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Aircraft Force Systems and the Equations of Motion Practice Test

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Aircraft Force Systems and the Equations of Motion topics are: Motion equations, aircraft force systems, lift and drag forces, minimum drag and power speed, aerodynamic relationships, thrust and power producing power plants. The forces acting on the vehicles, such as lift, drag, thrust, and weight, are considered to ensure proper flight characteristics, stability, and control. The aircraft's acceleration is equal to the difference between its current acceleration and the control input The flying qualities of an aircraft must be described analytically as motions of the aircraft's eg as... Show more

Aircraft Force Systems and the Equations of Motion topics are: Motion equations, aircraft force systems, lift and drag forces, minimum drag and power speed, aerodynamic relationships, thrust and power producing power plants.

The forces acting on the vehicles, such as lift, drag, thrust, and weight, are considered to ensure proper flight characteristics, stability, and control.

The aircraft's acceleration is equal to the difference between its current acceleration and the control input

The flying qualities of an aircraft must be described analytically as motions of the aircraft's eg as well as motions of the airframe about the eg. Both of these are caused by aerodynamic, thrust, and other forces and moments.

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Aircraft Force Systems and the Equations of Motion Practice Test

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1. At steady state flight condition

T<DT≠DT>DT=D

2. Gravitational force is the product of mass of the aircraft and its acceleration.

Don't KnowTrueMaybeFalse

3. Which of the following is the correct equation for net thrust?

FN=(Vj-V)FN=ṁ(V-Vj)FN=ṁ(Vj-V)FN=ṁ(Vj+V)

4. The range of R_e in the typical flight is ___________

106 to 109106 to 1010105 to 109106 to 108

5. In transonic region the mach number affects the aerodynamic characteristics.

MaybeDon't KnowTrueFalse

6. The zero-lift drag force will decrease with decrease respect to altitude.

TrueDon't KnowMaybeFalse

7. What is the theoretical value of lift curve slope of a flat airfoil?

π per radian4aπ per radian2π per radian3π per radian

8. The lift-dependent drag is reduced with the reduction in total drag.

MaybeFalseDon't KnowTrue

9. What is overall drag force?

The sum of drag force, lift-dependent drag and volume dependent wave dragThe sum of lift-dependent drag and volume dependent wave dragThe sum of drag force, zero-lift drag and lift-dependent dragThe sum of drag force, zero-lift drag, lift-dependent drag and volume dependent wave drag

10. Which of the following equation is correct?

P\(\sqrt{\sigma}\)=YVe3+\(\frac{ZW^2}{V_e}\) VemP=\(\sqrt[3]{\frac{ZW^2}{3Y}}\) P\(\sqrt{\sigma}\)=YVe2+\(\frac{ZW^2}{V_e}\) VemP=\(\sqrt[4]{\frac{ZW}{3Y}}\)

11. The aerodynamic forces arise from the relative motion between the aircraft and the air mass in which it is flying.

MaybeTrueFalseDon't Know

12. Leading edge flap deflection has the effect of increasing lift curve to a higher stalling angle of attack.

MaybeDon't KnowFalseTrue

13. Which of the following represents the correct formula for propeller efficiency?

η=\(\frac{P}{TV}\) η=\(\frac{TV}{P}\) η=\(\frac{T}{P}\) η=\(\frac{T}{PV}\)

14. Which of the following are the forces that are concerned with the performance of an aircraft?

Lift, dragLift, drag, weightLift, drag, weight, side forceLift, drag, side force

15. Which of the following relations are correct for pressure coefficient?

CP=\(\frac{TV}{\frac{\rho n^3D^5}{2}}\) CP=\(\frac{P}{\frac{\rho n^2D^5}{2}}\) CP=\(\frac{P}{\frac{\rho n^3D^4}{2}}\) CP=\(\frac{P}{\frac{\rho n^3D^5}{2}}\)

16. Drag power of an aircraft is achieved by multiplying drag force with true airspeed.

MaybeTrueDon't KnowFalse

17. The forms of powerplant used in aircraft propulsion are ___________

thrust-producing and weight producingweight-producing and power producingthrust-producing, power producing and weight producingthrust-producing and power producing

18. There are three types of drag.

Don't KnowMaybeFalseTrue

19. Which of the following is the correct formula for reynolds number?

Re=\(\frac{\rho Vl}{\mu}\) Re=\(\frac{PVl}{\mu}\) Re=\(\frac{\rho \mu l}{V}\) Re=\(\frac{\rho Vl}{P}\)

20. What is the relation between true air speed and equivalent air speed?

VT=\(\frac{V_e}{4\sqrt{\sigma}}\) VT=\(\frac{V_e}{\sqrt{\sigma}}\) VT=\(\frac{V_e}{3\sqrt{\sigma}}\) Ve=\(\frac{V_T}{\sqrt{\sigma}}\)

21. What kind of forces is responsible for airframe drag?

Forces resulting from discontinuous flowForces resulting from external flowForces resulting from continuous flowForces resulting from internal flow

22. Which of the following is the correct performance equation?

\(\big[\frac{\lambda}{u}+τ\big]+\frac{1}{2}\big[u^2+\frac{1}{u^2}\big]\)=Emax\(\big\{sin\gamma_2+\frac{V}{g}\big\}\) \(\big[\frac{\lambda}{u}+τ\big]-\frac{1}{2}\big[u^2+\frac{1}{u^2}\big]\)=Emax\(\big\{sin\gamma_2+\frac{V}{g}\big\}\) \(\big[\frac{\lambda}{u}+τ\big]+\frac{1}{2}\big[u^2+\frac{1}{u^2}\big]\)=Emax\(\big\{sin\gamma_2-\frac{V}{g}\big\}\) \(\big[\frac{\lambda}{u}+τ\big]-\frac{1}{2}\big[u^2+\frac{1}{u^2}\big]\)=Emax\(\big\{sin\gamma_2-\frac{V}{g}\big\}\)

23. The velocity of the engine exhaust flow is a function of the temperature of the exhaust gas.

FalseMaybeDon't KnowTrue

24. What is meant by stalling angle of attack?

The angle at which we get maximum liftThe angle at which we get minimum dragThe angle at which we get maximum dragThe angle at which we get minimum lift

25. The minimum drag speed is given by ___________

\(\big(\frac{2W}{\rho S}\big)^{\frac{1}{2}}\big(\frac{K}{C_{Dz}}\big)^\frac{1}{4}\) \(\big(\frac{2W}{\gamma \rho S}\big)^{\frac{1}{2}}\big(\frac{K}{C_{Dz}}\big)^\frac{1}{4}\) \(\big(\frac{2W}{\gamma \rho S}\big)^{\frac{1}{2}}\big(\frac{K}{C_{Dz}}\big)^\frac{1}{2}\) \(\big(\frac{2W}{\rho S}\big)^{\frac{1}{2}}\big(\frac{K}{C_{Dz}}\big)^\frac{1}{2}\)

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