problem1)(a) State the Prandtl Glauert’s rule and derive the expressions for the coefficients of pressure, lift and moment. In a low speed in compressible flow, the peak coefficient of pressure of an NACA 0009 airfoil is -0.25. Estimate the critical Mach number for this airfoil using Prandt’l Glauret’s rule.
b) prepare about quasi-one-dimensional flow. Air flowing in a duct has a velocity of 300 m/s, pressure 1.0 bar and temperature 290 K taking=1.4, R=287 J/kgK. Determine
(a) Stagnation pressure and temperature
(b) Velocity of sound in the dynamic and stagnation conditions.
(c) Stagnation pressure assuming constant density.
problem 2)a) A supersonic flow with Mach number 2.8 and pressure of 1 atm is deflected through an angle such that the Mach number behind the shock is 1.45. Find the angle of deflection and the pressure behind the shock.
b) What is a supercritical airfoil? How is it useful in increasing the drag divergence Mach number?
c) describe the term area rule. How does it affect the performance of an airplane?
problem 3)a) For the flow field shown in figure 3 determine β_{r}, M_{2} and M_{3} if M_{1} = 2.0 for β_{i} = 400.
b) describe what you understand by linearization.
problem 4)a) Derive velocity potential equation for a two-dimensional, steady, irrotational, isentropic flow.
b) Argon is stored in a reservoir at 300K ; Determine stagnation enthalpy and velocity of sound in it =1.658 and the molecular weight of argon is 39.94.
problem 5)a) At a given point in a flow T = 300 K, P = 1.2 atm and V = 250 m/s. At this point find out the corresponding values of P_{o}, To, P*, T* and M*.
b) The flow just upstream of a normal shock is given by P_{1} = 1 atm, T_{1} = 288 K and M_{1} = 2.6. find out the following properties at downstream of shock: P_{2}, T_{2}, ρ_{2}, M_{2}, P_{o2} and T_{o2}.
problem 6)a) Consider a supersonic flow with M = 2, P = 1 atm, T = 288 K. This flow is deflected at a compression corner through 20º. find out M, P, T, Po and To behind the resulting shock wave. Take the wave angle to be 53.4º.
b) A supersonic flow with M_{1} = 1.5, P_{1} = 1 atm and T_{1} = 288 K is expanded around a sharp corner through a deflection angle of 15º. find out M_{2}, P_{2}, T_{2}, P_{o2} and T_{o2}. Use the Prandtl-Meyer function and Mach number chart here.