This set of Aircraft Performance Quiz focuses on “Cruise Method 1 – 2”.

1. Relative airspeed acts as a shaping factor.

a) True

b) False

View Answer

Explanation: Relative airspeed acts as a shaping factor. Relative airspeed is given by \(\Big\{\frac{2u^3}{u^4+1}\Big\}\) where u is relative airspeed. The range equation in cruise method 1 is given by R

_{1}=\(\Big[\frac{V_{mdi}}{C}E_{max}\Big]\Big\{\frac{2u^3}{u^4+1}\Big\}\)l

_{n}ω where V is true airspeed, C is specific fuel consumption, L is lift, D is drag, E

_{max}is endurance, u is relative airspeed and ω is fuel ratio.

2. Which of the following represents range function?

a) \(\Big[\frac{V_{mdi}}{C}E_{max}\Big]\)l_{n}ω

b) \(\Big[\frac{V_{max}}{C}E_{max}\Big]\)l_{n}ω

c) \(\Big\{\frac{2u^3}{u^4+1}\Big\}\)l_{n}ω

d) \(\Big\{\frac{2u^4}{u^4+1}\Big\}\)l_{n}ω

View Answer

Explanation: The range function is given by \(\Big\{\frac{2u^3}{u^4+1}\Big\}\)l

_{n}ω. The range equation in cruise method 1 is given by R

_{1}=\(\Big[\frac{V_{mdi}}{C}E_{max}\Big]\Big\{\frac{2u^3}{u^4+1}\Big\}\)l

_{n}ω where V is true airspeed, C is specific fuel consumption, L is lift, D is drag, E

_{max}is endurance, u is relative airspeed and ω is fuel ratio.

3. Minimum range is given when the aircraft is fly’s at u=1.316.

a) True

b) False

View Answer

Explanation: Maximum range is given when the aircraft is fly’s at u=1.316. The range equation in cruise method 1 is given by R

_{1}=\(\Big[\frac{V_{mdi}}{C}E_{max}\Big]\Big\{\frac{2u^3}{u^4+1}\Big\}\)l

_{n}ω where V is true airspeed, C is specific fuel consumption, L is lift, D is drag, E

_{max}is endurance, u is relative airspeed and ω is fuel ratio.

4. Which of the following is correct statement regarding cruise method 1?

a) Fuel ratio for very long range aircraft is 1.3

b) Fuel ratio for short range aircraft is 1.3

c) Fuel ratio for medium to long range aircraft is 1.3

d) Fuel ratio for short range aircraft is 1.5

View Answer

Explanation: Fuel ratio for medium to long range aircraft is 1.3 and for short range aircraft is 1.1 and very long range aircraft is 1.5. Fuel ratio is given by ω. Fuel ratio is given by ratio of initial weight of aircraft to that of final weight of aircraft.

5. What is endurance factor?

a) \(\big[\frac{E_{max}}{C}\big]\)

b) \(\big[\frac{E_{max}}{VC}\big]\)

c) \(\big\{\frac{2u^3}{u^4+1}\big\}\)

d) \(\big\{\frac{2u^4}{u^4+1}\big\}\)

View Answer

Explanation: The endurance factor is given by \(\big[\frac{E_{max}}{C}\big]\) where E

_{max}is endurance and C is specific fuel consumption. The endurance equation is given by E=\(\big[\frac{E_{max}}{C}\big]\big\{\frac{2u^2}{u^4+1}\big\}\)l

_{n}ω where V is true airspeed, C is specific fuel consumption, L is lift, D is drag, E

_{max}is endurance, u is relative airspeed and ω is fuel ratio.

6. What is endurance function?

a) \(\big[\frac{E_{max}}{C}\big]\)

b) l_{n}ω

c) \(\big\{\frac{2u^2}{u^4+1}\big\}\)

d) \(\big\{\frac{2u^2}{u^4+1}\big\}\)l_{n}ω

View Answer

Explanation: The endurance factor is given by \(\big\{\frac{2u^2}{u^4+1}\big\}\)l

_{n}ω where E

_{max}is endurance and C is specific fuel consumption. The endurance equation is given by E=\(\big[\frac{E_{max}}{C}\big]\big\{\frac{2u^2}{u^4+1}\big\}\)l

_{n}ω where V is true airspeed, C is specific fuel consumption, L is lift, D is drag, E

_{max}is endurance, u is relative airspeed and ω is fuel ratio.

7. Cruise method 1 is ideal for troposphere.

a) True

b) False

View Answer

Explanation: Cruise method 1 is ideal for stratosphere. The range equation in cruise method 1 is given by R

_{1}=\(\Big[\frac{V_{mdi}}{C}E_{max}\Big]\Big\{\frac{2u^3}{u^4+1}\Big\}\)l

_{n}ω where V is true airspeed, C is specific fuel consumption, L is lift, D is drag, E

_{max}is endurance, u is relative airspeed and ω is fuel ratio.

8. Step climb helps in saving fuel.

a) True

b) False

View Answer

Explanation: Step climb helps in saving fuel.Cruise method 1 is ideal for stratosphere and uses step climb which helps in saving fuel and is economically efficient. The range equation in cruise method 1 is given by R

_{1}=\(\Big[\frac{V_{mdi}}{C}E_{max}\Big]\Big\{\frac{2u^3}{u^4+1}\Big\}\)l

_{n}ω where V is true airspeed, C is specific fuel consumption, L is lift, D is drag, E

_{max}is endurance, u is relative airspeed and ω is fuel ratio.

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