Avit 323 Block 9 Lift Equation DD Exam
100% Correct
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
What does not change the coefficient of lift? - ANSWERSweight, CG, aircraft pitch
attitude (AOA) or aircraft weight
Where can you find the wing surface area? - ANSWERSPOH Section 1
Archer: 172 sq. ft.
desire to keep lateral control through stall - ANSWERStip stalls last and root stalls first
washout - ANSWERSthe tip section has a negative twist, leading edge points down
stall strips - ANSWERScauses flow to seperate below critial angle of attack
best for stall pattern - ANSWERS"hershey bar wing"
rectangular and elliptical wings - ANSWERSstall at root first
tapered wing - ANSWERSstalls at trailing center first
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 hight to low is a - ANSWERSfavorable gradient
static pressure flows low to high is a - ANSWERSadverse gradient
turbulent flow has - ANSWERShigh velocity throughout layer
stagnation point - ANSWERSa point in a flow field where the local velocity of the fluid is
zero
laminar flow - ANSWERS-flow separates earlier
-more pressure drag
-less viscous drag
100% Correct
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
What does not change the coefficient of lift? - ANSWERSweight, CG, aircraft pitch
attitude (AOA) or aircraft weight
Where can you find the wing surface area? - ANSWERSPOH Section 1
Archer: 172 sq. ft.
desire to keep lateral control through stall - ANSWERStip stalls last and root stalls first
washout - ANSWERSthe tip section has a negative twist, leading edge points down
stall strips - ANSWERScauses flow to seperate below critial angle of attack
best for stall pattern - ANSWERS"hershey bar wing"
rectangular and elliptical wings - ANSWERSstall at root first
tapered wing - ANSWERSstalls at trailing center first
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 hight to low is a - ANSWERSfavorable gradient
static pressure flows low to high is a - ANSWERSadverse gradient
turbulent flow has - ANSWERShigh velocity throughout layer
stagnation point - ANSWERSa point in a flow field where the local velocity of the fluid is
zero
laminar flow - ANSWERS-flow separates earlier
-more pressure drag
-less viscous drag
