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PROBLEM. A supersonic wind-tunnel nozzle is to be designed for M = 2, with a throat section 1 sq ft in area. The supply pressure and temperature at the nozzle inlet, where the velocity is negligible, are 10 psia and 100°F, respectively. The preliminary design is to be based on the assumptions that the flow is isentropic, with k 1.4, and that the flow is one-dimensional at the throat and test section. It is desired to compute the mass flow, the test-section area, and the fluid properties at the throat and test section. Table B.2 is to be used. First we work out the reference stagna- 559.7°R. tion properties. We are given po = 10 psia and T, From these we compute = 459.7 + 100 =

PROBLEM. A supersonic wind-tunnel nozzle is to be designed for M = 2, with a throat section 1 sq ft in area. The supply pressure and temperature at the nozzle inlet, where the velocity is negligible, are 10 psia and 100°F, respectively. The preliminary design is to be based on the assumptions that the flow is isentropic, with k 1.4, and that the flow is one-dimensional at the throat and test section. It is desired to compute the mass flow, the test-section area, and the fluid properties at the throat and test section. Table B.2 is to be used. First we work out the reference stagna- 559.7°R. tion properties. We are given po = 10 psia and T, From these we compute = 459.7 + 100 =

Elements Of Electromagnetics
Elements Of Electromagnetics
7th Edition
ISBN:9780190698614
Author:Sadiku, Matthew N. O.
Publisher:Sadiku, Matthew N. O.
ChapterMA: Math Assessment
Section: Chapter Questions
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PROBLEM. A supersonic wind-tunnel nozzle is to be designed for M = 2, with a throat section 1 sq ft in area. The supply pressure and temperature at the nozzle inlet, where the velocity is negligible, are 10 psia and 100°F, respectively. The preliminary design is to be based on the assumptions that the flow is isentropic, with k = 1.4, and that the flow is one-dimensional at the throat and test section. It is desired to compute the mass flow, the test-section area, and the fluid properties at the throat and test section. Table B.2 is to be used. First we work out the reference stagna- tion properties. We are given po = 10 psia and To = 459.7 + 100 = 559.7°R. From these we compute Po Po = RT. 10(144) 53.3(559.7) 0.0483 lbm/ft Co 49.1VT. = 49.1V559.7 = 1162 ft/sec %3D
Transcribed Image Text:PROBLEM. A supersonic wind-tunnel nozzle is to be designed for M = 2, with a throat section 1 sq ft in area. The supply pressure and temperature at the nozzle inlet, where the velocity is negligible, are 10 psia and 100°F, respectively. The preliminary design is to be based on the assumptions that the flow is isentropic, with k = 1.4, and that the flow is one-dimensional at the throat and test section. It is desired to compute the mass flow, the test-section area, and the fluid properties at the throat and test section. Table B.2 is to be used. First we work out the reference stagna- tion properties. We are given po = 10 psia and To = 459.7 + 100 = 559.7°R. From these we compute Po Po = RT. 10(144) 53.3(559.7) 0.0483 lbm/ft Co 49.1VT. = 49.1V559.7 = 1162 ft/sec %3D
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