MCQOPTIONS
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MCQOPTIONS
This section includes 10 Mcqs, each offering curated multiple-choice questions to sharpen your Aircraft Performance knowledge and support exam preparation. Choose a topic below to get started.
| 1. |
The expression of range and endurance is written in terms of endurance factor and relative speed function. |
| A. | True |
| B. | False |
| Answer» B. False | |
| 2. |
The calculations in turboprop aircraft are done in a continuous function. |
| A. | True |
| B. | False |
| Answer» C. | |
| 3. |
The proportions of thrust and power are independent of speed and engine output. |
| A. | True |
| B. | False |
| Answer» B. False | |
| 4. |
ESPH is the combination of thrust output and shaft power output. |
| A. | True |
| B. | False |
| Answer» B. False | |
| 5. |
What is the full form of ESHP? |
| A. | Equivalent shaft horsepower |
| B. | Equal shaft horsepower |
| C. | Engine shaft horsepower |
| D. | Endurance shaft horsepower |
| Answer» B. Equal shaft horsepower | |
| 6. |
What is the range formula for mixed power-plant? |
| A. | R=Emax\(\big[Π\frac{\eta}{C_P}+(1+Π)\frac{uV_{md}}{C_T}\big]\big\{\frac{2u^2}{u^4-1}\big\}\)lnω |
| B. | R=Emax\(\big[Π\frac{\eta}{C_P}+(1-Π)\frac{uV_{md}}{C_T}\big]\big\{\frac{2u^2}{u^4-1}\big\}\)lnω |
| C. | R=Emax\(\big[Π\frac{\eta}{C_P}+(1-Π)\frac{uV_{md}}{C_T}\big]\big\{\frac{2u^2}{u^4+1}\big\}\)lnω |
| D. | R=Emax\(\big[Π\frac{\eta}{C_P}+(1+Π)\frac{uV_{md}}{C_T}\big]\big\{\frac{2u^2}{u^4+1}\big\}\)lnω |
| Answer» D. R=Emax\(\big[Π\frac{\eta}{C_P}+(1+Π)\frac{uV_{md}}{C_T}\big]\big\{\frac{2u^2}{u^4+1}\big\}\)lnω | |
| 7. |
What is the range of the power producing engine? |
| A. | RP=\(\big[\frac{\eta}{C_P}E_{max}\big]\big\{\frac{2u^2}{u^4+1}\big\}\)lnω |
| B. | RP=\(\big[\frac{\eta}{C_P}E_{max}\big]\big\{\frac{2u^3}{u^4+1}\big\}\)lnω |
| C. | RP=\(\big[\frac{\eta}{C_P}\big]\big\{\frac{2u^2}{u^4+1}\big\}\)lnω |
| D. | RP=\(\big[\frac{V_{mdi}}{C_P}E_{max}\big]\big\{\frac{2u^3}{u^4+1}\big\}\)lnω |
| Answer» B. RP=\(\big[\frac{\eta}{C_P}E_{max}\big]\big\{\frac{2u^3}{u^4+1}\big\}\)lnω | |
| 8. |
What is the range of thrust producing engine? |
| A. | RT=\(\big[\frac{V_{mdi}}{C_T}E_{max}\big]\big\{\frac{2u^4}{u^4+1}\big\}\)lnω |
| B. | RT=\(\big[\frac{V_{mdi}}{C_T}\big]\big\{\frac{2u^3}{u^4+1}\big\}\)lnω |
| C. | RT=\(\big[\frac{V_{mdi}}{C_T}E_{max}\big]\big\{\frac{2u^3}{u^4+1}\big\}\)lnω |
| D. | RT=\(\big[\frac{V_{mdi}}{C_T}E_{max}\big]\big\{\frac{u^3}{u^4+1}\big\}\)lnω |
| Answer» D. RT=\(\big[\frac{V_{mdi}}{C_T}E_{max}\big]\big\{\frac{u^3}{u^4+1}\big\}\)lnω | |
| 9. |
The residual energy is converted into __________ |
| A. | power |
| B. | thrust |
| C. | lift |
| D. | drag |
| Answer» C. lift | |
| 10. |
What is a turboprop? |
| A. | It is a combination of turbojet and ramjet |
| B. | It is a combination of turbojet and turbofan |
| C. | It is a combination of turbojet and scramjet |
| D. | It is a combination of turbojet and propeller engine |
| Answer» E. | |