Aero Exam 2 Verified Exam Questions and Answers Latest update
2026/2027
Question:
1. force and moment components are represented by what kind of letters
Answer:
capital letters
Question:
2. inertial angular velocity in body frame componetns
Answer:
p, q, r
Question:
3. what are the four control rudder, elevators, throttle, ailerons surfaces
Answer:
Question:
4. stability frame
Answer:
frame obtained by rotating the Body Frame about itsy-axis in the negative direction until the x-axis is
aligned with the project of V in the x-z plane
Question:
5. angle of attack
Answer:
frame obtained by rotating the Body Frame about itsy-axis in the negative direction until the x-axis is
aligned with the project ofV in the x-z plane
Question:
6. what is angle of the rota- angle of attack tion from F_B to F_s
Answer:
,Question:
7. lift equation
Answer:
L = .5*rho*V_a^2*S*C_l
Question:
8. drag equation
Answer:
D = 0.5*rho*V_a^2*S*C_D
Question:
9. Moment equation
Answer:
M = 1/2*rho*V_a^2*S*c*C_m
Question:
10. what is C_L a function of alpha, q, and delta_e
Answer:
Question:
11. what is C_D a function of alpha, q, delta_e
Answer:
Question:
12. what is C_M a function of alpha, q, delta_e
Answer:
Question:
13. what is C_M a function of
Answer:
, Question:
14. what is q
Answer:
inertial angular velocity about y in body coordinates
Question:
15. what is alpha_wb
Answer:
angle of attack of the wind. Angle between chord length and air relative velocity basically
Question:
16. what is C_L0
Answer:
coeflcient of lift when angle of attack is 0
Question:
17. What are the stability de- C_L_alpha, C_L, rivatives in longitudinal motion that relate to lift
Answer:
Question:
18. what is C_m_alpha
Answer:
Question:
19. what are the stability de- linearization of the L, M, D equations rivatives a product of
Answer:
Question:
20. C_M_alpha
Answer:
"pitch stiffness" change of M with your change in alpha
2026/2027
Question:
1. force and moment components are represented by what kind of letters
Answer:
capital letters
Question:
2. inertial angular velocity in body frame componetns
Answer:
p, q, r
Question:
3. what are the four control rudder, elevators, throttle, ailerons surfaces
Answer:
Question:
4. stability frame
Answer:
frame obtained by rotating the Body Frame about itsy-axis in the negative direction until the x-axis is
aligned with the project of V in the x-z plane
Question:
5. angle of attack
Answer:
frame obtained by rotating the Body Frame about itsy-axis in the negative direction until the x-axis is
aligned with the project ofV in the x-z plane
Question:
6. what is angle of the rota- angle of attack tion from F_B to F_s
Answer:
,Question:
7. lift equation
Answer:
L = .5*rho*V_a^2*S*C_l
Question:
8. drag equation
Answer:
D = 0.5*rho*V_a^2*S*C_D
Question:
9. Moment equation
Answer:
M = 1/2*rho*V_a^2*S*c*C_m
Question:
10. what is C_L a function of alpha, q, and delta_e
Answer:
Question:
11. what is C_D a function of alpha, q, delta_e
Answer:
Question:
12. what is C_M a function of alpha, q, delta_e
Answer:
Question:
13. what is C_M a function of
Answer:
, Question:
14. what is q
Answer:
inertial angular velocity about y in body coordinates
Question:
15. what is alpha_wb
Answer:
angle of attack of the wind. Angle between chord length and air relative velocity basically
Question:
16. what is C_L0
Answer:
coeflcient of lift when angle of attack is 0
Question:
17. What are the stability de- C_L_alpha, C_L, rivatives in longitudinal motion that relate to lift
Answer:
Question:
18. what is C_m_alpha
Answer:
Question:
19. what are the stability de- linearization of the L, M, D equations rivatives a product of
Answer:
Question:
20. C_M_alpha
Answer:
"pitch stiffness" change of M with your change in alpha
