For estimated value of the thrust loading, we got three different values of wing loading. As a designer typically which wing loading should be considered?

Any value

Lowest among all three

Always take average

Highest among all three

Correct Answer : Lowest among all three

Explanation : In general, we chose the lowest among all the values. This is done if and only if the lowest value can satisfy almost every mission phase requirement; from take-off to land. If it does not satisfy then, we should estimate another value.

Recently Updated in Aircraft Design Questions

What should be the aspect ratio (AR) of the prop aircraft if it is designed to work with maximum loiter wing loading of 32, CD0 = 0.06, dynamic pressure of 20 unit and Oswald efficiency as 0.6.

9.65

8.54

7.65

7.54

Correct Answer : Option (B) : 7.54

Explaination :

An aircraft is to be designed to have max lift coefficient as 2.8 and at q=10Pa. If maximum load factor n=5 then, what will be the stall speed?

1.80m/s

1.80mph

2.80mph

2.80m/s

Correct Answer : Option (A) : 1.80m/s

Explanation :

An aircraft has lift to drag ratio during cruise as 2.5 and load factor as 1.2. Which value of thrust loading should be selected?

0.28

0.38

0.48

0.58

Correct Answer : Option (C) : 0.48

Explanation : Given, load factor n=1.2, lift to drag L/D = 2.5
Now, n at cruise is given by, n = (T/W)*(L/D).
Hence, T/w is given as,
T/W = n / (L/D) = 1.2/2.5 = 0.48.