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. %3! 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 10(144) 53.3(559.7) Ро Po = 0.0483 lbm/ft RT. co = 49.1VT, = 49.1V559.7 1162 ft/sec %3D

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. %3! 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 10(144) 53.3(559.7) Ро Po = 0.0483 lbm/ft RT. co = 49.1VT, = 49.1V559.7 1162 ft/sec %3D

Structural Analysis

6th Edition

ISBN:9781337630931

Author:KASSIMALI, Aslam.

Publisher:KASSIMALI, Aslam.

Chapter2: Loads On Structures

Section: Chapter Questions

Problem 1P

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