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An aircraft wing is experiencing AOA of 5°. If downwash due to wing is 2.6° then, how much angle is being seen by tail of the aircraft?

Correct Answer: 2.4°
Tail AOA = wing AOA – downwash angle = 5°-2.6° = 2.4°.

An aircraft with wing aft tail configuration has tail efficiency of 0.95 and tail volume ratio of horizontal tail is 0.7. Determine pitching moment coefficient slope for the tail. Given lift curve slope of tail is 4.2 per rad. Consider downwash derivative as 0.6.

A typical jet transport aircraft needs to be sized based on following parameters. Wing area S=50m2, MAC=5m. If tail volume coefficient of horizontal tail is 1 and tail area is 10m2 then, find the required tail moment arm.

An aircraft experiences sideslip of 4° and side wash at vertical tail is 1.2°. What will be the AOA at vertical tail?

If Cvt = 0.05 then, find the vertical tail area. Given wing span b is 2m, wing area S=10m2 and tail moment arm Lvt=1m.

A NACA 22104 airfoil is operating at AOA = 3°. The lift-coefficient at this AOA is 0.15. Determine the value of angle of attack at designed lift co-efficient.

If an airfoil has lift of 200 N at 10° AOA, then what is induced drag produced by airfoil at that AOA?

An aircraft with elliptic wing planform has parasite drag coefficient as 0.6. Lift coefficient of wing is 0.25 and aspect ratio is 7.5. If induced drag co-efficient is 0.0235 then, find total drag coefficient for the wing.

An airfoil with symmetric profile has pitching moment about aerodynamic centre as 13 Nm at 4° AOA. Determine Pitching moment at same point if AOA is increased by 8°.

A wing alone aircraft has aerodynamic centre pitching moment coefficient of -0.126. If lift coefficient at zero AOA is 0.38 then, find Cm0. Consider Xcg=0.3.

An aircraft with elliptic wing planform has parasite drag coefficient as 0.9. Lift coefficient of wing is 1.8 and aspect ratio is 8.5. Find total drag coefficient for the wing.