1. AAE 451 AERODYNAMICS QDR 2 TEAM 4 Jared Hutter, Andrew Faust, Matt Bagg, Tony Bradford, Arun Padmanabhan, Gerald Lo, Kelvin Seah November 6, 2003

2. TEAM4 OVERVIEW Concept Review Wing and Tail Aerodynamic Parameters Aircraft Parameters 3-View Drawings of Aircraft Follow-Up Actions

3. TEAM4 CONCEPT REVIEW High Wing S = 47.8 ft 2 b = 15.5 ft, c = 3.1 ft AR = 5 Twin Booms 3 ft apart; 7.3 ft from Wing MAC to HT MAC Twin Engine 1.8 HP each Avionics Pod 20 lb; can be positioned front or aft depending on requirements Empennage Horizontal and Vertical Tails sized using modified Class 1 Approach (per D & C QDR 1)

4. TEAM4 WING & TAIL PARAMETERS Main WingHorz TailVert Tail Aspect Ratio53.22.1 Sweep Angle0010  Taper Ratio110.6 Dihedral Angle0  0  N.A. Incidence Angle2.5  -2.5  N.A. Maximum Lift Coefficient, C L max 1.330 Zero Angle-of-Attack Lift Coefficient, C L 0 0.335 Lift Curve Slope, C L  0.104 deg -1 Parasitic Drag Coefficient, C D 0 0.020 Induced Drag Coefficient, C D i 0.178 Zero Angle-of-Attack Moment Coefficient, C M 0 -0.059 Moment Curve Slope, C M  -0.022 deg -1 Aircraft Wetted Area  116.48 ft 2

5. TEAM4 AIRCRAFT PARAMETERS Lift Coefficient C L = C L  *  + C L  e *  elevator + C L0 C L = 0.1223(deg -1 )*  + 0.0145(deg -1 )*  elevator + 0.5124 Lift Curve Slope C L  = f(C L  W, C L  HT,  HT,  w)   HT = Ratio of dynamic pressure. Mostly caused by propeller wash and velocity Downwash, w = Caused by main wing’s vortex flow on tail. Changes effective angle of attack for the tail. Positive Negative

6. TEAM4 AIRCRAFT PARAMETERS Lift Curve Slope for Elevator Deflection C L  e = f(elevator size, horizontal tail planform) Zero Angle of Attack Lift Coefficient C L0 = f(C L0W, C L0HT,  HT, incident angles)   HT = Ratio of dynamic pressure. Mostly caused by propeller wash and velocity Incident angles are for both main wing and horizontal tail

7. TEAM4 AIRCRAFT PARAMETERS Moment Coefficient C M = C M  *  + C M  e *  elevator + C M0 C M = -0. 0225(deg -1 )*  + (-0.0027)(deg -1 )*  elevator + 0.0280 Moment Curve Slope C M  = f(dC M /dC L, C L )  dC M /dC L = f(CG, Aerodynamic Center of Aircraft)

8. TEAM4 AIRCRAFT PARAMETERS Zero Angle of Attack Moment Coefficient C M0 = f(C M0_W, C M0_HT [both about the CG]) LIFT WEIGHT Aerodynamic Center

9. TEAM4 AIRCRAFT PARAMETERS Aircraft C L and C M equations have velocity, altitude, and power setting embedded in them Tried different altitudes and velocities with both engines and a single engine Changes in C L and C M equations were less then 0.001 Aircraft C L higher then wing C L, as a result of prop- wash and lift from the horizontal tail past some the angle of incidence

10. TEAM4 TOP VIEW 7.3 ft 15.52 ft Aspect Ratio: 5 3.0 ft 2.1 ft 3.1 ft SCALED 6.7 ft

11. TEAM4 PROFILE & FRONT VIEWS 3.1 ft 15.52 ft 2.1 ft 1.8 ft SCALED

12. TEAM4 FOLLOW-UP ACTIONS Trim Diagrams Further verification of C L and C M data Update Dynamics & Controls group with regards to the change in control surfaces, and the changes in C L and C M

13. AAE 451 ?