Which of these factors contribute to additional total pressure losses inside the oblique shock diffuser?(a) Abrupt change of convergent – divergent sections(b) Shock wave interaction with walls(c) Isentropic flow(d) Presence of normal shockThe question was posed to me at a job interview.The query is from Compressible Flow through Diffusers topic in division Compressible Flow through Nozzles, Diffusers and Wind Tunnels of Aerodynamics

Which of these factors contribute to additional total pressure losses

1.	Which of these factors contribute to additional total pressure losses inside the oblique shock diffuser?(a) Abrupt change of convergent – divergent sections(b) Shock wave interaction with walls(c) Isentropic flow(d) Presence of normal shockThe question was posed to me at a job interview.The query is from Compressible Flow through Diffusers topic in division Compressible Flow through Nozzles, Diffusers and Wind Tunnels of Aerodynamics
Answer» Right answer is (b) Shock WAVE interaction with walls The explanation is: In real life, oblique shock DIFFUSERS have viscous flow. The presence of shock waves inside the diffuser leads to interaction with the viscous boundary layer of the diffuser walls which leads to additional pressure losses. There’s also friction involved which makes oblique shock diffusers far from the IDEAL diffusers which have no total pressure losses.

Discussion

No Comment Found

Related InterviewSolutions

In case of flow inside a nozzle, how should the exit pressure be in relation to the inlet pressure?(a) Exit pressure = Inlet pressure(b) Exit pressure > Inlet pressure(c) Exit pressure < Inlet pressure(d) There is no relation between the two pressuresThe question was posed to me in quiz.My question comes from Governing Equations for Quasi One Dimensional Flow topic in section Compressible Flow through Nozzles, Diffusers and Wind Tunnels of Aerodynamics
What is the ratio of throat area of diffuser to nozzle in supersonic wind tunnel with flow at Mach 2.7?(a) 0.4236(b) 0.8338(c) 2.36(d) 1.199I have been asked this question in class test.My question is taken from Supersonic Wind Tunnels topic in chapter Compressible Flow through Nozzles, Diffusers and Wind Tunnels of Aerodynamics
What is the relation between the entry and exit entropy of an actual supersonic diffuser?(a) s1 = s2(b) s1 > s2(c) s1 < s2(d) s1 s2 = 1The question was asked in exam.Asked question is from Compressible Flow through Diffusers topic in portion Compressible Flow through Nozzles, Diffusers and Wind Tunnels of Aerodynamics
Why is ideal supersonic diffuser not feasible?(a) Presence of shock waves(b) Varying cross – sectional area(c) Varying throat area(d) Choked flowI got this question in an international level competition.My doubt stems from Compressible Flow through Diffusers topic in portion Compressible Flow through Nozzles, Diffusers and Wind Tunnels of Aerodynamics
Normal shock diffuser is more efficient than the oblique shock diffuser.(a) True(b) FalseI got this question in an internship interview.My doubt stems from Compressible Flow through Diffusers topic in chapter Compressible Flow through Nozzles, Diffusers and Wind Tunnels of Aerodynamics
Which of these conditions is not applicable for choked flow?(a) The Mach number at the throat is zero(b) Mass flow is constant(c) Exit pressure is lower than inlet pressure(d) Exit pressure is same as the inlet pressureThis question was addressed to me in a job interview.My question comes from Governing Equations for Quasi One Dimensional Flow in section Compressible Flow through Nozzles, Diffusers and Wind Tunnels of Aerodynamics
In how many categories is the supersonic wind tunnel classified into?(a) 2(b) 3(c) 4(d) 6This question was addressed to me in unit test.The above asked question is from Supersonic Wind Tunnels topic in chapter Compressible Flow through Nozzles, Diffusers and Wind Tunnels of Aerodynamics
What is the relation between the nozzle A1t and diffuser throat area A2t in the supersonic wind tunnel?(a) At2 = At1(b) At2 > At1(c) At2 < At1(d) At2 At1 = 1The question was asked by my college professor while I was bunking the class.My question is taken from Supersonic Wind Tunnels topic in chapter Compressible Flow through Nozzles, Diffusers and Wind Tunnels of Aerodynamics
How is the flow compressed in an ideal supersonic wind tunnel inside a diffuser?(a) Isentropic(b) Adibatic(c) Isochoric(d) IsobaricThe question was asked by my college director while I was bunking the class.The origin of the question is Compressible Flow through Diffusers topic in chapter Compressible Flow through Nozzles, Diffusers and Wind Tunnels of Aerodynamics
In reality what happens due to the interaction of the oblique shock waves with the boundary layer on the walls of the diffuser?(a) Higher total pressure loss(b) Reduction of speed(c) Total pressure increase(d) Reduced skin friction dragThis question was posed to me in an online quiz.I need to ask this question from Supersonic Wind Tunnels in chapter Compressible Flow through Nozzles, Diffusers and Wind Tunnels of Aerodynamics

Discussion

No Comment Found

Related InterviewSolutions

Reply to Comment