Related InterviewSolutions

• A cambered airfoil is operating with 200N of lift. The velocity of the flow is 500m/s. Determine lift-induced drag by this camber airfoil.(a) 0N(b) 0(c) 0.5(d) 0.5This question was addressed to me during an online interview.Question is taken from Airfoil Selection-3 in division Airfoil and Geometry Selection of Aircraft Design
• Let’s consider we need to design supersonic aircraft then, which type of airfoil should be adopted?(a) Supersonic airfoil(b) Symmetric airfoil(c) Bluff shape(d) Thicker airfoilI got this question by my school teacher while I was bunking the class.The doubt is from Airfoil Selection-3 topic in section Airfoil and Geometry Selection of Aircraft Design
• If taper ratio is T and span is b with surface area as S then the root chord is _____(a) Croot = 2*S / (b*(1+T))(b) Croot = 2*S / (b*(3+T))(c) Croot = 2*S / (2b*(1+T))(d) Croot = 2*S / (1+T)This question was addressed to me during an internship interview.Asked question is from Wing Geometry-1 in section Airfoil and Geometry Selection of Aircraft Design
• A typical wing has aspect ratio of 7 and span of 2m. If taper ratio T = 0.2 then, find the value of root chord.(a) 0.4761m(b) 0.61m(c) 0.81m(d) 0.71cmThis question was posed to me in homework.Question is taken from Wing Geometry-1 in chapter Airfoil and Geometry Selection of Aircraft Design
• Which type of wing planform is shown below?(a) Tapered wing(b) Elliptic wing(c) Rectangular wing(d) Delta wingThis question was posed to me in an internship interview.My doubt is from Wing Geometry-1 topic in division Airfoil and Geometry Selection of Aircraft Design
• A thin airfoil is defined as NACA 0009 is at ɑ = 5°. What is the value of lift curve slope?(a) 2ᴨ per rad(b) 2ᴨ per degree(c) 4 per degree(d) 0.4 per degreeThis question was posed to me during an interview for a job.My query is from Airfoil Selection-2 topic in division Airfoil and Geometry Selection of Aircraft Design
• For high aspect ratio strength of the wing tip vortex is low.(a) True(b) FalseThis question was addressed to me during an online exam.My doubt stems from Wing Geometry-2 topic in chapter Airfoil and Geometry Selection of Aircraft Design
• Wing sweep is used to ____(a) increase critical mach number(b) decrease critical mach number(c) increase lofting(d) increase draftingThe question was asked during an interview.This is a very interesting question from Wing Geometry-2 topic in division Airfoil and Geometry Selection of Aircraft Design
• Canard pusher aircraft uses wing sweep to change location of aerodynamic centre.(a) True(b) FalseThe question was asked in an interview.This key question is from Wing Geometry-2 topic in section Airfoil and Geometry Selection of Aircraft Design
• An aerofoil is operating with flow velocity of 100m/s. Aerofoil is symmetric and is at 0° AOA. Determine lift produced by this aerofoil.(a) 10.5 N(b) 0 N(c) 50 N(d) 100NI have been asked this question during an interview.The question is from Airfoil Selection-1 topic in portion Airfoil and Geometry Selection of Aircraft Design