Which of the following is not an inlet location?

Lofting

Tail root location

Chin buried engine

Side inlet location of buried engine

Correct Answer : Side inlet location of buried engine

Explanation : Here, typical side inlet location of buried engine is shown. Tail root engine is located at root section of the tail. Lofting is mathematical modelling of aircraft components. It is an important step in aircraft design. Chin buried is similar to that of the nose inlet section. Chin inlet suffers from various drawbacks such as ingestion of foreign objects etc.

Recently Updated in Aircraft Design Questions

Typically, main fuel tank is located near to the ____

at cockpit

at passenger cabin

inboard section of the wing

at tip of the wing

Correct Answer : Option (C) : inboard section of the wing

Explanation : Typically, main fuel tank is located near to the inboard section of the wing. At tip, tip tanks are placed. Due to safety parameters, one soul avoid placing fuel tanks at the passenger cabin or at the cockpit.

Integral tanks are _________

cavities within the aircraft�s airframe itself

there is no such type of fuel tank

external tanks needs to be fabricated

external tanks required to put in the airframe

Correct Answer : Option (A) : cavities within the aircraft�s airframe itself

Explanation : As name suggests a typical integral tank is an integral part of the aircraft itself. Integral tanks are cavities within the structure of airframe. These cavities are then sealed in order to form a fuel tank. Integral tanks are not external tanks

What is the disadvantage of bladder fuel tank?

Self sealing

Thrust loading

Loss of available fuel volume

No loss in fuel volume

Correct Answer : Option (C) : Loss of available fuel volume

Explanation : A typical bladder tank is formed by stuffing a shaped rubber bag into a cavity in the aircraft structure. However, the thick rubber bag results in the kids of available fuel volume. Self-sealing property is one of the advantages of the bladder tank. Thrust loading is the ratio of thrust to weight.