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
Chapter2: Loads On Structures
Section: Chapter Questions
Problem 1P
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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
10(144)
53.3(559.7)
Ро
Po
= 0.0483 lbm/ft*
RT.
co = 49.1VT,
= 49.1V559.7
1162 ft/sec
%3D](/v2/_next/image?url=https%3A%2F%2Fcontent.bartleby.com%2Fqna-images%2Fquestion%2F89fdefb3-60e2-4830-b4ac-d28bc0267c11%2F4619a1b0-8ecc-4cf0-9320-67209c7a07a4%2Fyunx7jq_processed.jpeg&w=3840&q=75)
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
10(144)
53.3(559.7)
Ро
Po
= 0.0483 lbm/ft*
RT.
co = 49.1VT,
= 49.1V559.7
1162 ft/sec
%3D
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