Incompressible & Compressible Aerodynamics

(A) NACA 0012 (B) NACA 4415 (C) NACA 23012 (D) None of the above AE 2011 AEROSPACE ENGINEERING - AE AE The aerodynamic centre of a supersonic aerofoil, with chord c, is located at Q.19 (A) the leading edge (B) 0.25c (C) 0.5c (D) 0.75c Winglets are used on wings to minimize Q.20 (A) skin friction drag (B) profile drag (C) wave drag (D) induced drag Consider a potential flow with free stream velocity V∞, over a spinning circular cylinder of radius R and circulation . The stream function, ψ, where ψ = 0 on the cylinder surface, in cylindrical coordinates (r,) is given by (A) R r r Rr V ln21 cos2 2         (B) R r r Rr V ln21 cos2 2        