Vayudoot Aviation

1. M 0.80, OAT - 50°C, FL 330, GS 490 kt, VAR 20°W, Magnetic heading 140°, drift is 11° right. Calculate the true W/V?

025°/90 kts.

020°/95 kts.

020°/80 kts.

2. A/C is flying at TAS = 520 Kts. SAT is - 20°C. Find TAT.

- [TAT = SAT+ [TAS/87.1]2 = -20°C+[520/87.1]2 = 15.64°C.]

- [TAT = SAT+ [TAS/87.1]2 = -20°C+[520/87.1]2 = 15.63°C.]

3. FL120, OAT is ISA standard, CAS is 200 kt, Track is 222°(M), Heading is 215°(M), Variation is 15°W. time to fly 105 NM is 21 MIN. what is the W/V?

050°(T) / 75 kt.

050°(T) / 70 kt.

050°(T) / 50 kt.

4. An aircraft is flying at mach 0.86 and the true ambient air temperature is - 42°C. Determine

- [LSS = 39 × √ - 42 + 273 = 39 ×√231 = 593 KTS (B) 0.86 = TAS/593 TAS = 593 × 0.86 = 510 KTS.]

- [LSS = 39 × √ - 42 + 273 = 39 ×√231 = 593 KTS (B) 0.86 = TAS/593 TAS = 593 × 0.86 = 513 KTS.]

5. An increase of 0.15 Mach results in an increase of 93 kt TAS of an aircraft. The local speed of sound is

560 kt

620 kt

580 kt

6. A/C is flying at TAS = 400 Kts. SAT = -23°. Find Dynamic rise in temperature

- [DYNAMIC RISE = [TAS/87.1]2 = [400/87.1]2 = 21.09°C.]

- [DYNAMIC RISE = [TAS/87.1]2 = [400/87.1]2 = 22.09°C.]

7. An Air Data Computer (ADC)

transforms air data measurements into electric impulses driving servo motors in instruments

is an auxiliary system that provides altitude information in the event that the static source is blocked

measures position error in the static system and transmits this information to ATC to provide correct altitude reporting

8. IAS 120 kt, FL 80, OAT + 20°C. What is the TAS?

135 kts.

141 kts.

144 kts.

9. If the outside temperature at 35000ft is -40°C , the local speed of sound is

307kt

596kt

686kt

10. If pressure altitude is 40,000 ft. amsl, indicated TAT is -29°C what is the mach number assuming ISA conditions?

0.7.

0.75.

0.8.

11. Mach number is the ratio of?

TAS:LSS.

IAS:TAS.

CAS:LSS.

12. The difference between static air temperature and total air temperature is known as

the ram rise

hot ramp radiation

corrected outside are temperature

13. When descending through an isothermal layer at a constant Calibrated Airspeed (CAS), the True Airspeed (TAS) will?

Remain constant.

Increase at an exponential rate.

Decrease

14. When climbing through an isothermal layer at constant TAS?

Mach number increases.

Mach number decreases.

Mach number remains constant.

15. When descending through an inversion at constant mach number?

CAS decreases.

TAS increases.

TAS decreases.

16. Cruising at FL 390, M.84 is found to give a TAS of 499kt. The ISA deviation at this level will be

+17.

+19.

-19.

17. When descending through an isothermal layer at constant TAS?

Mach number remains constant.

Mach number decreases.

Mach number increases.

18. If a Decrease of 0.12 in the Mach number results in a decrease of 80 Knots in the TAS, what is the local speed of sound?

- [MACH NUMBER = TAS/LSS ; LSS = 80/12 = 667 KTS.]

- [MACH NUMBER = TAS/LSS ; LSS = 80/12 = 669 KTS.]

19. If mach number is 0.88 and TAT is -4°C, what is the pressure altitude in the international standard atmosphere?

22000 ft.

26000 ft.

28000 ft.

20. If pressure altitude is 30000 ft., indicated TAT is -10°C, mach number is 0.82, what is the density altitude?

31000 ft.

30472 ft.

30674 ft.

21. In An Air Data Computer (ADC), aero plane altitude is calculated from

Measurement of absolute barometric pressure from a static source on the fuselage

Measurement of outside air temperature (OAT)

The difference between absolute and dynamic pressure at the fuselage

22. When climbing through an inversion at constant CAS?

TAS increases.

Mach number decreases.

TAS remains constant.

23. At a fixed pressure altitude an increase in temperature will?

Decrease density but increase density altitude.

Not affect density altitude.

Increase density but decrease density altitude.

24. Calibrated air speed is

IAS plus the pressure error

IAS plus instrument error correction

IAS plus density error correction

25. A temperature sensor having a recovery factor of 0.75 indicates 30°C. Static Air Temperature (SAT) is 25°C. How high is the Ram-rise?

6.7°C.

5°C.

18.8°C

26. When climbing at a constant Mach number below the tropopause, in ISA conditions =, the Calibrated Airspeed (CAS) will

increase at a linear rate

increase at an exponential rate

decrease

27. When descending through an inversion at constant CAS?

TAS decreases.

Mach number remains constant.

Mach number increases.

28. As pressure altitude increases when climbing at constant mach number?

CAS will decrease then remain constant.

TAS will increase.

TAS will decrease then remain constant.

29. EAS is?

IAS corrected for adiabatic compression.

CAS corrected for adiabatic compression.

IAS corrected for pressure sensing errors.

30. The Airspeed Indicator measures

Differential pressure changes

Differential pressure

Static pressure changes.

31. When descending through an inversion at constant CAS?

TAS decreases.

TAS increases.

Mach number increases.

32. For a constant Calibrated Airspeed (CAS) and a level flight, a fall in ambient temperature will result in a

higher True Air Speed (TAS) due to an increase in air density

higher True Air Speed (TAS) due to an decrease in air density

lower True Air Speed (TAS) due to an increase in air density

33. When descending through an isothermal layer at a constant Calibrated Airspeed (CAS), the True Airspeed (TAS) will

increase at an exponential rate

increase at a linear rate

decrease

34. CAS is IAS corrected for

instrument error.

position error.

density error.

35. M: Mach number Ts: static temperature Tt: total temperature Which of the following statements is correct?

Ts = Tt / (1+0.2M2)

Ts = Tt × (1+9.2M2)

Ts = Tt × (0.2M2)

36. FL250,OAT -15°C, TAS 250 kt, Calculate the Mach No.?

0.40.

0.38.

0.45.

37. TAT = -25°. SAT = -35°. Find TAS.

- [-25° = -35°[TAS/87.1]2 ; + √10 = [TAS/87.1] ; TAS = 275.4 KTS.]

- [-25° = -35°[TAS/87.1]2 ; + √10 = [TAS/87.1] ; TAS = 273.4 KTS.]

38. Total Air Temp is always... than Static Air Temp and the difference varies with....

colder, CAS.

warmer, TAS.

warmer, altitude.

39. When descending through an isothermal level the TAS will _____, the CAS and the LSS will ________ :

Increase, increase, decrease

remain constant, decrease, increase

remain constant, increase, remain constant

40. EAS is

IAS corrected for compressibility

CAS corrected for position error

CAS corrected for compressibility

41. FL 350, Mach 0.80, OAT - 55°C. Calculate the values for TAS and local speed of sound (LSS)?

465 kt, LSS 575 kt.

460 kt, LSS 575 kt.

460 kt, LSS 567 kt.

42. As pressure altitude increases

Temperature increases then remains constant.

Temperature decreases.

Temperature decreases then remains constant.

43. If pressure altitude is 30000 ft amsl and mach number is 0.84 what is the ISA TAT?

10°C

-12°C.

-10°C.

44. At a constant Mach number, the calibrated airspeed (CAS)

remains unchanged when the outside temperature increases

decreases when the altitude increases

increases when the altitude increases

45. As pressure altitude increases when climbing at constant IAS?

TAS will increase.

CAS will increase.

CAS will decrease.

46. The velocity of sound at the sea level in a standard atmosphere is

661kt

1059kt

644kt

47. An is aircraft flying at a TAS of 1100 knots at FL650. A change in 0.1M causes a change i TAS of 57 knots. The temperature deviation at FL 650 assuming an ISA atmosphere is

-5

-2.5

+5

48. If indicated TAT is - 10°C, pressured altitude is 30000 ft. amsl, and mach number is 0.84, what is the temperature deviation?

2°C.

4°C.

-4°C.

49. TAS = 485 kt, OAT = ISA + 10°C, FL 410. Calculate the Mach number?

0.833.

0.825.

0.852.

50. Total air temp is _____ than _____ by an amount which is proportional to _____.

Higher, SAT, TAS

Higher, SAT, LSS

Higher, SAT, CAS

Question Bank

Questions for DETERMINATION OF TEMP