Related InterviewSolutions

• 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
• Which of the following is correct?(a) Aircraft which is statically stable may or may not be dynamically stable(b) Lift is equal to weight always(c) Thrust is only proportional to nose of aircraft(d) Drag is useful during takeoffThe question was posed to me in an online quiz.I would like to ask this question from Dynamic Stability in section Stability, Control, and Handling Qualities of Aircraft Design
• Thrust will affect the stability of the aircraft.(a) True(b) FalseI got this question during an interview.This intriguing question comes from Longitudinal Static Stability and Control-2 in chapter Stability, Control, and Handling Qualities of Aircraft Design
• Rolling moment will influence _______(a) aircraft lateral stability(b) longitudinal stability(c) pitch axis stability(d) pitching stability onlyThis question was addressed to me in an online interview.My question comes from Lateral-Directional Static Stability and Control in chapter Stability, Control, and Handling Qualities of Aircraft Design
• Stick fixed and stick free are similar.(a) True(b) FalseThe question was asked in an internship interview.My doubt stems from Stick-Free Stability topic in chapter Stability, Control, and Handling Qualities of Aircraft Design
• Following diagram represents ________(a) typical wind axis system(b) drag polar(c) lift curve slope(d) thrust required curveThis question was addressed to me during an online exam.My enquiry is from Longitudinal Static Stability and Control-1 in chapter Stability, Control, and Handling Qualities of Aircraft Design
• For pitching moment coefficient diagram shown below which one will have positive trim AOA?(a) Aircraft 1(b) Aircraft 2(c) Aircraft 3(d) Aircraft 3 and Curve 2 bothThe question was posed to me in an online quiz.This interesting question is from Longitudinal Static Stability and Control-1 topic in division Stability, Control, and Handling Qualities of Aircraft Design
• Elevator control power is given by _____(a) \(\frac{dCm}{d\delta e}\)(b) Zero lift drag(c) T = CD0 + K*CL(d) DCL/ɑI had been asked this question at a job interview.My query is from Longitudinal Static Stability and Control-2 topic in section Stability, Control, and Handling Qualities of Aircraft Design
• Aircraft is said to be statically stable if __________(a) it has initial tendency to come back to its original equilibrium condition after being disturbed(b) it has tendency to return to equilibrium state with the help of pilot’s input(c) it has more lift than weight always(d) it has more thrust than dragI have been asked this question in semester exam.This intriguing question comes from Longitudinal Static Stability and Control-1 topic in division Stability, Control, and Handling Qualities of Aircraft Design
• Find the appropriate value of pitching moment coefficient derivative if lift curve slope is 0.032 per degree and Xcg is 0.3. Consider neutral point is located at 60 % of chord from leading edge.(a) -0.0096 per degree(b) -7 per degree(c) 2.56 per degree(d) 0.1I had been asked this question by my college director while I was bunking the class.Question is taken from Longitudinal Static Stability and Control-2 topic in chapter Stability, Control, and Handling Qualities of Aircraft Design