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Correct Answer : 0.68
Explanation : Given, area ratio A/A* = 1.110Now, as we know, A/A* = (1/M)*(1+0.2M2)3*0.5787For given problem, we will substitute different values of Mach number from the options.Let’s consider M = 0.68Hence, for assumed value of Mach number,A/A* = (1/0.68)*(1+0.2*0.682)3*0.5787A/A* = 0.8510*1.092483 = 1.110.The evaluated area ratio is equal to the given area ratio.Hence, correct value of Mach number is 0.68.
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.
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
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.
