Aether Aerospace AAE 451 September 19, 2006 Aerodynamics 1 QDR Aether Aerospace AAE 451 September 19, 2006 Mark Davis Ashley Gordon Hank Kneitz Ryan Mulligan Joshua Rodewald Brandon Wampler Mathieu Hautier Samantha Pearcy

Aircraft Geometry The Angry Mosquito 4.4 ft 0.285 ft 3.54 ft 0.75 ft Quarter chord to quarter chord 0.75 ft The Angry Mosquito May 24, 2019 AAE 451, Aether Aerospace

Aerodynamic Design Point Max speed at steady, level flight α = 0º V = 175 ft/s (~120 mph) Sea level From vehicle sizing W = 5.5 lb S = 3.25 ft2 (W/S) = 1.7 lb/ft2 May 24, 2019 AAE 451, Aether Aerospace

Wing Airfoil Selection Process Airfoil Criterion “Low” Reynolds number, Re = 808,000 High lift to drag ratio Machinable geometry Research RC pylon racers Agricultural crop dusters Single engine, homebuilt May 24, 2019 AAE 451, Aether Aerospace

Wing Geometry Design Process Set Parameters: Aspect ratio, AR = 6 Initial value based on team experience Will be optimized for minimum induced and parasite drag taking structural considerations into account Taper ratio, l = 0.45 Best approximation for elliptical loading Calculate based on the above: Span, b Root/tip chords, Croot Ctip TE sweep, LTE TBD May 24, 2019 AAE 451, Aether Aerospace

Wing Geometry Wing Airfoil MH 24 S 3.25 ft2 Aspect Ratio 6 Taper Ratio 0.45 Leading Edge Sweep 0° Quarter Chord Sweep -3.6° Trailing Edge Sweep -24.5° Dihedral yes Quarter chord line 3.6° .45 ft 1 ft 24.5° 2.2 ft May 24, 2019 AAE 451, Aether Aerospace

Wing Airfoil Section MH-24 Used on pylon racers Optimized for “low” Re May 24, 2019 AAE 451, Aether Aerospace

Fuselage Design Based on Raymer historical data From Raymer, Table 6.3 Agricultural aircraft Homebuilt – metal/wood From Raymer, Table 6.3 a = 4 C = .23 Wo = 5.5 lbs Length = 5.9 ft May 24, 2019 AAE 451, Aether Aerospace

Tail Geometry Design Process Calculate required tail areas Historical data from Raymer cHT = 0.5 cVT = 0.04 SVT = 0.165 ft2 SHT = 0.333 ft2 May 24, 2019 AAE 451, Aether Aerospace

Tail Geometry Design Process V-Tail consideration V-tail requires same total tail area as conventional configuration Stails = 0.5 ft2 (total - conventional) Sv-tail = 0.25 ft2 per tail Dihedral angle 35º May 24, 2019 AAE 451, Aether Aerospace

Tail Geometry V-Tail Airfoil NACA 0009 S 0.25 ft2 - each Aspect Ratio 3.25 Taper Ratio 0.45 Leading Edge Sweep 0° Quarter Chord Sweep -6.66° Trailing Edge Sweep -29° Dihedral -35° Quarter chord line 6.66° .17 ft 0.38 ft 29° 0.9 ft May 24, 2019 AAE 451, Aether Aerospace

Tail Airfoil Section NACA 0009 Symmetric Low t/c May 24, 2019 AAE 451, Aether Aerospace

Aircraft Wetted Area Calculations May 24, 2019 AAE 451, Aether Aerospace

Fuselage Wetted Area Estimation Use scaled grid to estimate top and side fuselage areas Top Area ~ 3 ft2 Side Area ~ 2.8 ft2 1 sq box = 0.25 sq ft May 24, 2019 AAE 451, Aether Aerospace

Aircraft Drag Polar e = 0.75 Cfe = 0.006 k = 0.0707 CDo = 0.032 Historical data from Raymer CDo = 0.032 e = 0.75 Historical data from Raymer k = 0.0707 May 24, 2019 AAE 451, Aether Aerospace

Aircraft Drag Polar May 24, 2019 AAE 451, Aether Aerospace

Aircraft Lift Polar Cla = 8.3/rad Clo = 0.139 Raymer “90% est” From XFOIL & online data Clo = 0.139 From XFOIL & online data Raymer “90% est” 2-D to 3-D CLo = 0.9 Clo CLo = 0.125 CLa = 7.95 /rad May 24, 2019 AAE 451, Aether Aerospace

Lift Coefficient Curve *a in radians /rad May 24, 2019 AAE 451, Aether Aerospace

Maximum Lift Coefficient Justification Wind Tunnel Data: NACA 0009 Wind Tunnel Data: NACA 64-006 MH 24 Clmax = 1.0 2-D CLmax = 0.9 3-D CLmax,flaps = 1.6 Approximate a 0.7 increase to allow room for controllability May 24, 2019 AAE 451, Aether Aerospace

The Angry Mosquito

Wing/Tail Geometry Equations Span Root chord Tip chord TE sweep c/4 sweep May 24, 2019 AAE 451, Aether Aerospace

Overview Aircraft Geometry Airfoil Selection Wing and tail geometry Aspect Ratio Taper Ratio Sweep angle Dihedral Angle Aircraft wetted area Key Coefficients Lift coefficient Drag Polar Maximum lift coefficient May 24, 2019 AAE 451, Aether Aerospace