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
Related questions
Question
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
Expert Solution
This question has been solved!
Explore an expertly crafted, step-by-step solution for a thorough understanding of key concepts.
This is a popular solution!
Trending now
This is a popular solution!
Step by step
Solved in 3 steps with 2 images
Knowledge Booster
Learn more about
Need a deep-dive on the concept behind this application? Look no further. Learn more about this topic, civil-engineering and related others by exploring similar questions and additional content below.Recommended textbooks for you
Structural Analysis (10th Edition)
Civil Engineering
ISBN:
9780134610672
Author:
Russell C. Hibbeler
Publisher:
PEARSON
Principles of Foundation Engineering (MindTap Cou…
Civil Engineering
ISBN:
9781337705028
Author:
Braja M. Das, Nagaratnam Sivakugan
Publisher:
Cengage Learning
Structural Analysis (10th Edition)
Civil Engineering
ISBN:
9780134610672
Author:
Russell C. Hibbeler
Publisher:
PEARSON
Principles of Foundation Engineering (MindTap Cou…
Civil Engineering
ISBN:
9781337705028
Author:
Braja M. Das, Nagaratnam Sivakugan
Publisher:
Cengage Learning
Fundamentals of Structural Analysis
Civil Engineering
ISBN:
9780073398006
Author:
Kenneth M. Leet Emeritus, Chia-Ming Uang, Joel Lanning
Publisher:
McGraw-Hill Education
Traffic and Highway Engineering
Civil Engineering
ISBN:
9781305156241
Author:
Garber, Nicholas J.
Publisher:
Cengage Learning