

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 Kutta Condition according to the thin airfoil theory is_____(a) γ(c)=0(b) γ(x)=0(c) γ(ξ )=0(d) \(\frac {dz}{dx}\)=0This question was addressed to me in a job interview.I'm obligated to ask this question of The Symmetric Airfoil in division Incompressible Flow over Airfoils of Aerodynamics |
Answer» Right choice is (a) γ(c)=0 |
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52. |
The relation between lift coefficient and moment coefficient about the leading edge is_______(a) cm,le=-(\(\frac {c_l}{2}+\frac {\pi }{4}\)(A1-A2))(b) cm,le=-(\(\frac {c_l}{4}+\frac {\pi }{4}\)(A1-A2))(c) cm,le=-(\(\frac {c_l}{4}\)+(A1-A2))(d) cm,le=(\(\frac {c_l}{2}+\frac {\pi }{4}\)(A1-A2))The question was asked in semester exam.My enquiry is from The Cambered Airfoil in chapter Incompressible Flow over Airfoils of Aerodynamics |
Answer» Correct choice is (B) cm,LE=-(\(\FRAC {c_l}{4}+\frac {\pi }{4}\)(A1-A2)) |
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53. |
What is the thickness of NACA 0002 airfoil?(a) 3%(b) 1%(c) 0%(d) 2%I had been asked this question in exam.My question is based upon The Symmetric Airfoil topic in chapter Incompressible Flow over Airfoils of Aerodynamics |
Answer» The correct choice is (d) 2% |
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54. |
Generation of lift over an airfoil and formation of starting vortex is correctly explained by which of these?(a) Kutta-Joukowski Theorem(b) Kutta Condition and Kelvin’s Theorem(c) Kutta-Joukowski Theorem and Kelvin’s Theorem(d) Kutta Condition and Helmholtz TheoremI got this question in a job interview.The query is from Kelvin’s Circulation Theorem and the Starting Vortex topic in portion Incompressible Flow over Airfoils of Aerodynamics |
Answer» The correct choice is (b) KUTTA CONDITION and Kelvin’s Theorem |
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55. |
How starting vortex is formed?(a) As the airfoil begins to move vortex are formed(b) As the airflows on the airfoil vortex are formed(c) As the airfoil moves against the relative wind vortex are formed(d) As the airflows on the circular body vortex are formedThe question was posed to me in unit test.This intriguing question comes from The Kutta Condition topic in section Incompressible Flow over Airfoils of Aerodynamics |
Answer» Correct option is (a) As the airfoil BEGINS to move vortex are formed |
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56. |
What is a chord?(a) Distance between leading edge and chord(b) Distance between chord and chamber(c) Distance between leading edge and trailing edge(d) Distance between trailing edge and chordThis question was posed to me in an interview for internship.My question is from Airfoil Nomenclature in division Incompressible Flow over Airfoils of Aerodynamics |
Answer» Right answer is (c) DISTANCE between leading EDGE and trailing edge |
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57. |
Is flat vortex sheet with periodic boundaries can be used in high Reynolds number?(a) True(b) FalseThis question was posed to me by my school principal while I was bunking the class.Query is from The Vortex Sheet topic in division Incompressible Flow over Airfoils of Aerodynamics |
Answer» Correct answer is (a) True |
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58. |
Is surface is perturb the boundary layer and promote turbulence?(a) True(b) FalseThe question was asked during an interview.I'm obligated to ask this question of Turbulent Flow in section Incompressible Flow over Airfoils of Aerodynamics |
Answer» Correct option is (a) True |
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59. |
Example of turbulent flow?(a) Smoking rises from cigarette(b) Flow on a symmetric airfoil(c) Laminar flow(d) Turbulent flow on the airfoilI got this question in final exam.The origin of the question is Turbulent Flow topic in chapter Incompressible Flow over Airfoils of Aerodynamics |
Answer» Right OPTION is (a) Smoking RISES from cigarette |
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60. |
Is Reynolds number is used to predict the turbulence?(a) True(b) FalseThis question was addressed to me in an online quiz.My question is taken from Turbulent Flow topic in chapter Incompressible Flow over Airfoils of Aerodynamics |
Answer» The CORRECT answer is (a) True |
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61. |
Is unsteady vortices appears at turbulent flow?(a) True(b) FalseI got this question during a job interview.I'm obligated to ask this question of Turbulent Flow in section Incompressible Flow over Airfoils of Aerodynamics |
Answer» Right option is (a) True |
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62. |
Which of the following is not related to flow separation?(a) Reduction of lift(b) Increased drag(c) Adverse pressure gradients(d) Attached flowThis question was posed to me during a job interview.My enquiry is from Viscous Flow in section Incompressible Flow over Airfoils of Aerodynamics |
Answer» The CORRECT choice is (d) ATTACHED flow |
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63. |
Is pressure coefficient distributions are calculated for flow over an airfoil?(a) True(b) FalseI have been asked this question during an online exam.My enquiry is from Modern Low Speed Airfoils in division Incompressible Flow over Airfoils of Aerodynamics |
Answer» The correct choice is (a) True |
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64. |
Which of the following is a new NACA airfoil?(a) NACA 2212(b) NACA LS (1)-0407(c) NACA 0021(d) Both NACA LS (1)-0407 and NACA 2412I had been asked this question in an interview for internship.Query is from Modern Low Speed Airfoils topic in portion Incompressible Flow over Airfoils of Aerodynamics |
Answer» The correct OPTION is (b) NACA LS (1)-0407 |
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65. |
The standard NACA airfoils were based on ____(a) Computer modeling results(b) Numerical techniques and wind- tunnel testing(c) Experiment data(d) Theoretical dataI have been asked this question in class test.Question is from Modern Low Speed Airfoils topic in division Incompressible Flow over Airfoils of Aerodynamics |
Answer» The correct choice is (c) Experiment data |
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66. |
The lift per unit span for a thin, cambered airfoil with α=5°, A0=0.65, A1=1 is____(a) L’ = cπ\(V_∞^2\)ρ∞ (1.15)(b) L’ = cπ\(V_∞^2\)ρ∞ (1.65)(c) L’ = cπ\(V_∞^2\)ρ∞ (-0.35)(d) L’ = cπ\(V_∞^2\)ρ∞ (0.15)This question was addressed to me in a job interview.The question is from The Cambered Airfoil topic in portion Incompressible Flow over Airfoils of Aerodynamics |
Answer» Correct choice is (a) L’ = cπ\(V_∞^2\)ρ∞ (1.15) |
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67. |
The zero-lift angle of attack for a thin, cambered airfoil increases in magnitude with the increasing camber of the airfoil.(a) True(b) FalseThe question was asked by my school principal while I was bunking the class.This key question is from The Cambered Airfoil topic in division Incompressible Flow over Airfoils of Aerodynamics |
Answer» The correct ANSWER is (a) True |
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68. |
Is thin sheet of intense vorticity is unstable at downstream?(a) True(b) FalseThis question was posed to me during an online exam.My question is from Kelvin’s Circulation Theorem and the Starting Vortex in division Incompressible Flow over Airfoils of Aerodynamics |
Answer» Correct answer is (a) True |
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69. |
Mathematically, what is meant by Kelvin’s Circulation Theorem for an inviscid and incompressible flow? (For the same set of fluid elements moving in a closed curve along with the fluid).(a) DΓ/Dt = 0(b) γ1 ≥ Γ2, where 1 is the upstream direction(c) Γ = -∮C1V.ds(d) Γ = 0The question was asked in homework.The query is from Kelvin’s Circulation Theorem and the Starting Vortex in section Incompressible Flow over Airfoils of Aerodynamics |
Answer» CORRECT ANSWER is (a) DΓ/Dt = 0 To explain: Kelvin’s theorem states that the time rate of change of circulation for a SET of fluid elements in a closed curve moving along the fluid is zero. In other WORDS, circulation remains CONSTANT, not zero. Γ = -∮C1V.ds is the definition of circulation. |
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70. |
It is possible to have lift without friction (i.e. in an inviscid medium).(a) True(b) FalseThe question was asked in an internship interview.My enquiry is from Kelvin’s Circulation Theorem and the Starting Vortex topic in chapter Incompressible Flow over Airfoils of Aerodynamics |
Answer» The CORRECT option is (b) False |
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71. |
Turbine blades are used to extract energy from the high temperatures.(a) False(b) TrueThe question was posed to me in examination.Enquiry is from Airfoil Characteristics topic in division Incompressible Flow over Airfoils of Aerodynamics |
Answer» The correct OPTION is (b) True |
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72. |
Is axial compressor is a compressor that can continuously pressurize gasses?(a) True(b) FalseI have been asked this question in an online quiz.My doubt stems from Airfoil Characteristics in portion Incompressible Flow over Airfoils of Aerodynamics |
Answer» Correct answer is (a) True |
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73. |
What parameter is used to decrease the stall speed?(a) Chord(b) Chord line(c) Camber(d) Camber lineThis question was posed to me in my homework.Question is from Airfoil Nomenclature topic in section Incompressible Flow over Airfoils of Aerodynamics |
Answer» Correct answer is (c) Camber |
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74. |
The transition point for a flow can be found using____(a) Average of Reynolds numbers at leading and trailing edges(b) It is always the mid-chord(c) Hit and trial methods(d) Critical Reynolds numberThe question was posed to me in homework.Origin of the question is Turbulent Flow in portion Incompressible Flow over Airfoils of Aerodynamics |
Answer» The correct option is (d) Critical Reynolds number |
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75. |
A given flow can be laminar all over an airfoil in a real case. Select the correct statement for the assumption given above.(a) Always true(b) Always false(c) True only for symmetric airfoils(d) Depends on the Reynolds numberI have been asked this question in final exam.This key question is from Turbulent Flow topic in section Incompressible Flow over Airfoils of Aerodynamics |
Answer» Right ANSWER is (b) Always false |
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76. |
For a Reynolds number Rec=10×10^5 and chord length 1m, what is the turbulent boundary layer thickness at the trailing edge (in cm)?(a) 0.0216(b) 0.037(c) 2.16(d) 0.37I got this question in quiz.My enquiry is from Turbulent Flow in chapter Incompressible Flow over Airfoils of Aerodynamics |
Answer» Correct ANSWER is (c) 2.16 |
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77. |
Is laminar flow is used to increase the drag and reduce the lift?(a) True(b) FalseI got this question in class test.My query is from Turbulent Flow in portion Incompressible Flow over Airfoils of Aerodynamics |
Answer» Right option is (a) True |
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78. |
The correct formula for the Fourier sine series appearing in the solution of thin airfoil theory is_____(a) An=\(\frac {2}{\pi }\int_0^{\pi }\frac {dz}{dx}\) cosn∅ d∅(b) An=\(\frac {1}{\pi }\int_0^{\pi }\frac {dz}{dx}\) cosn∅ d∅(c) An=\(\frac {2}{\pi }\int_0^{2\pi }\frac {dz}{dx}\) cosn∅ d∅(d) An=α-\(\frac {1}{\pi }\int_0^{\pi }\frac {dz}{dx}\) cosn∅ d∅I had been asked this question in my homework.Query is from The Cambered Airfoil in section Incompressible Flow over Airfoils of Aerodynamics |
Answer» The CORRECT answer is (a) An=\(\frac {2}{\pi }\int_0^{\pi }\frac {dz}{DX}\) cosn∅ d∅ |
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79. |
Is flow separation over the top surface of the airfoil at high angle of attack?(a) True(b) FalseThe question was asked in an interview for internship.This intriguing question comes from Modern Low Speed Airfoils in portion Incompressible Flow over Airfoils of Aerodynamics |
Answer» Correct answer is (a) True |
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80. |
NACA 0023 is______(a) Negatively cambered airfoil(b) Positively cambered airfoil(c) Symmetrical airfoil(d) Thin cambered airfoilThis question was posed to me in my homework.The question is from The Cambered Airfoil in portion Incompressible Flow over Airfoils of Aerodynamics |
Answer» CORRECT choice is (c) Symmetrical airfoil To explain: The first two digits in the NACA nomenclature give the maximum camber and POSITION of maximum camber. For a symmetric airfoil, both of these are zero. |
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81. |
Is supercritical airfoil has flattened upper surface?(a) True(b) FalseI had been asked this question during an internship interview.The question is from The Cambered Airfoil topic in portion Incompressible Flow over Airfoils of Aerodynamics |
Answer» Right option is (a) True |
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82. |
For a flat plate, aerodynamic center and center of pressure coincide.(a) True(b) FalseI have been asked this question in an interview for job.This interesting question is from The Symmetric Airfoil topic in division Incompressible Flow over Airfoils of Aerodynamics |
Answer» Right ANSWER is (a) True |
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83. |
The Kutta condition is not satisfied at the trailing edge where θ=π in transformed coordinates for a symmetrical airfoil.(a) True(b) FalseThe question was asked in a job interview.I would like to ask this question from The Symmetric Airfoil in division Incompressible Flow over Airfoils of Aerodynamics |
Answer» The correct answer is (b) False |
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84. |
Is symmetric airfoil produce positive lift?(a) False(b) TrueThe question was posed to me in a national level competition.The question is from The Symmetric Airfoil in chapter Incompressible Flow over Airfoils of Aerodynamics |
Answer» The correct option is (b) True |
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85. |
Is wake behind the airfoil exhibits a continuous vortex?(a) False(b) TrueI got this question in an online interview.I need to ask this question from The Symmetric Airfoil in chapter Incompressible Flow over Airfoils of Aerodynamics |
Answer» Correct CHOICE is (b) True |
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86. |
How lift is calculated?(a) Perpendicular to the direction of motion(b) Parallel to the direction of motion(c) opposite to the direction of motion(d) relative to the direction of motionThe question was asked in semester exam.This is a very interesting question from The Symmetric Airfoil in division Incompressible Flow over Airfoils of Aerodynamics |
Answer» Correct answer is (a) PERPENDICULAR to the direction of motion |
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87. |
Is fluid flows across the airfoil with a backward facing step?(a) False(b) TrueThe question was asked in final exam.This intriguing question originated from The Symmetric Airfoil topic in division Incompressible Flow over Airfoils of Aerodynamics |
Answer» The correct option is (b) True |
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88. |
Is kelvin established his result subject to weaker conditions?(a) True(b) FalseThe question was asked by my school principal while I was bunking the class.My enquiry is from Kelvin’s Circulation Theorem and the Starting Vortex in portion Incompressible Flow over Airfoils of Aerodynamics |
Answer» The correct OPTION is (a) True |
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89. |
The skin-friction drag coefficient for turbulent flow on the bottom surface of an airfoil, with chord length being 1m is _____ (Reynolds number at the trailing edge Rec=32×10^5)(a) 0.074(b) 0.0037(c) 0.027(d) 0.0074I have been asked this question in semester exam.This intriguing question comes from Turbulent Flow in section Incompressible Flow over Airfoils of Aerodynamics |
Answer» Correct choice is (B) 0.0037 |
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90. |
Is dimensionless Reynolds number is an important parameter?(a) False(b) TrueThe question was posed to me in class test.My question comes from Laminar Flow topic in section Incompressible Flow over Airfoils of Aerodynamics |
Answer» Correct choice is (b) True |
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91. |
The extra term appearing in the thin airfoil theory solution for a cambered airfoil is a______(a) Full Fourier series(b) Fourier sine series(c) Fourier cosine series(d) ConstantThe question was asked in homework.This intriguing question originated from The Cambered Airfoil in portion Incompressible Flow over Airfoils of Aerodynamics |
Answer» The correct answer is (b) Fourier SINE SERIES |
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92. |
Select the unmatched pair.(a) Pressure distribution: lift(b) Shear stress: skin-friction drag(c) Flow separation: form drag(d) Air pressure: pressure dragThis question was posed to me by my college professor while I was bunking the class.This key question is from Viscous Flow in chapter Incompressible Flow over Airfoils of Aerodynamics |
Answer» Right OPTION is (d) Air pressure: pressure drag |
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93. |
Is positive camber upper surface is more convex?(a) True(b) FalseI had been asked this question in a job interview.This intriguing question comes from The Cambered Airfoil topic in chapter Incompressible Flow over Airfoils of Aerodynamics |
Answer» Right choice is (a) True |
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94. |
Select the incorrect statement for a thin, symmetric airfoil out of the following.(a) Quarter-chord is the aerodynamic center(b) Quarter-chord is the center of pressure(c) Moment about quarter-chord depends on the angle of attack(d) Moment about quarter-chord is zeroThis question was addressed to me in an international level competition.Origin of the question is The Symmetric Airfoil topic in division Incompressible Flow over Airfoils of Aerodynamics |
Answer» The correct answer is (c) MOMENT about quarter-chord depends on the angle of attack |
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95. |
How lift and drag ratio can be expressed in a relation?(a) Dividing the lift coefficient by the drag coefficient(b) Dividing the lift coefficient by the moment coefficient(c) Dividing the drag coefficient by the lift coefficient(d) Dividing the drag coefficient by the moment coefficientI had been asked this question by my college director while I was bunking the class.My question is from Airfoil Characteristics topic in chapter Incompressible Flow over Airfoils of Aerodynamics |
Answer» Correct option is (a) Dividing the LIFT coefficient by the drag coefficient |
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96. |
Is flat bottomed wing is more efficient than fully-symmetrical airfoil?(a) True(b) FalseI had been asked this question by my college director while I was bunking the class.The origin of the question is The Symmetric Airfoil topic in section Incompressible Flow over Airfoils of Aerodynamics |
Answer» RIGHT answer is (a) True Explanation: The flat bottomed wing is more EFFICIENT at low SPEEDS than a fully-symmetrical AIRFOIL with an angle of attack LESS, so that the reason most of the flat bottomed, under cambered wing uses less power and drag for the same lift. |
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97. |
For which of the followingKelvin’s theorem is applicable?(a) Flow with Viscous Stresses(b) Compressible Flow(c) Inviscid, Compressible Barotropic Flow(d) Flow with Non-Conservative Body ForcesI had been asked this question in examination.I'd like to ask this question from Kelvin’s Circulation Theorem and the Starting Vortex in division Incompressible Flow over Airfoils of Aerodynamics |
Answer» The CORRECT CHOICE is (c) INVISCID, Compressible Barotropic Flow |
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98. |
What is the thickness in NACA 2412 airfoil?(a) 12%(b) 24%(c) 41%(d) 2%I had been asked this question in exam.The origin of the question is Airfoil Nomenclature topic in section Incompressible Flow over Airfoils of Aerodynamics |
Answer» Right choice is (a) 12% |
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99. |
Who designed the nomenclature of airfoil?(a) NACA series(b) EULAR series(c) EPPLER series(d) CLARK seriesI had been asked this question by my college professor while I was bunking the class.Asked question is from Airfoil Nomenclature in division Incompressible Flow over Airfoils of Aerodynamics |
Answer» Correct option is (a) NACA series |
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100. |
The skin-friction coefficient for turbulent flow Cf is proportional to Rec. The proportionality constant is_____(a) 0.074(b) 0.64(c) 0.33(d) 1.328I had been asked this question in an international level competition.The question is from Turbulent Flow topic in division Incompressible Flow over Airfoils of Aerodynamics |
Answer» Correct choice is (a) 0.074 |
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