Lift Equation - ANSWERSLift=CL((ov2)/295)S
Coefficient of Lift - ANSWERSthe ratio between dynamic pressure and lift pressure; measures efficiency of the airfoil generating lift
rectangular and elliptical wings - ANSWERSstall at root first
tapered wing - ANSWERSstalls at trailing center fir...
Coefficient of Lift - ANSWERSthe ratio between dynamic pressure and lift pressure;
measures efficiency of the airfoil generating lift
rectangular and elliptical wings - ANSWERSstall at root first
tapered wing - ANSWERSstalls at trailing center first
stagnation point - ANSWERSa point in a flow field where the local velocity of the fluid is
zero
laminar flow - ANSWERS-seperates earlier
-more pressure drag
-less viscous drag
turbulent flow - ANSWERS-seperates later
-less pressure drag
-more viscous drag
Where can you find the wing surface area? - ANSWERSPOH Section 1
Archer: 172 sq. ft.
Cl(max) - ANSWERSthe angle of attack where any increase in AOA will result in
decreased lift (stall)
Cl decreases when - ANSWERScritical angle of attack is exceeded
static pressure flows - ANSWERShigh to low
turbulent flow has - ANSWERShigh velocity throughout layer
best for stall pattern - ANSWERS"hershey bar wing"
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