AQT Aviation Mathematics & Calculations 3

Question 1

Using the formula WCA ≈ (wind speed ÷ TAS) × sin(wind angle) × 60, if wind is 20 knots, TAS is 120 knots, and the wind angle is 90°, what is the wind correction angle?

Accepted Answer

10°

Answer

5°

Answer

7°

Answer

12°

Question 2

An aircraft weighs 4,000 lbs and enters a 60° bank level turn where the load factor is 2.0. What is the effective structural load on the aircraft?

Accepted Answer

8,000 lbs

Answer

4,000 lbs

Answer

6,000 lbs

Answer

10,000 lbs

Question 3

A glider has a best glide ratio of 20:1. At 6,000 ft AGL (using 6,000 ft ≈ 1 nm), what is the maximum glide distance?

Accepted Answer

20 nm

Answer

15 nm

Answer

25 nm

Answer

30 nm

Question 4

Pressure altitude is 4,000 ft with an ISA temperature deviation of +20°C. Using 120 ft per degree of deviation, what is the density altitude?

Accepted Answer

6,400 ft

Answer

4,000 ft

Answer

5,200 ft

Answer

7,600 ft

Question 5

An aircraft flies at 150 knots TAS heading 090°. Wind is from 180° at 30 knots (a pure crosswind). What is the approximate groundspeed?

Accepted Answer

153 knots

Answer

120 knots

Answer

150 knots

Answer

165 knots

Question 6

An aircraft requires 2,400 ft of runway at sea level. At density altitude 5,000 ft, the correction factor is 1.4. What is the new required takeoff distance?

Accepted Answer

3,360 ft

Answer

2,800 ft

Answer

3,200 ft

Answer

3,600 ft

Question 7

An aircraft has a total moment of 264,000 in-lbs and a CG located 88 inches aft of the datum. What is the total weight of the aircraft?

Accepted Answer

3,000 lbs

Answer

2,500 lbs

Answer

2,800 lbs

Answer

3,200 lbs