AAE 451 Aircraft Design First Flight Boiler Xpress November 21, 2000 Team Members Oneeb Bhutta, Matthew Basiletti , Ryan Beech, Mike Van Meter Professor Dominick Andrisani

3-D Views 11ft 6ft

Aerodynamic Design Issues Lift Low Reynolds Number Regime Slow Flight Requirements Drag Power Requirements Accurate Performance Predications Stability and Control Trimmability Roll Rate Derivatives

Low Reynolds Number Challenges Separation Bubble-to be avoided! Laminar Flow -more Prone to Separation Airfoil Sections designed for Full-sized Aircraft don’t work well for below Rn=800,000 Our Aircraft Rn=100,000-250,000

Airfoil Selection Wing: Tail sections: Selig S1210 CLmax = 1.53 Incidence= 3 deg Tail sections: flat plate for Low Re Incidence = -5 deg

Drag Prediction Assume Parabolic Drag Polar Based on Empirical Fit of Existing Aircraft

Parasite Drag Drag Build-up Method of Raymer (Ref. Raymer eq.12.27 & eq.12.30) Blasius’ Turbulent Flat Plate- Adjusted for Assumed Surface Roughness

Drag Polar Aircraft Drag Polar CL 0.2 0.4 0.6 0.8 1 1.2 1.4 1.6 1.8 0.02 0.04 0.06 0.08 0.1 0.12 0.14 0.16 Aircraft Drag Polar CL CD CDi CDo

Power Required Predict: Power required for cruise Battery energy for 15 20 25 30 35 40 16 18 22 24 26 28 32 Velocity [ft/s] Power Required [ft-lb/s] Predict: Power required for cruise Battery energy for

Aerodynamic Properties Wetted area = 44.5 sq.ft. Span Efficiency Factor = 0.75 CLa = 5.3 / rad CL de = 0.4749 /rad L/Dmax = 15.5 Vloiter = 24 ft/s CLmax = 1.53 CLcruise = 1.05 Xcg = 0.10-0.38 (% MAC) Static Margin = 0.12 at Xcg = 0.35

Stability Diagram Cmcg CL elev deflect=-8 deg -4 4 8 0.2 0.4 0.6 0.8 1 4 8 0.2 0.4 0.6 0.8 1 1.2 1.4 1.6 1.8 -0.4 -0.3 -0.2 -0.1 0.1 0.3 CL Cmcg

Flow Simulation

Parasite Drag CDo for Wing and Tail surfaces For Fuselage, booms & pods (Ref. Raymer eq.12.31 & eq.12.33)

Tail Geometry Horizontal Tail: Area = 2.2 Span = 3.0ft Chord = 0.73ft Vh = 0.50 Vertical Tail- 25% added Area = 1.75 sq.ft Span = 1.63 ft Chord = 0.60 ft Vv = 0. 044

Control Surface Sizing: Elevator Area Ratio = 0.30 Chord = 2.7 in. Rudder Area Ratio = 0.40 Single rudder of chord = 7.5 in. Ailerons Area Ratio = 0.10 Aileron chord = 3 in.

Equipment Layout & CG. Controls equipment Propulsion component Rotation angle = 10deg Tip Back angle= 15deg Controls equipment Propulsion component Airframe component 17.54 in. Miscellaneous Weight

Equipment Layout (3-D)

Landing Loads Vland=1.3Vstall=25ft/s g = -5 deg Vvert=2.2ft/s Vland=1.3Vstall=25ft/s For d = 1 in., k = 15.2 lb/in For 1 inch strut travel, peak load = 15.2 lb sspar = 240 psi on landing

Static Margin, Aerodynamic Center, and c.g. Xac = 0.46 Xcg = 0.35 SM = 0.11

Horizontal and Vertical Tail Sizing Vh - Horizontal tail volume coefficient = 0.50 Vv - Vertical tail volume coefficient = 0.044

Control Surface Sizing Based on historical data from Roskam Part II Tables 8.1 and 8.2. Homebuilts Single Engine 0.095 0.08 0.42 0.36 0.44 0.42

Control Surface Sizing (cont.) Sa = 1.35ft2 Sr = 0.80ft2 Se = 1.00ft2 Max. surface deflection is 15 deg.

Climb Performance Max. Climb Angle, G G = 7.3 deg.

Turning Performance Maximum turn rate r = 50ft Vmax = 28ft/s Y= 0.28 rad/s

Propulsion Design Issues Power Power required Power available Endurance Can we complete the mission Verification Motor test to take place this week

Power Power required is determined by aircraft Power available comes from the motor

System Efficiencies Propeller Gearbox Motor Speed Controller 60-65% 95% Motor 90% Speed Controller Total System Efficiency 50.7%

System Components Propeller Gearbox Motor Speed Controller Freudenthaler 16x15 and 14x8 folding Gearbox “MonsterBox” (6:1,7:1,9.6:1) Motor Turbo 10 GT (10 cells) Speed Controller MX-50

Economics Preliminary Design Testing 525 man-hours @ $75 = $39,375 $81.70 in materials

Economics Prototype Manufacturing Flight Testing 300 man-hours @ $75 = $22,500 $417.35 in materials Flight Testing $900 Prototype manufacturing budget $200 max

The Budget

Total Project Cost The Bottom Line $67,024.05

Questions?