Can you please do this question correctly,thanks!!
Can you please do this question correctly,thanks!! 183 184Question 2.6 Air is flowing at supersonic speed over a two-dimensional wedge with an upstream static pressure, P, and static temperature, T,...
Question 2.8 Refering to the figure below, a supersonic flow with upstream Mach number, M, static pressure, pi, and static temperature, Ti, as specified in the table below, encounters a corner with a turning angle ore Determine the angle of the oblique shock, ?, the angle of the reflected wave, q, the Mach numbers M2 and M, and the downstream static pressure Ps and static temperature Ty Mi P1 M3 P3 T3 Design Data Value Unit Mach number (M) Static...
Question 2.10 A two-dimensional wedge-shaped airfoil, with chord, c, consists of straight-line segments with wedge angles, θ¡et and θaf, at the leading and trailing edges, as defined in the figure and given in the table below. The airfoil operates at an angle of attack, α, and it is moving through air at a supersonic speed, M. The atmospheric temperature and pressure far upstream of the airfoil are T and p as specified in the table The various flow regions are...
2. Find the Mach number and air speed corresponding of 500 kPa(abs) in an air flow with a (static) pressure of 100 kPa and measured (stagnation) temperature of 500 K. DISCUSSION: Suppose that, instead of assuming that a normal shock occurs upstream of the Pitot tube, it is assumed that the flow upstream is ISENTROPIC... what would the estimated flow speed be in that case? (NOTE: A normal shock is always observed to form upstream of bluff bodies such as...
Can you please do this question correctly. Thanks!! 08 Question 2.7 Two possibilities are considered for the design of a two-dimensional jet engine inlet as shown in the figures (a-b) below. The inlet is to operate at the Mach number Mi, shown in the table below. In the first design configuration, shown in figure (a), the deceleration of the flow takes place through a normal shock. For the second case, shown in figure (b), a wedge-shaped diffuser is used to...
Problem 4 (15%) A supersonic wind tunnel operates with air at the total pressure Pt temperature Te 420K, and Mach number M 2.0. 420kPa absolute, total a) (10%) Calculate the temperature and the pressure in the test section (where M 2.0 occurs). T1 = kPa (5%) if a normal shock wave occurs in the test section, calculate the temperature and pressure after the shock wave. b) kPa
Can you please help me with part (e), thanks! A B 72 Question 1.4 A convergent-divergent nozzle is designed to operate with isentropic flow with an exit Mach number, Me. The flow in the nozzle is supplied from a reservoir of air with a static pressure of PR and a static temperature of TR and the nozzle has a throat area, AT, as specified in the table below 73 Design Data Value Unit 75 Exit Mach number (ME) 76 77...