6PaPo(-)6M,(M+S)Egn. 357MActivity No. 1Title: Pressure, Density, Temperature, and Mach Number Changes Across a Normal Shock WaveExplanation of TableColumn No.:, M, given27M-1R63P6M,P M₁ +5T (7M-1M+S)a¹.T₂36M,5. M.M.(M₁² + 5) ²7M-10M₁1.01.11.21.31.41.51.65.0Reniten(2)"//R.Solve in 3decimalplacesSURM(3P:/Solve in 3decimalplaces52½Solve in 3decimalplacesPacket(5)M₂Solve in 2decimalplaces

It is asked to calculate the pressure, Density, temperature and match number changes across a…

Activity No. 1 Title: Pressure, Density. Temperature, and Mach Number Changes Across a Normal Shock Wave Explanation of Table Column No.: D. M, given P 7M-1 (2), R 6 6M, AM₁ +5 T (7M-1XM+5) 4 7₁ 36M, 5 M₂ 7M,

Activity No. 1 Title: Pressure, Density. Temperature, and Mach Number Changes Across a Normal Shock Wave Explanation of Table Column No.: D. M, given P 7M-1 (2), R 6 6M, AM₁ +5 T (7M-1XM+5) 4 7₁ 36M, 5 M₂ 7M,

Elements Of Electromagnetics

7th Edition

ISBN:9780190698614

Author:Sadiku, Matthew N. O.

Publisher:Sadiku, Matthew N. O.

ChapterMA: Math Assessment

Section: Chapter Questions

Problem 1.1MA

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Question

6
Pa
Po
(-)
6M,
(M+S)
Egn. 35
7M
Activity No. 1
Title: Pressure, Density, Temperature, and Mach Number Changes Across a Normal Shock Wave
Explanation of Table
Column No.:
, M, given
27M-1
R
6
3P
6M,
P M₁ +5
T (7M-1M+S)
a
¹.
T₂
36M,
5. M.
M.
(M₁² + 5) ²
7M-1
0
M₁
1.0
1.1
1.2
1.3
1.4
1.5
1.6
5.0
Reniten
(2)
"//R.
Solve in 3
decimal
places
SURM
(3
P:/
Solve in 3
decimal
places
52
½
Solve in 3
decimal
places
Packet
(5)
M₂
Solve in 2
decimal
places

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Activity No. 1 Title: Pressure, Density, Temperature, and Mach Number Changes Across a Normal Shock Wave Explanation of Table Column No.: 1, M₁ given S (2), P7M₁-1 R 6 6M,² M₂² +5 (7M,'-1XM, +5) 36M, M₁² +5 7M-1 P₂ P T. T₁ 5 M₂
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Air flows from a tank through a nozzle into the standardatmosphere, as in Fig. A normal shock stands in theexit of the nozzle, as shown. Estimate (a) the pressure inthe tank and (b) the mass flow.
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3:34 ull Q3.pdf Q1) Air at mach number 2 , pressure 0.5* 10° N/m² and a temperature of 0 °C , over a wedge and generation of an oblique shock wave 40° . determine : 1. Static pressure and temperature downstream the shock. 2. The mach number of the flow downstream the shock. 3. The wedge angle. *********** Q2) As shown in figure (1) A mach number 2.4 air stream at oblique shock angle of (B1-2 =30°) of incident shock with turning angle (0=10°). determine : 1. the mach number of the flow upstream the reflected shock. 2. the mach number of the flow downstream the reflected shock. M2 M3 Figure (1)
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