MCQOPTIONS
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MCQOPTIONS
This section includes 9 Mcqs, each offering curated multiple-choice questions to sharpen your Aerodynamics knowledge and support exam preparation. Choose a topic below to get started.
| 1. |
What is the source of wave drag exerted on the supersonic airfoil? |
| A. | Shock waves |
| B. | Skin friction |
| C. | Viscous boundary layer |
| D. | Trailing vortex |
| Answer» B. Skin friction | |
| 2. |
What happens to the coefficient of pressure in a supersonic flow for an increase in Mach number? |
| A. | Increases |
| B. | Decreases |
| C. | Remains unaffected |
| D. | First increases then decreases |
| Answer» C. Remains unaffected | |
| 3. |
For supersonic flow, which differential equation is obtained for the linearized perturbation potential equation? |
| A. | Elliptic partial differential equation |
| B. | Hyperbolic differential equation |
| C. | Parabolic differential equation |
| D. | Linear differential equation |
| Answer» C. Parabolic differential equation | |
| 4. |
What is the lift coefficient over a flat plate at an angle of attack of 3 degrees in a supersonic flow at Mach 4? |
| A. | 0.0512 |
| B. | 0.0541 |
| C. | 0.0628 |
| D. | 0.0714 |
| Answer» C. 0.0628 | |
| 5. |
Wave drag coefficient as derived from linearized theory is independent of the airfoil shape and thickness. |
| A. | True |
| B. | False |
| Answer» C. | |
| 6. |
According to lineralized theory, what is the formula for coefficient of lift over the a flat plate in a supersonic flow? |
| A. | cl=\(\frac {4α}{\sqrt {M_∞^2-1}}\) |
| B. | cl=\(\frac {4α^2}{\sqrt {M_∞^2-1}}\) |
| C. | cl=\(\frac {4α}{\sqrt {M_∞^2+1}}\) |
| D. | cl=\(\frac {4α^2}{\sqrt {M_∞^2+1}}\) |
| Answer» B. cl=\(\frac {4α^2}{\sqrt {M_∞^2-1}}\) | |
| 7. |
The Cp value for supersonic airfoil surface which is inclined away from the freestream is positive. |
| A. | True |
| B. | False |
| Answer» B. False | |
| 8. |
What is the value of Cp at the forward surface in a biconvex airfoil? |
| A. | Zero |
| B. | Positive |
| C. | Negative |
| D. | Infinite |
| Answer» C. Negative | |
| 9. |
Which of these equations is used for computing the lift and wave drag over a supersonic airfoil? |
| A. | Cp=\(\frac {2θ}{\sqrt {M_∞^2-1}}\) |
| B. | Cp=\(\frac {2θ}{\sqrt {M_∞^2+1}}\) |
| C. | Cp=\(\frac {\sqrt {M_∞^2-1}}{θ}\) |
| D. | Cp=\(\frac {\sqrt {M_∞^2+1}}{θ}\) |
| Answer» B. Cp=\(\frac {2θ}{\sqrt {M_∞^2+1}}\) | |