Aersp_312_HW_No_7

# Aersp_312_HW_No_7 - Aerospace 312 Homework No 7 Assigned...

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Aerospace 312 Homework No 7 Assigned: April 16, 2010 D. K. McLaughlin Due: April 23, 2010 Problem: Given two configurations of a supersonic wind tunnel shown in the attached figure. This project will give you some practice working with isentropic compressible flows, normal and oblique shock waves and the workings of a supersonic wind tunnel. The ultimate goal of this problem is to compute the inlet to outlet stagnation pressure ratio for the two versions of supersonic wind tunnel. This ratio is a measure of the pumping power that is required to operate the tunnel. In it’s present configuration the cross sectional areas of the first throat and the test section are given as: 500 and 843.5 cm 2 respectively. The air in the upstream settling chamber has been heated to 100 C, and for this calculation you can assume that the pressure in the settling chamber is 30 psig. Configuration a). In this configuration the control of supersonic flow in the test section is maintained by the normal shock wave in the expanding section downstream of the test section. For this calculation

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Aersp_312_HW_No_7 - Aerospace 312 Homework No 7 Assigned...

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