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Aerodynamics Practice Test: Subsonic Compressible Flow over Airfoils - Linear Theory, Linearized Supersonic Flow
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Avg score: 74% • Most missed: “What is the source of wave drag exerted on the supersonic airfoil?”
This quiz covers: Prandtl glauert compressibility, supercritical airfoil and supersonic airfoils application. Subsonic compressible flow over airfoils is an inviscid, compressible, and irrotational flow. This means that there is no mechanism to rotate the fluid elements.  Potential flow solutions in two and three dimensions can provide accurate results for aerofoil and wing analysis if the flow Mach number is less than 0.4. In this low subsonic region, the flow is incompressible so that no density variations need to be considered in the governing equations.  Compressibility strengthens the... Show more
Aerodynamics Practice Test: Subsonic Compressible Flow over Airfoils - Linear Theory, Linearized Supersonic Flow
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23 Questions

1. Prandtl – Glauert compressibility correction is based on which of the following methods?
2. If the lift coefficient for an aircraft at low speed is 0.45, then what is the value of the coefficient of drag at Mach number 0.7?
3. What is the source of wave drag exerted on the supersonic airfoil?
4. Supercritical wings are characterized as high-lifting wings.
5. What is the value of Cp at the forward surface in a biconvex airfoil?
6. High speed subsonic aircrafts are designed with thick airfoil wings.
7. How is supercritical airfoil different from the NACA 64 series airfoil?
8. For which of thee flows is Prandtl – Glauert compressibility correction is effective?
9. What is the source of wave drag exerted on the supersonic airfoil?
10. Wave drag coefficient as derived from linearized theory is independent of the airfoil shape and thickness.
11. What is the lift coefficient over a flat plate at an angle of attack of 3 degrees in a supersonic flow at Mach 4?
12. According to lineralized theory, what is the formula for coefficient of lift over the a flat plate in a supersonic flow?
13. For supersonic flow, which differential equation is obtained for the linearized perturbation potential equation?
14. The Cp value for supersonic airfoil surface which is inclined away from the freestream is positive.
15. For which of these conditions is Prandtl – Glauert compressibility equation valid?
16. What is the value of Cp at the forward surface in a biconvex airfoil?
17. What is the lift coefficient over a flat plate at an angle of attack of 3 degrees in a supersonic flow at Mach 4?
18. High speed subsonic aircrafts are designed with thick airfoil wings.
19. Wave drag coefficient as derived from linearized theory is independent of the airfoil shape and thickness.
20. What happens to the coefficient of pressure in a supersonic flow for an increase in Mach number?
21. According to lineralized theory, what is the formula for coefficient of lift over the a flat plate in a supersonic flow?
22. What is a critical Mach number?
23. Prandtl – Glauert compressibility correction is applied for finding airfoil properties at low speed.

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