InterviewSolution

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51.	Following diagram represents ____(a) spline lofting(b) conic layout(c) array lofting(d) circle loftingThe question was posed to me during an internship interview.I'd like to ask this question from Configuration Layout in division Configuration Layout and Loft of Aircraft Design
Answer» CORRECT option is (a) SPLINE lofting Explanation: TYPICAL layout is SHOWN by using spline lofting. In spline lofting we use spline line which can be seen in figure. A spline line is used to connect the number of known points in order to have required amount of smoothness as shown in above diagram.

52.	If distance between shoulder point and tangent point is much higher then, it will produce ____________(a) flat C/S shape(b) circle shape only(c) circle with diameter as distance(d) circle of radius as distance between pointsThe question was posed to me during a job interview.This question is from Configuration Layout topic in chapter Configuration Layout and Loft of Aircraft Design
Answer» The correct answer is (a) flat C/S shape The explanation: SELECTION of the shoulder point plays vital role in CONIC curve. If shoulder point is too FAR from tangent point it will result in flat c/s shape. SIMILARLY, if it is too close it will generate non-flat curve.

53.	Find the distance DS in the following diagram. Given contour is parabolic.(a) 3.12(b) 4.12(c) 6.2(d) 0.5I got this question in final exam.My question comes from Configuration Layout topic in section Configuration Layout and Loft of Aircraft Design
Answer» The CORRECT answer is (a) 3.12 Easiest explanation: GIVEN, a PARABOLIC contour. A parabolic shape has conic shape parameter of 0.5. From figure, Conic shape parameter CSP = \|DS\|/\|DC\| From Pythagorean Theorem, \|DC\| = 6.24. Hence, \|DS\| = CSP\|DC\| = 0.56.24 = 3.12.

54.	Term marked by ’?’ in diagram is ________(a) tip chord(b) root chord(c) thrust(d) liftThis question was addressed to me in my homework.This is a very interesting question from Configuration Layout in chapter Configuration Layout and Loft of Aircraft Design
Answer» Right option is (a) tip chord To explain: Typical wing planform is shown in figure. Chord at the fuselage SECTION is CALLED ROOT chord. Chord at wing tip is called tip chord. THRUST is a propulsive force. Lift is an upward force.

55.	If a fuselage has length of 12m and area when viewed from top and side are 4m^2 and 8m^2 respectively. Find the approximate value of volume.(a) 2.26m^3(b) 2.65m^2(c) 2.285(d) 2.65The question was asked during a job interview.I want to ask this question from Configuration Layout topic in chapter Configuration Layout and Loft of Aircraft Design
Answer» RIGHT choice is (a) 2.26m^3 To elaborate: given, Stop = 4m^2, ASIDE = 8m^2, L = 12m Now, internal volume V is given by, V = 3.4(StopAside/4L) = 3.4(48/412) = 3.432/48 = 2.26m^3.

56.	For wetted area Aw, which of the following is correct?(a) Aw = 3.4(Stop + Aside) / 2(b) Aw = 3.4(Stop + Aside) / 5(c) Aw = 3.4(Stop + Aside) / 4(d) Aw = 3.4(Stop + Aside) / 3The question was asked in a national level competition.The query is from Configuration Layout topic in section Configuration Layout and Loft of Aircraft Design
Answer» Right option is (a) AW = 3.4(STOP + Aside) / 2 The best I can explain: Typically, wetted AREA can be estimated through top view and side view of the fuselage. Typically we consider average of the area VIEWED from top and side to find approximated wetted area. Wetted area is given as, Aw = 3.4(Stop + Aside) / 2. Stop = area viewed from top and Aside = area viewed from side.

57.	Let’s consider we want to loft fuselage by using flat wrap method then, __________(a) longitudinal control lines must be straight(b) longitudinal control lines must be curved(c) longitudinal lines must be avoided(d) always use cross shape parameterThis question was addressed to me in unit test.This is a very interesting question from Configuration Layout in portion Configuration Layout and Loft of Aircraft Design
Answer» CORRECT choice is (a) LONGITUDINAL control lines must be straight The explanation: Typically, to use flat wrap method following 2 conditions are required. 1. Longitudinal control lines needs to be straight and 2. Tangent angles of conic should remain CONSTANT LONGITUDINALLY.

58.	The purpose of the longitudinal control lines is __________(a) to connect end points, shoulder points and tangent point of different conic curves(b) to connect tangent points at half distance only of same conic curve(c) only to produce control of lifting lines of same curve(d) to change lifting line slopeI had been asked this question in quiz.The query is from Configuration Layout topic in chapter Configuration Layout and Loft of Aircraft Design
Answer» The correct choice is (a) to connect END points, shoulder points and TANGENT point of different conic CURVES The explanation: Longitudinal CONTROL lines are used to develop SMOOTHLY – lofted fuselage. Longitudinal control lines will connect end points of different conic curves. It is also used to connect different shoulder points and tangent points to respective shoulder points and tangent points of different conic curves.

59.	Let’s consider flat wrapping is to be used for lofting. If wing has taper ratio of 0.4, span of 26.6ft and root chord Cr is 76in then, find the area to be covered by flat wrapping.(a) 118ft^2(b) 200ft^2(c) 1600in(d) 10mThis question was addressed to me by my school teacher while I was bunking the class.Question is from Configuration Layout topic in chapter Configuration Layout and Loft of Aircraft Design
Answer» CORRECT OPTION is (a) 118ft^2 To elaborate: Given, CR = 76in = 7612ft = 912ft, span b=26.6ft, TAPER ratio t=0.4 Area S is given by, S = Crb(1+t)/2 = 91226.6*(1+0.4)/2 = 16981.44 in^2 = 16981.44/144 ft^2 = 118ft^2.

60.	The first step of conic construction is __________(a) selecting desired end points at desired tangent angle(b) selecting a circle to proceed(c) selecting ellipse always(d) selecting parabola alwaysThe question was asked by my college director while I was bunking the class.Asked question is from Configuration Layout topic in portion Configuration Layout and Loft of Aircraft Design
Answer» The correct option is (a) selecting desired end POINTS at desired tangent angle The explanation: Conic lofting method is a step by step method to GENERATE conic of desired cross-section. In GENERAL, first step of any conic development is to fixe two end points of the SHAPE. And based on this endpoint we will fix the tangent point as per our requirement.

61.	Typically, a fuselage is lofted by using 5-10 control station based on requirements of fuselage.(a) True(b) FalseI had been asked this question by my college professor while I was bunking the class.This question is from Configuration Layout in division Configuration Layout and Loft of Aircraft Design
Answer» RIGHT answer is (a) True To explain I would say: CONTROL STATION or control cross section are used to develop the LONGITUDINAL control lines. These control stations are DRAWN to enclose the different internal components.

62.	Following graph represents ____(a) graphical method to find MAC(b) graphical method to produce drag(c) graphical method to find lift(d) graphical method to find lift-curveThis question was addressed to me in exam.Question is taken from Configuration Layout topic in section Configuration Layout and Loft of Aircraft Design
Answer» Right answer is (a) GRAPHICAL method to FIND MAC To EXPLAIN: Above figure is showing the typical graphical method to find the MAC. Here, first we project the root chord from tip chord and vice-versa as shown by DASHED lines from respective chords. After that we draw a line from which will connect midpoints of root and tip chord. Intersection of both lines will provide MAC which will be LOCATED at Y distance from root chord as shown.

63.	Wing planform is always elliptic.(a) True(b) FalseThe question was asked in an interview.The question is from Configuration Layout in section Configuration Layout and Loft of Aircraft Design
Answer» CORRECT answer is (b) False The best I can explain: WING planform is shape generate when viewed from TOP. Elliptic WINGS are more EFFICIENT in terms of lifting properties. However to manufacture it is also difficult. Hence, wing planform is not always elliptic rather it will be selected according to mission requirements.

64.	Fuselage has wetted area of 20m^2. Given Aright = 5m^2. Find the value of area viewed from top.(a) 6.8m^2(b) 9.8m^2(c) 6.8m(d) 68mThe question was posed to me in an interview for internship.The query is from Configuration Layout in portion Configuration Layout and Loft of Aircraft Design
Answer» CORRECT answer is (a) 6.8m^2 Easiest explanation: GIVEN WETTED AREA Aw = 20m^2, Aright = 5m^2. Now, area vied from top A is given by, A = 0.588Aw – Aright = 0.58820 – 5 = 11.764-5 = 6.764 = 6.8m^2.

65.	Which of the following is correct in terms of the wing layout with twist?(a) Incidence at each span station must be considered and chord should be rotated accordingly(b) Only untwist airfoils can be used for layout(c) Only rotation of chord line is required at c/6 points(d) Only chord line should be rotated by reducing length of chordThis question was addressed to me in examination.The above asked question is from Configuration Layout topic in chapter Configuration Layout and Loft of Aircraft Design
Answer» The correct CHOICE is (a) Incidence at each span station MUST be considered and chord should be rotated accordingly Best explanation: In general, airfoils are drawn to find the complete WING layout. When wing has some twist then, we need to find incidence at each span station in order to include EFFECTS of twist. Also chord needs to be rotated accordingly before drawing an actual airfoil for lofting.