Consider the wind tunnel shown in Figures 6.7 and 6.8. Atmospheric air enters the system with...
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Consider the wind tunnel shown in Figures 6.7 and 6.8. Atmospheric air enters the system with a pressure and temperature of 14.7 psia, and 80°F, respectively, and has negligible velocity at section 1. The test section has a cross- sectional area of 1 ft2 and operates at a Mach number of 2.5. You may assume that the diffuser reduces the velocity to approximately zero and that final exhaust is to the atmosphere with negligible velocity. The system is fully insulated and there are negligible friction losses. Find: (a) The throat area of the nozzle. (b) The mass flow rate. (c) The minimum possible throat area of the diffuser. (d) The total pressure entering the exhauster at startup (Figure 6.7). (e) The total pressure entering the exhauster when running (Figure 6.8). (f) The hp value required for the exhauster (based on an isentropic compression). Shock EXI XII M>1 M>1 M<I Shock M=1 Test section Test section Static Pressure M-1 Nozzle Diffuser Exhauster Position in Wind Tunnel Figure 6.8 Supersonic tunnel in running condition (with associated pressure variation). M<I -Nozzle Diffuser Exhauster m Position in Wind Tunnel Figure 6.7 Supersonic tunnel at startup (with associated Mach number variation). M-1 Consider the wind tunnel shown in Figures 6.7 and 6.8. Atmospheric air enters the system with a pressure and temperature of 14.7 psia, and 80°F, respectively, and has negligible velocity at section 1. The test section has a cross- sectional area of 1 ft2 and operates at a Mach number of 2.5. You may assume that the diffuser reduces the velocity to approximately zero and that final exhaust is to the atmosphere with negligible velocity. The system is fully insulated and there are negligible friction losses. Find: (a) The throat area of the nozzle. (b) The mass flow rate. (c) The minimum possible throat area of the diffuser. (d) The total pressure entering the exhauster at startup (Figure 6.7). (e) The total pressure entering the exhauster when running (Figure 6.8). (f) The hp value required for the exhauster (based on an isentropic compression). Shock EXI XII M>1 M>1 M<I Shock M=1 Test section Test section Static Pressure M-1 Nozzle Diffuser Exhauster Position in Wind Tunnel Figure 6.8 Supersonic tunnel in running condition (with associated pressure variation). M<I -Nozzle Diffuser Exhauster m Position in Wind Tunnel Figure 6.7 Supersonic tunnel at startup (with associated Mach number variation). M-1
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