Vayudoot Aviation

1. The machmeter gives an indication of mach number by measuring the ratio:

dynamic pressure / pitot pressure

static pressure / dynamic pressure

pitot pressure / static pressure

dynamic pressure/ static pressure

2. The relationships between TAS, mach number (MNo) and local speed of sound (LSS) is

LSS = MNo / TAS

MNo = LSS x TAS

TAS = MNo x LSS

MNo = LSS / TAS

3. When descending below the tropopause under normal conditions (increasing temperature) at a constant CAS:

the TAS will increase and the mach number will decrease.

the TAS will decrease and the mach number will increase.

both TAS and mach number will increase.

both TAS and mach number will decrease.

4. The errors to which the machmeter is subject are

instrument error, position error, density error and manoeuvre induced error.

instrument error, position error, barometric error, temperature error and manoeuvre induced error.

instrument error, position error, compressibility error and manoeuvre induced error.

instrument error, position error and manoeuvre induced error.

5. An aircraft is flying at FL350 with a JSA deviation of +8. The mach no is 0.83 and the TAS 485. If the aircraft descends to FL300 and maintains the same mach no and TAS, the JSA deviation will now be

-2

+2

+8

-18

6. When climbing at a constant mach number below the tropopause through an inversion

the CAS will decrease and the TAS will increase.

the CAS and TAS will both increase.

the CAS and TAS will both decrease.

the CAS will increase and the TAS will decrease.

7. At FL 350 with a JSA deviation of -12, the true airspeed when flying at M 0.78 is

490 kt

460 kt

436 kt

447 kt

8. The local speed of sound is equal to: (K = Constant)

K √ temperature (°K) knots

K √ temperature (°K) metres per second

K √ temperature (°F) knots

K √ temperature (°C. knots

9. Cruising at FL390, M 0.84 is found to give a TAS of 499 kt. The ISA deviation at this level will be:

-17

+19

+17

-19

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