e=0.99009Elliptic Spanload00 0.1 0.2 0.3 0.4 0.5 0.6 0.7 0.8 0.9 1η=y/(b/2)*Using Lifting Line Theory

Band-aids

Pricing InformationKit Prices Total = $44,950 Fuselage = $11,450 Wing = $11,450 Landing Gear = $13,950 Final Assembly = $10,950 Lycoming I0-540-K1H5 = $47,447

Referencewww.newglasair.com