Related InterviewSolutions

• What is the flow over right circular cone at zero angle of attack is considered to be?(a) One – dimensional(b) Quasi three – dimensional(c) Three – dimensional(d) Quasi two – dimensionalThis question was posed to me in exam.The above asked question is from Quantitative Formulation in division Linearized and Conical Flows of Aerodynamics
• Thicker the airfoil, higher is the critical Mach number.(a) True(b) FalseI got this question in an online quiz.My question is from Critical Mach Number in chapter Linearized and Conical Flows of Aerodynamics
• The linearized perturbation velocity potential equation for supersonic flow takes form of which of these partial differential equations?(a) Elliptic(b) Hyperbolic(c) Parabolic(d) LinearI got this question in a national level competition.This question is from Linearized Supersonic Flow topic in section Linearized and Conical Flows of Aerodynamics
• What is the surface boundary condition for a thin airfoil at a subsonic flow? (Where shape of the airfoil is represented as y = f(x))(a) \(\frac {∂ϕ}{∂x}\) = V∞ \(\frac {df}{dx}\)(b) \(\frac {∂ϕ}{∂y} = \frac {df}{dy}\)(c) \(\frac {∂ϕ}{∂x}\) = – V\(_∞^2 \frac {df}{dx}\)(d) \(\frac {∂ϕ}{∂x} = \frac {dV_∞}{dx}\)I got this question in exam.My question comes from Linearized Subsonic Flow in division Linearized and Conical Flows of Aerodynamics
• Which of these assumptions is invalid for the linearized velocity potential equation?(a) \(\frac {u^{‘}}{V_∞}\) 1(d) \(\frac {w^{‘}}{V_∞}\)
• Linearized pressure distribution for higher deflection angle is inaccurate.(a) True(b) FalseThis question was addressed to me by my school principal while I was bunking the class.I'd like to ask this question from Linearized Pressure Coefficient in chapter Linearized and Conical Flows of Aerodynamics
• If a cone with half angle 30.2 degrees is kept in a flow at Mach number 3.5, then what is the value of Mach number downstream of the shockwave?(a) 1.110(b) 2.482(c) 1.648(d) 3.45I had been asked this question during an internship interview.Question is taken from Physical Aspects of Conical Flow topic in portion Linearized and Conical Flows of Aerodynamics
• Where does the flow remain supersonic in a conical surface?(a) Between the oblique shock and the sonic line(b) Between the oblique shock and the conical surface(c) Between the sonic line and the conical surface(d) Flow is not supersonic beyond the oblique shockThis question was addressed to me in an internship interview.I would like to ask this question from Physical Aspects of Supersonic Flow over Cones in division Linearized and Conical Flows of Aerodynamics
• For a given cone angle and freestream Mach number, how many oblique shock(s) is/are present?(a) 1(b) 2(c) 4(d) InfinityThe question was asked in homework.My question is based upon Physical Aspects of Supersonic Flow over Cones topic in portion Linearized and Conical Flows of Aerodynamics
• What is the irrotationally condition for a conical flow?(a) Vθ = \(\frac {∂(V_r )}{∂θ}\)(b) Vϕ = \(\frac {∂(V_r )}{∂ϕ}\)(c) Vθ = \(\frac {1}{r} \frac {∂(V_θ )}{∂θ}\)(d) Vθ = \(\frac {∂(V_r )}{∂θ}\)VrI have been asked this question in an interview.This interesting question is from Quantitative Formulation in division Linearized and Conical Flows of Aerodynamics