1. Design Chapter 8 First Half

2. Design Requirements and Specifications Payload Range Cruising Speed Takeoff & Landing Distance Ceiling

3. Economic Requirements Cost Fuel Consumption Maintainability Reliability

4. Airworthiness Requirements Design must meet FAA standards for safety FAA is responsible for safety of all civil aircraft Federal Air Regulations Part 23 –Light Planes 12,500 lbs or less Federal Air Regulations Part 25 –Airworthiness Standards: Transport Category Airplanes

5. Design Phase Conceptual Design –General concept of what the plane will look like –Jet/prop, single/multi, high wing/low wing, fixed gear/retractable gear Preliminary Design –The aerodynamic design, consideration of aerodynamics in arriving at overall configuration

6. Design Phase Detail Design –The final stage –Design of supporting structure –Modification to preliminary desugn decisions

7. Initial Conception Step one: Study the design & specifications Step two: Determine what characteristics to shoot for in payload, speed, range, takeoff distance, landing distance, climb rate, & ceiling.

8. Terms Wing loading –the ratio of weight to wing area –the average weight that each unit of wing area must carry –W/S Power loading –the amount of power per unit of weight –P/W

9. Fuselage Design The fuselage design shape for aerodynamic efficiency (low drag) Optimum shape for a typical four-place light plane is a fuselage length of approx. 24 feet with a diameter of 8 feet Figure 8-1 p. 217 Figure 8-2 p. 218, figure 8-3, 8-4

10. Fuselage Design Tandem/ Side by side Seat pitch Aerodynamic stand point Cabin Height

11. Wing Design High/ Low configuration High Wing –better L/D ratio, lateral stability, shorter landing distance, better crash & fire protection Low Wing –better landing gear support, roll maneuverability, easier refueling, shorter takeoff distance, crash energy absorption

12. Planform Selection Planform figure 8-7 combination of rectangular & tapered wing planform Optimum airfoil –low drag coefficient, min. drag at design lift coefficient, max. lift coefficient, pitching moment coefficient, sufficient thichness for spar, fuel, & landing gear

13. Increased Thickness Increases maximum lift coefficient Increase drag coefficient Provides greater space for structure and fuel

14. Increased Camber Increases design lift coefficient Increases pitching moment Increases lift coefficient

15. Power Plant Selection Power to weight to ratio actual engine dimensions location of the carburetor best choice of prop cowling design

16. Quiz on Chapter 8

17. Quiz on chapter 8 List and explain two design obstacles to study when designing a plane.