c) A nozzle in a wind tunnel gives a test-section Mach number of 2.0. Alr etes th nozzle from a large reservoir at 0,69 bar and 310 K. The cross-sectional area of the throat is 1000 cm2. Determine...
ANSWER [0.54 and 1.63] (b) Air flows through a converging-diverging nozzle. At point "A" in the converging section, the cross-sectional area is 50 cm2 and the Mach number was measured to be 0.4. At point "B" in the diverging section, the cross-sectional area is 40 cm2. Find the possible Mach numbers at point "B" Assume that the flow is isentropic and the air specific ratio γ-1.4 and the gas constant R: 287 J/kg K. (b) Air flows through a converging-diverging...
(4 Marks/Markah) b) A supersonic wind tunnel nozzle is to be designed for Mach number, Ma = 2.5 with a test section I m' in area as shown in Figure 2. The supply pressure and the temperature at the nozzle inlet, where the velocity is negeligible, are 8 x 10° Pa and 27Crespectively. The preliminary design is to be based on the assumptions that the flow is isentropic, with k =1.4, R = 287 Jkg.K, and that the flow is...
A blow down supersonic wind tunnel has a test section area of 0.2 m2 and a design Mach number of 2.5. The pressure and temperature in the high pressure air tank is 50 MPa and 400 K. Ignore all losses between the high pressure tank and the test section. a) Estimate the throat area of the nozzle. b) Estimate the static pressure and static temperature in the test section. c) Estimate the required gas temperature in the high pressure tank...