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Design
| Term | Definition |
|---|---|
| What are Performance design drivers? | 1.)Wing Loading meet airworthiness regulation requirements and Design Specification requirements 2.)Max speed + Minimum Climb gradient - Drive Low wing load design 3.)Cruise efficiency + Insensitivity to gust - Drive High wing load design |
| What are Flying Quality design drivers? | - Stall must be symmetric, Start inboard and Not lead to large nose up pitching moment -Sufficient design margins such that the wing doesn't experience dangerous dynamic loading d to flow seperation at any point in flight envelope |
| What are Flying Quality design drivers? | -Wing insensitivity to gust -Wing contribution to aerodynamic stability derivatives should lead to flight dynamics appropriate to safe and efficient flight controls (via piolt or computer) |
| What are Stuctural Framework design drivers? | -Minimise structural mass + Meet airworthiness regulation -Framework must support wing system + Fuel + Propulsion engine + High Lift |
| What are Internal volume design drivers? | -Wing internal volume = Primary fuel storage + Inertial relief -Minimum wing size of long range aircraft may be limited by available fuel volume |
| What are the advantages of Low Wing ? | -Easier to service -Structurally simple spars can be carried through fuselage -Wing shield fuselage in the event of a crash + Act as flotation device |
| What are some disadvantages of Low wing design? | - Less aerodynamically efficient compared to High and Mid wing -Reduced ground Clearance = Higher likelihood of debris |
| What are the advantages of High Wing ? | -Higher aerodynamically efficiency -Cleaner air( Less disturbed) - Greater engine clearance : Larger engines + BPR - Lower centre of gravity = Natural stability |
| What are the disadvantages of High Wing ? | -Harder to manufacture wing + Fuselage - Harder to mantaine flaps + Wings + Engines -Reniforment of fuselage |
| What are the Disadvantages of Mid Wing ? | - Structurally worse than High + Low -Additional supports in fuselage for wings = weight |
| Aspect Ratio | AR=Span/ SMC = Span^2/Gross Area |
| Advantages of high AR ratio? | - long thinner wings = Improves L/D -More stable -Additional support and inertial relief required -Cost is increased weight -Less induced drag -Less power required to maintain speed = less fuel consumption |
| Disadvantages of high AR ratio? | - Long thinner wing -Additional support and inertial relief required -Cost is increased weight |
| Disadvantages of low AR ratio? | -More induced drag -More power required to maintain speed = fuel consumption increases |
| Advantages of Low AR ratio? | - Less stability = More manoeuvrable -More induced drag -Less L/d -Lower wing weight |
| Aspect ratio and Airworthness | - A higher aspect ratio in the event of an engine failure will meet Airworthniness requirement with greater ease than a low aspect ratio |
| Advantages Structural effects of taper vs no taper | - Wing taper shifts load distribution inboard and hence reduces wing root being moment leading to a lighter structure compared to untapered wing |
| Aerodynamic effects of taper | -Given AR,Induced Drag is minimised when the load (and hence chord distribution is elliptical For constant aerofoil section, tapered wings required more twist (washout) to maintain a uniform angle of attack along the span |
| Wing profile selection | - High speed performance: High L/D at medium CL and high M - Low Speed Performance: High Lift + Low Mach |
| Supercritical Airfoil | -Delay the onset of wave drag at transonic speed -Flattened upper surface -Highly cambered (Curved) Aft section -Greater Leading edge radius |
| Thickness to Chord Ratio Minimum Drag | -Small as possible |
| Thickness to Chord Ratio Minimum Strutural weight | - Large as posssibke |
| No taper | - Wings are square and easy to manufacture |
| Advantages of Wing sweep | - Reduces component of velocity normal to leading edge -Increases wing critical Mach number for the same thickness or -Allows greater thickness for the same critical mach number -Increases Roll sensitivity |
| Disadvantages of Wing sweep ? | -Increases Mass of the wing to offset torsional load -Reduces CL max( Flaps effectiveness depends of t.e sweep) -Reduces aileron effectiveness due to spanwise flow towards tips -Risk Tip stall -Increase Boundary layer thickness= Increase Drag |
| Dihedral angle advantages ? | -Increases engine clearance - Increases lateral stability in Yaw - Better cross wind performance |
Created by:
Studybuddy321123
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