Aerodynamics PDR # 2 AAE451 – Team 3 November 18, 2003 Brian Chesko Brian Hronchek Ted Light Doug Mousseau Brent Robbins Emil Tchilian

Conventional Tail – NACA 0012 Aircraft Walk Around Wing Span = 14.6 ft A/C Length = 10 ft Conventional Tail – NACA 0012 Pusher Internal Pod Low wing – Clark Y Tricycle Gear

Dimensions Wing Horizontal Tail Vertical Tail* Area (ft2) 42.9 12 2.4 Aspect Ratio 5 3 0.6 *Still some issues with sizing vertical tail

Alpha L=0 Determination Xfoil runs of ClarkY foil at cruise and takeoff Cruise: αL=0= -3.5° Takeoff no flap: αL=0 = -3.8° Takeoff 10° flap: αL=0 = -7° Takeoff 15° flap: αL=0 = -7.8°

Flaperons necessary to meet stall requirements Stall Performance CL needed = 1.19 Wing without flaps reaches CL at a=13° Wing stall possible Wing with 15° flap deflection reaches CL at 11° Required CL Flaperons necessary to meet stall requirements

NACA Empirical Data For ClarkY Foil Approximate Stall angle ~14° http://naca.larc.nasa.gov/reports/1933/naca-report-431/

Stall Performance Required CL CD = 0.119 at required CL

Cruise Performance CL needed = 0.366 CL achieved at a = 1.9° Total Lift produced = 57 lbf Total Drag = 2.6 lbf, L/D =21

NACA Empirical Data For ClarkY Foil is approximately 22 http://naca.larc.nasa.gov/reports/1933/naca-report-431/

Operating Parameters Stall 1.19 11° 15° 0.119 10 T/O 0.989 8.8° 0.084 CL a Flap Deflection CD L/D Stall 1.19 11° 15° 0.119 10 T/O 0.989 8.8° 0.084 12 Cruise 0.366 1.9° 0° 0.014 24

Horizontal Tail CL = -0.32 required of horizontal tail at cruise AR = 3 Span = 6 Chord = 2 Requires Tail Angle of -5° CL = -0.32 required of horizontal tail at cruise

Fuselage Drag Assumptions Cf for turbulent flow Fuselage approximated as box Interference factor, Q, 1.2 (low end of unfilleted low wings) FF from Raymer Eq. (12.31) 1.33 ft 0.67 ft 5 ft

Drag Build Up at Cruise Component CD Drag Wing 0.014 2.6 lbf Fuselage 0.00458 0.64 lbf Horizontal Tail 0.0179 0.75 lbf More to come…

Summary Wing Horizontal Tail Foil: ClarkY Foil: NACA 0012 Taper Ratio = 1 Dihedral Angle = 5° AR = 5 S = 42 ft2 Angle of Incidence = 2° Horizontal Tail Foil: NACA 0012 Taper Ratio = 1 Dihedral Angle = 0º AR = 3 S = 12 ft2 Angle of Incidence = -5°

Questions?