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Aerodynamics Practice Test: Linearized and Conical Flows
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Linearized and Conical Flows topics include: Linearized velocity potential equation, linearized pressure coefficient, linearized subsonic and supersonic flow, critical mach number, conical and supersonic flow physical aspects, quantitative formulation, improved compressibility corrections and historical note. Supersonic linearized conical-flow theory is used to determine the flow over slender pointed cones. The linearized method can have wide application to any form of boundary conditions for conical flow.  Conical flow is a flow where physical characteristics like velocity and pressure are... Show more
Aerodynamics Practice Test: Linearized and Conical Flows
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25 Questions

1. What is the coefficient of lift according to the linearized theory over a flat plate kept at an inclination of 3 degrees having a freestream Mach number of 2?
2. What happens to the flow around the airfoil at upper critical Mach number?
3. The flow stream behind the shock in a conical flow is parallel to the conical surface.
4. Under which condition do we get the detached shock wave on a cone?
5. What is the cause of truncation error in numerical solution?
6. Conical flow is rotational according to the result obtained from Crocco’s theorem.
7. Which of these is the linearized perturbation velocity potential equation over a thin airfoil in a subsonic compressible flow?
8. The numerical solution results in certain amount of truncation error.
9. Which of these is not the assumption for Taylor – Maccoll conical flow?
10. Which of these is the compatibility equation along C characteristic line?
11. What is the velocity potential for a slender body in uniform flow with perturbations?
12. For a wedge and cone of same half angle, the shock wave formed at the cone is weaker.
13. What happens to the velocity downstream of the shock as the deflection angle increases?
14. Method of characteristics is applicable for which of these flows?
15. What is the coefficient of pressure at minimum pressure point a function of?
16. Which of these assumptions are not made while obtaining the linearized perturbation velocity potential equation?
17. The local Mach number at a point on the airfoil reaches 1 for critical Mach number.
18. What is the relation between maximum allowed cone angle and wedge angle for attached shock wave?
19. What is the application of studying conical flow?
20. Which of these methods is employed to find solution using method of characteristics?
21. Up to which Mach number is Prandtl – Glauert rule applicable for subsonic flow?
22. What is the irrotationally condition for a conical flow?
23. What happens to the shock wave when the cone angle is less than the maximum cone angle?
24. Which equation is satisfied when the Mach number approaches to zero in linearized velocity potential equation?
25. In which equation is total velocity and it double derivative substituted to obtain the perturbation velocity potential equation?