MCQOPTIONS
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MCQOPTIONS
This section includes 6 Mcqs, each offering curated multiple-choice questions to sharpen your Aerodynamics Questions and Answers knowledge and support exam preparation. Choose a topic below to get started.
| 1. |
Select the flow which is not laminar all over the thin airfoil at α=0°. |
| A. | The given values are for Rec. |
| B. | 7×105 |
| C. | 9×104 |
| D. | 2×103 |
| E. | We can’t say with just this information |
| Answer» B. 7×105 | |
| 2. |
The total skin-friction drag coefficient for laminar flow with Reynolds number at the trailing edge being Rec=40000 and chord length is 1m, is _____ |
| A. | 0.01328 |
| B. | 0.00664 |
| C. | 0.02656 |
| D. | 0.664 |
| Answer» B. 0.00664 | |
| 3. |
The constant which is present while establishing a relationship for Cf and Rec for a laminar flow is_____ |
| A. | 2.65 |
| B. | 0.664 |
| C. | π |
| D. | 1.33 |
| Answer» E. | |
| 4. |
The coefficient of skin-friction drag coefficient Cf, as conventionally defined, when used gives half the value of total drag. |
| A. | True |
| B. | False |
| Answer» B. False | |
| 5. |
The boundary layer thickness for an incompressible, laminar flow at a distance x with Reynolds number Rex is δ. Which is____ |
| A. | Directly proportional to √x |
| B. | Inversely proportional to x |
| C. | Directly proportional to Rex |
| D. | Inversely proportional to Rex2 |
| Answer» B. Inversely proportional to x | |
| 6. |
For a Reynolds number Rec=9×104 and chord length 1m, what is the laminar boundary layer thickness at the trailing edge (in cm)? |
| A. | 2.34 |
| B. | 3 |
| C. | 1.5 |
| D. | 1.67 |
| Answer» E. | |