Typically, designer designs thrust loading based on ________

only Lift

only landing conditions

only static sea-level conditions

static sea-level conditions, take-off requirement etc

Correct Answer : static sea-level conditions, take-off requirement etc

Explanation : When designer speaks for a thrust loading it generally refers to the value which has been calculated for standard day conditions, static sea-level conditions, take-off performance etc. Different phases incorporate different values of thrust loading. Hence, a designer typically converts them to take-off conditions.

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.