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?(a) Lowest among all three(b) Highest among all three(c) Any value(d) Always take averageThe question was posed to me in an online quiz.Enquiry is from Selection of Thrust-Weight and Wing Loading in portion Thrust-Weight Ratio and Wing Loading of Aircraft Design

For estimated value of the thrust loading, we got three different valu

1.	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?(a) Lowest among all three(b) Highest among all three(c) Any value(d) Always take averageThe question was posed to me in an online quiz.Enquiry is from Selection of Thrust-Weight and Wing Loading in portion Thrust-Weight Ratio and Wing Loading of Aircraft Design
Answer» Correct ANSWER is (a) Lowest among all three The best I can explain: 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.

Discussion

No Comment Found

Related InterviewSolutions

A/C with higher thrust to weight ratio can accelerate more quickly.(a) True(b) FalseI had been asked this question by my college director while I was bunking the class.This question is from Thrust Weight Ratio-1 in section Thrust-Weight Ratio and Wing Loading of Aircraft Design
An aircraft has catapult end speed of 30m/s and wind over deck as 20m/s. If maximum CL is 2.6 and density is 1.22 then, find catapult wing loading.(a) 3276.859(b) 327(c) 32(d) 2I have been asked this question in an interview for job.The origin of the question is Wing Loading in division Thrust-Weight Ratio and Wing Loading of Aircraft Design
Design lift coefficient is determined by wing loading.(a) True(b) FalseThis question was addressed to me in an online interview.I'm obligated to ask this question of Wing Loading in chapter Thrust-Weight Ratio and Wing Loading of Aircraft Design
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?(a) 0.48(b) 0.58(c) 0.38(d) 0.28The question was asked in final exam.This is a very interesting question from Selection of Thrust-Weight and Wing Loading topic in portion Thrust-Weight Ratio and Wing Loading of Aircraft Design
A prop driven A/C has BHP/W as 0.08. If density ratio is 0.2 and take off lift coefficient is 3 then find take-off parameter for the aircraft. Given wing loading W/s = 35.(a) 700(b) 800(c) 900(d) 500This question was addressed to me in a national level competition.Query is from Wing Loading topic in portion Thrust-Weight Ratio and Wing Loading of Aircraft Design
Low wing loading increases __________(a) weight and cost of aircraft(b) weight only(c) lofting(d) draftingI had been asked this question in a national level competition.The origin of the question is Selection of Thrust-Weight and Wing Loading in section Thrust-Weight Ratio and Wing Loading of Aircraft Design
A twin turbo prop is flying with power loading of 12. What will be the maximum velocity?(a) 48.225 mph(b) 48.225 m/s(c) 48.225 km/h(d) 225.48 m/hThe question was asked by my college professor while I was bunking the class.My query is from Thrust Weight Ratio-2 in division Thrust-Weight Ratio and Wing Loading of Aircraft Design
An aircraft is flying with wing loading of 50 and maximum CL as 2.4. If density is 1.225 then, find the stall speed of the aircraft.(a) 5.832m/s(b) 5.823(c) 5.632m/s(d) 5.632I got this question by my school principal while I was bunking the class.This intriguing question originated from Wing Loading topic in portion Thrust-Weight Ratio and Wing Loading of Aircraft Design
A jet aircraft has maximum lift to drag as 12. Find the value of the thrust loading at the cruise.(a) 0.096(b) 0.0069(c) 0.96(d) 0.0096The question was asked in an interview for job.Question is taken from Thrust Weight Ratio-2 in chapter Thrust-Weight Ratio and Wing Loading of Aircraft Design
Thrust loading is defined as ____________(a) ratio of thrust produced by an engine to the weight of the aircraft(b) ratio of lift to thrust(c) ratio of drag to thrust(d) ratio of lift to weightThis question was addressed to me in class test.This interesting question is from Thrust Weight Ratio-2 topic in chapter Thrust-Weight Ratio and Wing Loading of Aircraft Design

Discussion

No Comment Found

Related InterviewSolutions

Reply to Comment