Question

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?

(a) 2.4°

(b) 4.5°

(c) 6.7°

(d) 1.23°

This question was addressed to me in unit test.

This question is from Longitudinal Static Stability and Control-2 topic in section Stability, Control, and Handling Qualities of Aircraft Design

Answer 1

Correct answer is (a) 2.4°

For explanation: Tail AOA = wing AOA – downwash angle = 5°-2.6° = 2.4°.