Air flows isentropically. Using the below table and find the divergent exit temperature, and pressure. Using equations to find the exit area at Ma = 2. Throat Ma = 0.4 A=0.2 m2 Ma = 2 P=1 Mpa atm T=300 K TABLE A-13 One-dimensional isentropic compressible flow functions for an ideal gas with k- 1.4 Ma Ma ANA PIP plpo TIT TABLE 12-2 The critical-pressure, critical-temperature, and çritical-density ratios for isentropic flow of some ideal gases 1.0000 0.9930 0.9725 0.9395 0.8956 0.8430 0.7840 0.7209 0.6560 1.0000 0.9950 0.9803 0.9564 0.9243 0.8852 0.8405 1.0000 0.9980 0.9921 0.9823 0.9690 0.9524 0.9328 0.9107 0.8865 0.1094 0.2182 0.3257 0.4313 0.5345 0.6348 0.7318 0.8251 0.9146 1.0000 1.1583 1.2999 1.4254 1.5360 1.6330 1.7179 1.7922 5.8218 2.9635 2.0351 1.5901 1.3398 1.1882 0.1 0.2 0.3 0.4 0.5 0.6 0.7 0.8 0.9 1.0 1.2 1.4 1.6 1.8 2.0 2.2 Monatomic Superheated steam, k-1.3 Hot products of combustion, k- 1.33 Air, gases, k-1.667 k- 1.4 0.5457 0.5404 0.5283 0.4871 1.0944 1.0382 1.0089 1.0000 1.0304 1.1149 1.2502 1.4390 0.7916 0.7400 0.6870 0.6339 0.5311 0.4374 0.3557 0.2868 0.2300 0.1841 0.8696 0.8584 0.8333 0.7499 0.5913 0.5283 0.4124 0.3142 0.2353 0.1740 0.1278 0.0935 0.0684 0.8606 0.8333 0.7764 0.7184 0.6614 0.6068 0.5556 0.5081 0.6276 0.6295 0.6340 0.6495 Po A 10+1M120k-1)] A* k + 2 1.6875 2.0050 2.4031 2.4 0.1472 0.4647
Air flows isentropically. Using the below table and find the divergent exit temperature, and pressure. Using equations to find the exit area at Ma = 2. Throat Ma = 0.4 A=0.2 m2 Ma = 2 P=1 Mpa atm T=300 K TABLE A-13 One-dimensional isentropic compressible flow functions for an ideal gas with k- 1.4 Ma Ma ANA PIP plpo TIT TABLE 12-2 The critical-pressure, critical-temperature, and çritical-density ratios for isentropic flow of some ideal gases 1.0000 0.9930 0.9725 0.9395 0.8956 0.8430 0.7840 0.7209 0.6560 1.0000 0.9950 0.9803 0.9564 0.9243 0.8852 0.8405 1.0000 0.9980 0.9921 0.9823 0.9690 0.9524 0.9328 0.9107 0.8865 0.1094 0.2182 0.3257 0.4313 0.5345 0.6348 0.7318 0.8251 0.9146 1.0000 1.1583 1.2999 1.4254 1.5360 1.6330 1.7179 1.7922 5.8218 2.9635 2.0351 1.5901 1.3398 1.1882 0.1 0.2 0.3 0.4 0.5 0.6 0.7 0.8 0.9 1.0 1.2 1.4 1.6 1.8 2.0 2.2 Monatomic Superheated steam, k-1.3 Hot products of combustion, k- 1.33 Air, gases, k-1.667 k- 1.4 0.5457 0.5404 0.5283 0.4871 1.0944 1.0382 1.0089 1.0000 1.0304 1.1149 1.2502 1.4390 0.7916 0.7400 0.6870 0.6339 0.5311 0.4374 0.3557 0.2868 0.2300 0.1841 0.8696 0.8584 0.8333 0.7499 0.5913 0.5283 0.4124 0.3142 0.2353 0.1740 0.1278 0.0935 0.0684 0.8606 0.8333 0.7764 0.7184 0.6614 0.6068 0.5556 0.5081 0.6276 0.6295 0.6340 0.6495 Po A 10+1M120k-1)] A* k + 2 1.6875 2.0050 2.4031 2.4 0.1472 0.4647
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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Air flows isentropically. Using die below table and find the divergent exit temperature, and pressure. Using equnlions lo find the exit area at Ma =2.
![Air flows isentropically. Using the below table
and find the divergent exit temperature, and
pressure. Using equations to find the exit area
at Ma = 2.
Throat
Ma = 0.4
A= 0.2 m2
Ma = 2
P= 1 Mpa atm
T=300 K
TABLE A-13
One-dimensional isentropic compressible flow functions for an ideal
gas with k= 1.4
Ma
Ma*
AA
PIP
plpo
TITO
TABLE 12-2
1.0000
0.9950
0.9803
The critical-pressure, critical-temperature, and çritical-density ratios for
isentropic flow of some ideal gases
1.0000
0.9930
0.9725
0.9395
0.8956
0.8430
0.7840
1.0000
0.9980
0.9921
0.9823
0.9690
0.9524
0.9328.
0.9107
0.8865
0.8606
0.8333
0.7764
00
0.1
0.2
0.3
0.4
0.5
0.6
0.1094
0.2182
0.3257
0.4313
0.5345
0.6348
5.8218
2.9635
2.0351
1.5901
1.3398
1.1882
1.0944
1.0382
Monatomic
Superheated
steam,
k-1.3
Hot products
of combustion,
k- 1.33
Air,
k- 1.4
0.9564
gases,
k-1.667
0.9243
0.8852
0.8405
0.7916
0.7400
0.6870
0.6339
0.5457
0.5404
0.5283
0.4871
P.
0.7318
0.8251
0.9146
1.0000
1.1583
1.2999
1.4254
1.5360
0.7209
0.6560
0.7
0.8696
0.8584
0.8333
0.7499
0.8
1.0089 0.5913
1.0000
1.0304
1.1149
1.2502
1.4390
1.6875
2.0050
2.4031
0.9
0.6276
0.6295
0.6340
0.6495
0.5283
0.4124 0.5311
0.3142
0.2353
0.1740
0.1278
0.0935
0.0684
1.0
Po
1.2
0.4374
0.3557
0.2868
0.7184
0.6614
0.6068
0.5556
0.5081
0.4647
1.4
1.6
1
k - 1
10+1/20k– 1)]
1+ Ma?
1.8
2.0
2.2
2.4
Mal
A*
k +
2
1.6330
1.7179
1.7922
0.2300
0.1841
0.1472](/v2/_next/image?url=https%3A%2F%2Fcontent.bartleby.com%2Fqna-images%2Fquestion%2F86a82b01-6731-4ef3-92de-3758f4f7ebe1%2Fa2bc4320-498c-4cf6-b6ba-ff4e4bd665b3%2Fge4n7cb_processed.jpeg&w=3840&q=75)
Transcribed Image Text:Air flows isentropically. Using the below table
and find the divergent exit temperature, and
pressure. Using equations to find the exit area
at Ma = 2.
Throat
Ma = 0.4
A= 0.2 m2
Ma = 2
P= 1 Mpa atm
T=300 K
TABLE A-13
One-dimensional isentropic compressible flow functions for an ideal
gas with k= 1.4
Ma
Ma*
AA
PIP
plpo
TITO
TABLE 12-2
1.0000
0.9950
0.9803
The critical-pressure, critical-temperature, and çritical-density ratios for
isentropic flow of some ideal gases
1.0000
0.9930
0.9725
0.9395
0.8956
0.8430
0.7840
1.0000
0.9980
0.9921
0.9823
0.9690
0.9524
0.9328.
0.9107
0.8865
0.8606
0.8333
0.7764
00
0.1
0.2
0.3
0.4
0.5
0.6
0.1094
0.2182
0.3257
0.4313
0.5345
0.6348
5.8218
2.9635
2.0351
1.5901
1.3398
1.1882
1.0944
1.0382
Monatomic
Superheated
steam,
k-1.3
Hot products
of combustion,
k- 1.33
Air,
k- 1.4
0.9564
gases,
k-1.667
0.9243
0.8852
0.8405
0.7916
0.7400
0.6870
0.6339
0.5457
0.5404
0.5283
0.4871
P.
0.7318
0.8251
0.9146
1.0000
1.1583
1.2999
1.4254
1.5360
0.7209
0.6560
0.7
0.8696
0.8584
0.8333
0.7499
0.8
1.0089 0.5913
1.0000
1.0304
1.1149
1.2502
1.4390
1.6875
2.0050
2.4031
0.9
0.6276
0.6295
0.6340
0.6495
0.5283
0.4124 0.5311
0.3142
0.2353
0.1740
0.1278
0.0935
0.0684
1.0
Po
1.2
0.4374
0.3557
0.2868
0.7184
0.6614
0.6068
0.5556
0.5081
0.4647
1.4
1.6
1
k - 1
10+1/20k– 1)]
1+ Ma?
1.8
2.0
2.2
2.4
Mal
A*
k +
2
1.6330
1.7179
1.7922
0.2300
0.1841
0.1472
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