B4 (a) Ste the parameter that is normally used to differentiate between incompressible and compressible flow conditions. What value is normally chosen for this parameter to signify a change from one...
Poblem Comergini sentropie regim (no shock waves) Consider isentropic flow through a converging-diverging nozzle. The exit area of the nozzle is , and the throat area of the nozzle is . The air entering the nozzle has stagnation conditions: , and Use Figure D.1 or Table D (a) Calculate the mass flow rate for choked flow (that is, sonic flow at the throat). Hints: See Section 11.7, use Figure D.1 to find density and temperature at M 1 (throat), find...
Assume air is entering a converging-diverging nozzle with subsonic speed. What are the possible flow conditions at the throat of the converging-diverging nozzle? (circle all correct answers and assume friction is negligible in the nozzle). a. Subsonic flowb. Supersonic flowc. Sonic flow
Q6 (a) Explain briefly the different between incompressible and compressible fluid flow (5 marks) (6) Air at pressure and temperature of 200 kPa, 373.2 K flows through a duct at Mach Number of 0.8. The gas constant and specific heat ratio of air are 0.287 kJ/kg k, 1.4 respectively. Determine, (1) air velocity: (11) stagnation pressure: (111) stagnation temperature and (iv) stagnation density (8 marks) Nitrogen enters a converging diverging nozzle from a reservoir at a pressure of 700 kPa...
Fundamentals-of-Compressible-Fluid-Dynamics Balachandran CHAPTER 4 6. A conical diffuser of 15 cm has an area ratio of 4. If the pressure, temperature and velocity at the inlet section are 0.69 bar, 340 K and 180 m/s, estimate the exit pressure and exit velocity. What will be the change in impulse function. [Ans. p2 = 0.8074 bar; V2 = 45 m/s; F2 - F1 = 4167.5 N] 7. The Mach number at inlet and exit of a supersonic diffuser are 3 and...