

InterviewSolution
This section includes InterviewSolutions, each offering curated multiple-choice questions to sharpen your knowledge and support exam preparation. Choose a topic below to get started.
201. |
What is the graph that is represented in the airfoil section?(a) Lift-moment ratio(b) Coefficient of lift-coefficient of drag ratio(c) Angle of attack-drag ratio(d) Lift–angle of attack ratioThe question was posed to me in quiz.The question is from Airfoil Characteristics in portion Incompressible Flow over Airfoils of Aerodynamics |
Answer» Right option is (B) Coefficient of lift-coefficient of drag ratio |
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202. |
Is turbulence flow is irregular?(a) False(b) TrueThis question was posed to me in my homework.Origin of the question is Turbulent Flow in portion Incompressible Flow over Airfoils of Aerodynamics |
Answer» Correct ANSWER is (b) True |
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203. |
The total skin-friction drag coefficient for laminar flow with Reynolds number at the trailing edge being Rec=40000 and chord length is 1m, is _____(a) 0.01328(b) 0.00664(c) 0.02656(d) 0.664The question was asked during an interview for a job.My question is based upon Laminar Flow topic in portion Incompressible Flow over Airfoils of Aerodynamics |
Answer» The correct CHOICE is (a) 0.01328 |
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204. |
The essential assumption of airfoil being a flat plate with a zero angle of attack gives accurate results always.(a) False(b) TrueI had been asked this question in final exam.The above asked question is from Laminar Flow topic in division Incompressible Flow over Airfoils of Aerodynamics |
Answer» Right option is (a) False |
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205. |
Is interface between the solid and fluid, shear stresses develop as the solid attempts to slow down the fluid flowing?(a) True(b) FalseThe question was posed to me by my school principal while I was bunking the class.This intriguing question comes from Viscous Flow topic in division Incompressible Flow over Airfoils of Aerodynamics |
Answer» Right CHOICE is (a) True |
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206. |
A higher value of L/D ratio deteriorates climbing performance for the flight.(a) True(b) FalseI got this question in an interview for job.This intriguing question comes from Modern Low Speed Airfoils in section Incompressible Flow over Airfoils of Aerodynamics |
Answer» Correct ANSWER is (b) False |
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207. |
The quarter-chord is the aerodynamic center for a cambered airfoil.(a) True(b) FalseI have been asked this question in quiz.I'd like to ask this question from The Cambered Airfoil topic in division Incompressible Flow over Airfoils of Aerodynamics |
Answer» The correct CHOICE is (a) True |
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208. |
Select the statement which is not true for the solution of \(\frac {1}{2\pi } \int_0^c \frac {\gamma(\xi)d\xi}{x-\xi}\)=V∞(α-\(\frac {dz}{dx}\)) for a cambered airfoil.(a) An depends on chord length of the airfoil(b) A0 depends on the slope of the camber line(c) An depends on the slope of the camber line(d) A0 depends on the angle of attackThis question was posed to me by my school teacher while I was bunking the class.My doubt is from The Cambered Airfoil in section Incompressible Flow over Airfoils of Aerodynamics |
Answer» Correct option is (a) An DEPENDS on chord length of the airfoil |
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209. |
Is supersonic flight uses supercritical airfoil?(a) True(b) FalseThe question was posed to me in unit test.Asked question is from The Cambered Airfoil topic in division Incompressible Flow over Airfoils of Aerodynamics |
Answer» Right choice is (a) True |
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210. |
Is ‘C’ denotes a dyed circuit, composed of same fluid particles?(a) False(b) TrueI got this question during an online exam.My question is from Kelvin’s Circulation Theorem and the Starting Vortex topic in division Incompressible Flow over Airfoils of Aerodynamics |
Answer» Correct choice is (b) True |
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211. |
How stagnation point on the topside of the airfoil reaches the trailing edge?(a) Due to viscous forces(b) Due to surface forces(c) Due to pressure forces(d) Due to drag forcesI have been asked this question in an interview.Question is from The Kutta Condition in division Incompressible Flow over Airfoils of Aerodynamics |
Answer» The correct OPTION is (a) Due to viscous forces |
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212. |
Is fluid is initially in irrotational motion?(a) True(b) FalseI had been asked this question during an interview.My question is taken from Kelvin’s Circulation Theorem and the Starting Vortex topic in section Incompressible Flow over Airfoils of Aerodynamics |
Answer» Correct option is (a) True |
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213. |
Vortex flow occurs at ___________(a) Leading edge(b) Trailing edge(c) Chord(d) Chamber lineThis question was addressed to me by my college professor while I was bunking the class.Question is taken from The Kutta Condition in section Incompressible Flow over Airfoils of Aerodynamics |
Answer» RIGHT answer is (b) Trailing edge Explanation: VORTEX flow occurs at the trailing edge and because the RADIUS of the sharp trailing edge is zero, the speed of the air around the trailing edge should be INFINITELY fast, real fluid cannot move at infinite speed, they can move extremely fast FINITE speed. |
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214. |
How many stagnation points on the oval cylinder with non-zero angle of attack?(a) Two(b) Zero(c) More than zero(d) OneI got this question at a job interview.My enquiry is from The Kutta Condition topic in chapter Incompressible Flow over Airfoils of Aerodynamics |
Answer» Correct choice is (a) Two |
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215. |
How vortex filament are arrange in the vortex sheet?(a) Side by side(b) Front and back(c) Up and down(d) Left and rightThe question was posed to me by my college professor while I was bunking the class.The doubt is from The Vortex Sheet topic in chapter Incompressible Flow over Airfoils of Aerodynamics |
Answer» The correct OPTION is (a) Side by side |
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216. |
Define stalling angle in the graph.(a) The curve increases maximum at a particular section and decreases rapidly in the same section(b) The curve increases at different section and decreases rapidly at different section(c) The curve remains constant at all section(d) Lift curve will increases and drag curve will remain constantI got this question at a job interview.Query is from Airfoil Characteristics in portion Incompressible Flow over Airfoils of Aerodynamics |
Answer» The correct choice is (a) The curve increases MAXIMUM at a PARTICULAR section and decreases RAPIDLY in the same section |
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