If an aircraft has three components which can be considered as vulnerable components then, evaluate total vulnerable area. Given area of component 1, 2 and 3 are 5ft^2, 4ft^2 and 80ft^2 respectively with Pk as 1, 0.5 and 0.3 for component 1, 2 and 3 respectively.(a) 31ft^2(b) 50ft^2(c) 10ft^2(d) 4ftThe question was posed to me in my homework.This key question is from Configuration Layout topic in section Configuration Layout Considerations of Aircraft Design

If an aircraft has three components which can be considered as vulnera

1.	If an aircraft has three components which can be considered as vulnerable components then, evaluate total vulnerable area. Given area of component 1, 2 and 3 are 5ft^2, 4ft^2 and 80ft^2 respectively with Pk as 1, 0.5 and 0.3 for component 1, 2 and 3 respectively.(a) 31ft^2(b) 50ft^2(c) 10ft^2(d) 4ftThe question was posed to me in my homework.This key question is from Configuration Layout topic in section Configuration Layout Considerations of Aircraft Design
Answer» The correct CHOICE is (a) 31ft^2 Easy explanation: Given, part 1: area a1=5ft^2, pk1=1 Part 2: area a2=4ft^2, pk2=0.5 Part 2: area a3=80ft^2, pk3=0.3 Total VULNERABLE area = a1pk1 + a2pk2 + a3pk3 = 51 + 40.5 + 800.3 = 5+2+24 = 31ft^2.

Discussion

No Comment Found

Related InterviewSolutions

If an aircraft is not designed properly then __________(a) it can experience excessive flow separation(b) it will have more lift(c) it will have less drag(d) it will have higher aerodynamic efficiencyThe question was asked in an interview for job.The origin of the question is Configuration Layout topic in portion Configuration Layout Considerations of Aircraft Design
Short and fat fuselage will have ___________(a) lower tail arm(b) higher tail arm(c) higher fineness ratio(d) higher wetted areaI had been asked this question during an interview.I'd like to ask this question from Configuration Layout topic in section Configuration Layout Considerations of Aircraft Design
Which of the following is incorrect?(a) Tightly packed fuselage will not affect maintainability(b) Waiting area can be minimized by lowering fineness ratio(c) Fineness ratio is division of length of fuselage to maximum diameter(d) Wetted area can affect the drag propertiesThe question was posed to me in my homework.The query is from Configuration Layout in division Configuration Layout Considerations of Aircraft Design
Vortex generator is used to ____________(a) reattach separated flow(b) increase volume(c) increase surface area(d) separate flowThis question was addressed to me in my homework.My question is based upon Configuration Layout in division Configuration Layout Considerations of Aircraft Design
What is the disadvantage of short and fat fuselage?(a) Higher supersonic wave drag(b) Higher incompressible wave drag(c) Lower supersonic wave drag(d) Lower wetted areaThe question was asked in a job interview.The question is from Configuration Layout topic in chapter Configuration Layout Considerations of Aircraft Design
Span-loading is defined as __________(a) distribution of weight along span as lift distribution(b) thrust loading(c) wing loading(d) inverse of power loadingI got this question in my homework.My question comes from Configuration Layout topic in chapter Configuration Layout Considerations of Aircraft Design
Following diagram represents __________(a) ideal span loading(b) ideal thrust loading(c) ideal wing loading(d) ideal power loadingThe question was asked at a job interview.My enquiry is from Configuration Layout topic in division Configuration Layout Considerations of Aircraft Design
Drag divergence Mach number will increase by using _______________(a) area rule(b) increment in total volume(c) increase in drag(d) drag increment at maximum areaI got this question during a job interview.I want to ask this question from Configuration Layout in chapter Configuration Layout Considerations of Aircraft Design
___________ can be considered as one of the most powerful aerodynamic consideration.(a) Wetted area(b) Number of spars(c) Number of ribs(d) Only wingspanThis question was addressed to me in an internship interview.This key question is from Configuration Layout in portion Configuration Layout Considerations of Aircraft Design
What is the load path?(a) Structural elements by virtue of which opposing forces are connected(b) Structural elements by virtue of which similar forces are connected(c) Structural elements by virtue of which opposite moments are linked(d) Lifting pathI have been asked this question in unit test.I would like to ask this question from Configuration Layout topic in section Configuration Layout Considerations of Aircraft Design

Discussion

No Comment Found

Related InterviewSolutions

Reply to Comment