Related InterviewSolutions

• Hypersonic similarity is applicable for only irrotational flow.(a) True(b) FalseThe question was posed to me in quiz.The query is from Hypersonic Similarity in section Transonic and Hypersonic Flows of Aerodynamics
• For which range of values is the hypersonic similarity rule valid for very slender bodies?(a) K = 0.5 to infinity(b) K > 1.5(c) 0.5 < K < 1.5(d) 2 < K < 1000I got this question in semester exam.Question is taken from Hypersonic Similarity in portion Transonic and Hypersonic Flows of Aerodynamics
• The ratio \(\frac {C_p}{τ^{2}}\) behind a shock wave is a function of which of these parameters?(a) Hypersonic similarity parameter K and γ(b) Angle of attack and wedge angle(c) Coefficient of lift and wedge angle(d) Hypersonic similarity parameter and angle of attackThis question was addressed to me in semester exam.Question is taken from Hypersonic Similarity in chapter Transonic and Hypersonic Flows of Aerodynamics
• Which of these does not result in two or more flows being dynamically similar?(a) Streamlines are geometrically similar(b) The shape of the blunt body is same(c) Length of the body is same(d) Non dimensional parameters remain sameThis question was posed to me in an interview for job.My doubt stems from Hypersonic Similarity topic in chapter Transonic and Hypersonic Flows of Aerodynamics
• For which of these Mach numbers is flow considered to be hypersonic?(a) M < 1(b) M = 1(c) M > 5(d) 1 < M < 5The question was posed to me at a job interview.I need to ask this question from Hypersonic Flow topic in division Transonic and Hypersonic Flows of Aerodynamics
• On which of this parameter is the coefficient of lift over a two – dimensional body at hypersonic flow dependent?(a) γ.\(\frac {α}{τ}\)(b) γ, K, M∞(c) M∞T, \(\frac {α}{τ}\), γ(d) M∞T, K, γI have been asked this question in quiz.I'm obligated to ask this question of Hypersonic Similarity topic in chapter Transonic and Hypersonic Flows of Aerodynamics
• What is viscous interaction?(a) Interaction between viscous flow and boundary layer(b) Interaction between inviscid flow and boundary layer(c) Interaction between shock wave and inviscid flow(d) Interaction between shock wave and viscous flow inside boundary layerThe question was asked in unit test.My doubt is from Hypersonic Flow topic in portion Transonic and Hypersonic Flows of Aerodynamics
• Which of these surfaces is used for reentry vehicles at hypersonic speed?(a) Aluminum(b) Carbon(c) Ablative surface(d) CopperI had been asked this question in an online quiz.I need to ask this question from Hypersonic Flow in portion Transonic and Hypersonic Flows of Aerodynamics
• Boundary condition V.n = 0 is applied at the surface to non dimensionlize the governing equations when fluid is being transferred.(a) True(b) FalseI have been asked this question in an interview for job.Query is from Mach Number Independence in section Transonic and Hypersonic Flows of Aerodynamics
• Mach number independence for conical cylinder is achieved at a lower Mach number compared to the sphere.(a) True(b) FalseThe question was posed to me in final exam.This key question is from Mach Number Independence topic in section Transonic and Hypersonic Flows of Aerodynamics