Following diagram represents _______(a) lift curve slope vs mach number(b) drag polar(c) thrust required minimum(d) wing loading chartThe question was posed to me in an interview for internship.The doubt is from Aerodynamics in section Aerodynamics of Aircraft Design

Following diagram represents _______(a) lift curve slope vs mach numbe

1.	Following diagram represents _______(a) lift curve slope vs mach number(b) drag polar(c) thrust required minimum(d) wing loading chartThe question was posed to me in an interview for internship.The doubt is from Aerodynamics in section Aerodynamics of Aircraft Design
Answer» Correct ANSWER is (a) lift curve slope vs mach number Easiest explanation: The above diagram is showing a TYPICAL variation between lift curve and Mach number. Drag polar is nothing but the drag variation with lift or angle of ATTACK. It is used to ESTIMATE drag properties of airfoil and WING. Wing loading is defined as the ratio of weight to the reference area.

Discussion

No Comment Found

Related InterviewSolutions

Aerodynamic forces are generated due to ______________(a) shear and pressure force acting on body(b) shear effects only(c) only pressure forces(d) twisting of beamThe question was asked in exam.My doubt stems from Aerodynamic Forces topic in division Aerodynamics of Aircraft Design
For ideal flow, total pressure along streamline will be _________(a) constant(b) increases(c) decreases(d) always decreases by halfThis question was posed to me in class test.I would like to ask this question from Aerodynamic Forces topic in division Aerodynamics of Aircraft Design
Increment in the skin friction drag due to prop-wash is called _________(a) scrubbing drag(b) vortex(c) swirl(d) curling flowThe question was asked during an online interview.Asked question is from Aerodynamic Forces in portion Aerodynamics of Aircraft Design
If static air pressure is 0.5 bar and dynamic pressure is 0.85 bar then, find total pressure acting on a body.(a) 1.35(b) 5(c) 7(d) 8.56I had been asked this question by my school principal while I was bunking the class.My doubt stems from Aerodynamic Forces topic in section Aerodynamics of Aircraft Design
Consider an incompressible flow. If static pressure increases then, the local freestream velocity __________(a) decreases(b) increase(c) remains same(d) insufficient dataI had been asked this question during a job interview.Query is from Aerodynamic Forces topic in portion Aerodynamics of Aircraft Design
For an incompressible flow, if local area velocity decreases then, the dynamic pressure will ________(a) decrease(b) increase(c) constant(d) independent of velocityThis question was posed to me in final exam.I'd like to ask this question from Aerodynamic Forces topic in division Aerodynamics of Aircraft Design
Skin friction drag is defined as _________(a) drag due to friction between skin and fluid flow(b) wing lift drag(c) such drag does not exist(d) lift inducedThe question was asked in quiz.I need to ask this question from Aerodynamic Forces in chapter Aerodynamics of Aircraft Design
Following diagram represents __________(a) plain flap(b) aileron(c) rudder(d) spoilerThe question was asked in exam.My question is taken from Aerodynamics in section Aerodynamics of Aircraft Design
_______ is one of the sources of drag.(a) Viscous separation(b) Drafting(c) Signal strength(d) Lift onlyThis question was posed to me in an online quiz.This interesting question is from Aerodynamic Forces in chapter Aerodynamics of Aircraft Design
For a symmetrical airfoil drag coefficient at zero lift is 0.05 and induced drag coefficient is 0.0025. Find the total drag coefficient.(a) 0.0525(b) 0.45(c) 5.25(d) 52.5This question was addressed to me in unit test.I need to ask this question from Aerodynamic Coefficients in division Aerodynamics of Aircraft Design

Following diagram represents _______(a) lift curve slope vs mach number(b) drag polar(c) thrust required minimum(d) wing loading chartThe question was posed to me in an interview for internship.The doubt is from Aerodynamics in section Aerodynamics of Aircraft Design

Discussion

No Comment Found

Related InterviewSolutions

Reply to Comment