

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.
51. |
The 3D flow characteristic attributed to the wings is a by-product of_____(a) Pressure imbalance over top and bottom surfaces of the wing(b) Pressure imbalance between leading and trailing edge of the airfoil(c) Thickness of the wing(d) Extra lift producedI have been asked this question in class test.I need to ask this question from Downwash and Induced Drag topic in chapter Flow over Airfoils over Finite Wing of Aerodynamics |
Answer» Correct answer is (a) Pressure IMBALANCE over top and bottom surfaces of the WING |
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52. |
Is change in lift distribution is known as lift section?(a) True(b) FalseThe question was asked in an interview for job.This intriguing question comes from Prandtl’s Classical Lifting-Line Theory topic in chapter Flow over Airfoils over Finite Wing of Aerodynamics |
Answer» RIGHT choice is (a) True The best I can explain: The change in lift distribution is known at given lift section, it is possible to predict how that section influences the lift over its NEIGHBORS, the VERTICAL induced VELOCITY, up wash or down wash can be quantified using the velocity distribution with in VORTEX. |
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53. |
The incorrect difference between airfoil and wings is_______(a) Presence of induced drag in wings(b) Different effective angles of attack seen by(c) Difference in the lift-curve slope(d) Lift slope of the wing is higher than of airfoilThe question was posed to me during an online exam.The above asked question is from Prandtl’s Classical Lifting-Line Theory topic in section Flow over Airfoils over Finite Wing of Aerodynamics |
Answer» Correct choice is (d) Lift slope of the wing is higher than of AIRFOIL |
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54. |
The lift coefficient for the airfoil section on a wing ______(a) Depends on local lift slope for airfoil(b) Is same for the entire wing(c) Is equal to the aerodynamic twist(d) Is constant alwaysThis question was addressed to me in a national level competition.I would like to ask this question from Prandtl’s Classical Lifting-Line Theory topic in chapter Flow over Airfoils over Finite Wing of Aerodynamics |
Answer» Right option is (a) Depends on local lift slope for airfoil |
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55. |
The lift distribution goes to zero at the tips for the finite wings.(a) False(b) True(c) Only true for elliptical wings(d) Only true for rectangular wingThis question was addressed to me in an interview for job.Asked question is from The Vortex Filament, the Biot-Savart Law, Helmholtz Theorem topic in division Flow over Airfoils over Finite Wing of Aerodynamics |
Answer» Correct option is (B) True |
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56. |
Is lift and drag are the total aerodynamic force acting the body?(a) True(b) FalseThe question was posed to me in semester exam.My doubt is from Downwash and Induced Drag topic in portion Flow over Airfoils over Finite Wing of Aerodynamics |
Answer» The correct option is (a) True |
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57. |
Is Newton’s third law of motion is an application for lift on airfoil?(a) False(b) TrueI have been asked this question in an online quiz.The above asked question is from Downwash and Induced Drag topic in division Flow over Airfoils over Finite Wing of Aerodynamics |
Answer» Correct answer is (b) True |
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58. |
For a finite wing, the local relative wind differs by the free-stream velocity by some angle. This angle is called as ____(a) Angle of attack(b) Twist angle(c) Relative angle of attack(d) Induced angle of attackThis question was posed to me in quiz.My question is from Downwash and Induced Drag in chapter Flow over Airfoils over Finite Wing of Aerodynamics |
Answer» CORRECT option is (d) Induced angle of attack The BEST explanation: For a wing, induced velocity in the downward direction is PRESENT apart from the free-stream velocity. The resultant of both (RELATIVE local wind) is inclined to the free-stream velocity by an angle, which is called the induced angle of attack. |
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59. |
The infinite downwash at the wing tips for a single horseshoe vortex in Prandtls lifting line theory was a wrong result. Which of the following does not relate to the correction made?(a) Superimposition of horseshoe vortices(b) Lifting line along the span(c) Trailing vortices only at the tip(d) Different length of bound vorticesThe question was posed to me during an online exam.Query is from Prandtl’s Classical Lifting-Line Theory topic in division Flow over Airfoils over Finite Wing of Aerodynamics |
Answer» Right CHOICE is (c) TRAILING vortices only at the tip |
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60. |
Is Biot-savart law is used for computing the resultant magnetic field?(a) True(b) FalseI had been asked this question in a job interview.My question is from The Vortex Filament, Biot-Savart Law, Helmholtz Theorem topic in division Flow over Airfoils over Finite Wing of Aerodynamics |
Answer» Right answer is (a) True |
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61. |
Is prandtl lifting line theory is a mathematical model that predicts lift distribution over a three-dimensional wing?(a) True(b) FalseI got this question in an online interview.I'm obligated to ask this question of The Lifting Surface Theory in portion Flow over Airfoils over Finite Wing of Aerodynamics |
Answer» Right CHOICE is (a) True |
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62. |
A condition in which the wing has different values of α along the span is called as ______(a) Washout(b) Geometric twist(c) Aerodynamic twist(d) WashinThe question was posed to me at a job interview.This is a very interesting question from The Vortex Filament, the Biot-Savart Law, Helmholtz Theorem topic in portion Flow over Airfoils over Finite Wing of Aerodynamics |
Answer» Correct option is (b) Geometric TWIST |
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63. |
Select the incorrect statement regarding the terminology used in the study of incompressible flow over finite wings.(a) Induced drag is finite(b) Circulation is constant(c) Downwash is absent(d) Vorticity induces velocityThis question was addressed to me in quiz.This is a very interesting question from The Vortex Filament, the Biot-Savart Law, Helmholtz Theorem topic in division Flow over Airfoils over Finite Wing of Aerodynamics |
Answer» Right option is (c) Downwash is absent |
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64. |
Is induced drag produce lift?(a) True(b) FalseThe question was posed to me during an interview for a job.Question is taken from Downwash and Induced Drag in section Flow over Airfoils over Finite Wing of Aerodynamics |
Answer» The correct CHOICE is (a) True |
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65. |
According to the reasoning given by Prandtl for his lifting line theory, finite wing is like a ________(a) Bound vortex(b) Horseshoe vortex(c) Free vortex(d) Trailing vortexThis question was posed to me in an interview.I want to ask this question from Prandtl’s Classical Lifting-Line Theory in portion Flow over Airfoils over Finite Wing of Aerodynamics |
Answer» Right answer is (a) Bound VORTEX |
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66. |
The total drag coefficient for a wing is given by______(a) cd=\(\frac {D_f+D_P+D_i}{Sq_∞}\)(b) Cd=\(\frac {D_f+D_P}{Sq_∞}\)(c) Cd=\(\frac {D_f+D_P+D_i}{Sq_∞}\)(d) Cd=\(\frac {D_f+D_P}{Sq_∞}\)+DiThe question was posed to me in an interview for internship.My question comes from Downwash and Induced Drag in division Flow over Airfoils over Finite Wing of Aerodynamics |
Answer» Right choice is (c) Cd=\(\FRAC {D_f+D_P+D_i}{Sq_∞}\) |
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67. |
Which is the wrong implication of the elliptical lift distribution for a wing?(a) Circulation varies elliptically along span(b) Span length does not affect circulation(c) Lift is zero at the tips(d) Maximum lift is at the centerThe question was posed to me during an interview.This is a very interesting question from Prandtl’s Classical Lifting-Line Theory in portion Flow over Airfoils over Finite Wing of Aerodynamics |
Answer» The correct option is (b) Span length does not affect circulation |
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68. |
Is integral is usually around a closed curve?(a) True(b) FalseThe question was posed to me during an interview.My doubt stems from The Vortex Filament, Biot-Savart Law, Helmholtz Theorem topic in section Flow over Airfoils over Finite Wing of Aerodynamics |
Answer» CORRECT answer is (a) True The EXPLANATION is: The integral is usually around a closed curve since stationary electric currents can only flow around closed paths when they are bounded. However, the law ALSO applies to infinitely long wires as used in the definition of the SI UNIT of electric current. |
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69. |
Which is the incorrect analogyout of the following regarding Biot-Savart law?(a) Induced velocity: Magnetic induction(b) Vortex Filament: Current-carrying Wire(c) Vorticity: Velocity(d) Aerodynamics: ElectromagnetismThis question was posed to me by my college director while I was bunking the class.My question comes from The Vortex Filament, the Biot-Savart Law, Helmholtz Theorem topic in section Flow over Airfoils over Finite Wing of Aerodynamics |
Answer» Right answer is (C) Vorticity: Velocity |
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70. |
The angle between the chord line and the direction of free-stream velocity is called the angle of attack.(a) True for airfoil only(b) True for wing only(c) True for airfoil and partially true for wings(d) FalseThis question was addressed to me during an interview.This key question is from Downwash and Induced Drag in section Flow over Airfoils over Finite Wing of Aerodynamics |
Answer» Right CHOICE is (c) True for airfoil and partially true for wings |
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71. |
The circulation at the center for an elliptical wing distribution does not depend upon ________(a) Lift distribution(b) Density of fluid at center(c) Free-stream velocity(d) Total span lengthThis question was posed to me during an online interview.This is a very interesting question from Prandtl’s Classical Lifting-Line Theory topic in chapter Flow over Airfoils over Finite Wing of Aerodynamics |
Answer» The correct answer is (b) Density of FLUID at center |
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72. |
Is wing tips vortices produce the down wash?(a) True(b) FalseI have been asked this question during an interview.The doubt is from Downwash and Induced Drag in portion Flow over Airfoils over Finite Wing of Aerodynamics |
Answer» Right option is (a) True |
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73. |
Is it difficult to predict the amount of lift that a wing geometry will generate?(a) False(b) TrueI had been asked this question in an online quiz.My question is from Prandtl’s Classical Lifting-Line Theory topic in portion Flow over Airfoils over Finite Wing of Aerodynamics |
Answer» Correct answer is (b) True |
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74. |
The velocity induced by an infinite vortex filament, with strength Γ at some point is correctly given as______ (r, h are the distance and height to the point respectively).(a) V=\(\frac {\Gamma }{2\pi h}\)(b) V=\(\frac {\Gamma }{2\pi r}\)(c) V=\(\frac {\Gamma }{2h}\)(d) V=\(\frac {\Gamma }{2r}\)I had been asked this question in quiz.My question is from The Vortex Filament, the Biot-Savart Law, Helmholtz Theorem topic in division Flow over Airfoils over Finite Wing of Aerodynamics |
Answer» Right answer is (a) V=\(\frac {\Gamma }{2\pi h}\) |
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75. |
The incorrect statement regarding Helmholtz theorems is____(a) Valid for all inviscid flows(b) Γ remains constant along vortex filament(c) Describes vortex behavior(d) Vortex filament forms a closed loop or extends till the boundaries of the fluidThe question was posed to me in an internship interview.My question is based upon The Vortex Filament, the Biot-Savart Law, Helmholtz Theorem topic in section Flow over Airfoils over Finite Wing of Aerodynamics |
Answer» Correct option is (a) Valid for all inviscid FLOWS |
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76. |
The downward velocity induced by the trailing vortex in the vicinity of the wing-tips is called as _____(a) Downwash(b) Local relative velocity(c) Effective velocity(d) Wing velocityThis question was posed to me in examination.My question is from Downwash and Induced Drag in division Flow over Airfoils over Finite Wing of Aerodynamics |
Answer» Right choice is (a) Downwash |
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77. |
Select the incorrect statement for a flow over wings.(a) Induced drag comes from pressure- drag(b) Pressure imbalance makes D’Alembert’s paradox does not occur(c) 3D flow over wings cause induced drag(d) Induced drag is a ‘type’ of pressure- dragI got this question in an interview for job.My query is from Downwash and Induced Drag topic in division Flow over Airfoils over Finite Wing of Aerodynamics |
Answer» The correct OPTION is (a) Induced drag COMES from pressure- drag |
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78. |
The trailing vortex is formed at each wing-tip as there is a circulatory motion established by the____(a) Leaking flow at the wing- tips(b) Flowing wind(c) Viscosity(d) Air tornadoesThis question was addressed to me by my college director while I was bunking the class.I want to ask this question from Downwash and Induced Drag in section Flow over Airfoils over Finite Wing of Aerodynamics |
Answer» The correct answer is (a) Leaking flow at the WING- tips |
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79. |
The span-wise component of flow over the top surface of the wing flows______(a) From wing-tip to root(b) From root to wing-tip(c) Along the free-stream direction(d) Perpendicular to the wing upwardsThe question was posed to me in unit test.My question is taken from Downwash and Induced Drag topic in division Flow over Airfoils over Finite Wing of Aerodynamics |
Answer» The correct OPTION is (a) From wing-tip to root |
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80. |
Is local induced change the angle of attack on a given section of a wing?(a) True(b) FalseThe question was posed to me in examination.Question is from Prandtl’s Classical Lifting-Line Theory in portion Flow over Airfoils over Finite Wing of Aerodynamics |
Answer» Correct option is (a) True |
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81. |
Is shed vortex can be modeled at vertical velocity?(a) True(b) FalseThe question was posed to me at a job interview.My doubt stems from Prandtl’s Classical Lifting-Line Theory topic in chapter Flow over Airfoils over Finite Wing of Aerodynamics |
Answer» Right choice is (a) True |
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82. |
Is vortex filament cannot begin or terminate in the air?(a) True(b) FalseI have been asked this question in my homework.This intriguing question originated from Prandtl’s Classical Lifting-Line Theory in section Flow over Airfoils over Finite Wing of Aerodynamics |
Answer» Correct option is (a) True |
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83. |
In Biot-Savart law, the circulation taken about any path enclosing the vortex filament is____(a) Constant(b) Depends on the local strength(c) Zero(d) Path-dependentThis question was addressed to me in an online interview.My question comes from The Vortex Filament, the Biot-Savart Law, Helmholtz Theorem topic in chapter Flow over Airfoils over Finite Wing of Aerodynamics |
Answer» The correct choice is (a) CONSTANT |
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84. |
Which of the following is incorrect for a finite wing?(a) Streamlines on the top surface bend towards the root(b) Span-wise flow at the bottom surface is towards the tip(c) Higher pressure region exists at the top surface(d) Streamlines on the bottom surface bend towards the tipI got this question by my college professor while I was bunking the class.This key question is from Downwash and Induced Drag topic in portion Flow over Airfoils over Finite Wing of Aerodynamics |
Answer» Correct choice is (C) Higher pressure region exists at the top surface |
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85. |
Tapered wings are used more rather than elliptical wing planforms practically. The reason being______(a) Easy to manufacture than elliptic wings(b) Aspect ratio more important for low induced drag(c) Tapered wing resembles elliptic wing highly(d) Tapered wing is another name for elliptic wingI had been asked this question in exam.The query is from Prandtl’s Classical Lifting-Line Theory topic in division Flow over Airfoils over Finite Wing of Aerodynamics |
Answer» Correct choice is (a) Easy to manufacture than ELLIPTIC WINGS |
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86. |
Is 2D version of Biot-Savart equation is used, when the sources are invariant in one direction?(a) True(b) FalseI had been asked this question in an internship interview.This intriguing question originated from The Vortex Filament, Biot-Savart Law, Helmholtz Theorem in portion Flow over Airfoils over Finite Wing of Aerodynamics |
Answer» Right ANSWER is (a) True |
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87. |
Is circular filament is of constant thickness?(a) True(b) FalseThe question was asked in final exam.The origin of the question is The Vortex Filament, Biot-Savart Law, Helmholtz Theorem in portion Flow over Airfoils over Finite Wing of Aerodynamics |
Answer» Right choice is (a) True |
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88. |
Is vortex filament is a very thin strip?(a) True(b) FalseThe question was posed to me in class test.Origin of the question is The Vortex Filament, Biot-Savart Law, Helmholtz Theorem in section Flow over Airfoils over Finite Wing of Aerodynamics |
Answer» Right ANSWER is (a) True |
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89. |
Biot-Savart law can be used to describe inviscid, incompressible flows.(a) True(b) FalseI have been asked this question during an online interview.This interesting question is from The Vortex Filament, the Biot-Savart Law, Helmholtz Theorem in portion Flow over Airfoils over Finite Wing of Aerodynamics |
Answer» Right option is (a) TRUE |
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90. |
Is air pressure on the top of the wing is lower than the pressure below the wing?(a) True(b) FalseI had been asked this question in semester exam.The doubt is from Downwash and Induced Drag in section Flow over Airfoils over Finite Wing of Aerodynamics |
Answer» The CORRECT answer is (a) True |
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91. |
For an inviscid, incompressible flow over finite wings, D’Alembert’s paradox occurs.(a) True(b) FalseI got this question by my college professor while I was bunking the class.This interesting question is from Downwash and Induced Drag in chapter Flow over Airfoils over Finite Wing of Aerodynamics |
Answer» Right ANSWER is (B) False |
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92. |
Is down wash is change in direction of lift?(a) True(b) FalseThis question was posed to me during an interview.This intriguing question comes from Downwash and Induced Drag in section Flow over Airfoils over Finite Wing of Aerodynamics |
Answer» The correct ANSWER is (a) True |
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93. |
Induced drag is generated by a component of lift for a finite wing.(a) True(b) FalseThe question was asked by my college director while I was bunking the class.This interesting question is from Downwash and Induced Drag topic in portion Flow over Airfoils over Finite Wing of Aerodynamics |
Answer» The correct answer is (a) True |
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94. |
The airfoil and the wing behave exactly the same way in terms of aerodynamic properties.(a) True(b) FalseI have been asked this question in final exam.I'd like to ask this question from Downwash and Induced Drag in division Flow over Airfoils over Finite Wing of Aerodynamics |
Answer» The correct CHOICE is (b) False |
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