Problem 1 (5 points): An aircraft is flying at a cruising speed of 250 m/s at an altitude of 4000 m. The ambient air is first decelerated in a diffuser before it enters the com- pressor. Assuming both the diffuser and the compressor to be isentropic, determine (a) the stagnation pressure at the compressor inlet and (b) the required compressor work per unit mass if the stagnation pressure ratio of the compressor is 8. Table C.2 Properties of the U.S. Standard Atmosphere (SI Units)" Altitude Temperature (m) (°C) Acceleration of Gravity, g (m/s²) Density, Dynamic Viscosity, Pressure, p [N/m²(abs)] P (kg/m³) μ (N-s/m²) -1,000 21.50 9.810 15.00 9.807 1.013 1.139 E +5 E+5 1.347 E+0 1.225 1.821 E-5 E+0 1.789 E-5 1,000 8.50 9.804 8.988 E+4 1.112 E +0 1.758 E-5 2,000 2.00 9.801 7.950 E+4 1.007 E +0 1.726 E-5 3,000 -4.49 9.797 7.012 E+4 9.093 E 1 1.694 E-5 4,000 -10.98 9.794 6.166 E +4 8.194 E 1 - 1.661 E-5 5,000 -17.47 9.791 5.405 E+4 7.364 E 1 1.628 E-5 6,000 -23.96 9.788 4.722 E+4 6.601 E- 1 1.595 E-5 7,000 -30.45 9.785 4.111 E + 4 5.900 E 1 1.561 E-5 8,000 -36.94 9.782 3.565 E+4 5.258 E 1 1.527 E-5 9,000 -43.42 9.779 3.080 E+4 4.671 E 1 1.493 E-5 10,000 -49.90 9.776 2.650 E+4 4.135 E-1 1.458 E-5 15,000 -56.50 9.761 1.211 E +4 1.948 E-1 1.422 E-5 20,000 -56.50 9.745 5.529 E + 3 8.891 E-2 1.422 E-5 25,000 -51.60 9.730 2.549 E + 3 4.008 E-2 1.448 E-5 30,000 -46.64 9.715 1.197 E + 3 1.841 E-2 1.475 E-5 40,000 -22.80 9.684 2.871 E + 2 3.996 E-3 1.601 E-5 50,000 -2.50 9.654 7.978 E+1 1.027 E-3 1.704 E-5 60,000 -26.13 9.624 2.196 E+1 3.097 E-4 1.584 E-5 70,000 -53.57 9.594 5.221 E+0 8.283 E-5 1.438 E-5 80,000 -74.51 9.564 1.052 E+0 1.846 E-5 1.321 E-5 "Data abridged from U.S. Standard Atmosphere, 1976, U.S. Government Printing Office, Washington, D.C.
Problem 1 (5 points): An aircraft is flying at a cruising speed of 250 m/s at an altitude of 4000 m. The ambient air is first decelerated in a diffuser before it enters the com- pressor. Assuming both the diffuser and the compressor to be isentropic, determine (a) the stagnation pressure at the compressor inlet and (b) the required compressor work per unit mass if the stagnation pressure ratio of the compressor is 8. Table C.2 Properties of the U.S. Standard Atmosphere (SI Units)" Altitude Temperature (m) (°C) Acceleration of Gravity, g (m/s²) Density, Dynamic Viscosity, Pressure, p [N/m²(abs)] P (kg/m³) μ (N-s/m²) -1,000 21.50 9.810 15.00 9.807 1.013 1.139 E +5 E+5 1.347 E+0 1.225 1.821 E-5 E+0 1.789 E-5 1,000 8.50 9.804 8.988 E+4 1.112 E +0 1.758 E-5 2,000 2.00 9.801 7.950 E+4 1.007 E +0 1.726 E-5 3,000 -4.49 9.797 7.012 E+4 9.093 E 1 1.694 E-5 4,000 -10.98 9.794 6.166 E +4 8.194 E 1 - 1.661 E-5 5,000 -17.47 9.791 5.405 E+4 7.364 E 1 1.628 E-5 6,000 -23.96 9.788 4.722 E+4 6.601 E- 1 1.595 E-5 7,000 -30.45 9.785 4.111 E + 4 5.900 E 1 1.561 E-5 8,000 -36.94 9.782 3.565 E+4 5.258 E 1 1.527 E-5 9,000 -43.42 9.779 3.080 E+4 4.671 E 1 1.493 E-5 10,000 -49.90 9.776 2.650 E+4 4.135 E-1 1.458 E-5 15,000 -56.50 9.761 1.211 E +4 1.948 E-1 1.422 E-5 20,000 -56.50 9.745 5.529 E + 3 8.891 E-2 1.422 E-5 25,000 -51.60 9.730 2.549 E + 3 4.008 E-2 1.448 E-5 30,000 -46.64 9.715 1.197 E + 3 1.841 E-2 1.475 E-5 40,000 -22.80 9.684 2.871 E + 2 3.996 E-3 1.601 E-5 50,000 -2.50 9.654 7.978 E+1 1.027 E-3 1.704 E-5 60,000 -26.13 9.624 2.196 E+1 3.097 E-4 1.584 E-5 70,000 -53.57 9.594 5.221 E+0 8.283 E-5 1.438 E-5 80,000 -74.51 9.564 1.052 E+0 1.846 E-5 1.321 E-5 "Data abridged from U.S. Standard Atmosphere, 1976, U.S. Government Printing Office, Washington, D.C.
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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![Problem 1 (5 points): An aircraft is flying at a cruising speed of 250 m/s at an altitude
of 4000 m. The ambient air is first decelerated in a diffuser before it enters the com-
pressor. Assuming both the diffuser and the compressor to be isentropic, determine
(a) the stagnation pressure at the compressor inlet and (b) the required compressor
work per unit mass if the stagnation pressure ratio of the compressor is 8.
Table C.2
Properties of the U.S. Standard Atmosphere (SI Units)"
Altitude Temperature
(m)
(°C)
Acceleration
of Gravity,
g (m/s²)
Density,
Dynamic
Viscosity,
Pressure, p
[N/m²(abs)]
P
(kg/m³)
μ
(N-s/m²)
-1,000
21.50
9.810
15.00
9.807
1.013
1.139 E +5
E+5
1.347 E+0
1.225
1.821 E-5
E+0
1.789 E-5
1,000
8.50
9.804
8.988 E+4
1.112 E +0
1.758 E-5
2,000
2.00
9.801
7.950 E+4
1.007 E +0
1.726 E-5
3,000
-4.49
9.797
7.012
E+4
9.093 E 1
1.694 E-5
4,000
-10.98
9.794
6.166 E +4
8.194 E 1
-
1.661 E-5
5,000
-17.47
9.791
5.405
E+4
7.364 E 1
1.628 E-5
6,000
-23.96
9.788
4.722
E+4
6.601 E- 1
1.595 E-5
7,000
-30.45
9.785
4.111
E + 4
5.900 E 1
1.561 E-5
8,000
-36.94
9.782
3.565
E+4
5.258 E 1
1.527 E-5
9,000
-43.42
9.779
3.080 E+4
4.671 E 1
1.493 E-5
10,000
-49.90
9.776
2.650
E+4
4.135 E-1
1.458 E-5
15,000
-56.50
9.761
1.211 E +4
1.948 E-1
1.422 E-5
20,000
-56.50
9.745
5.529
E + 3
8.891 E-2
1.422 E-5
25,000
-51.60
9.730
2.549 E + 3
4.008 E-2
1.448 E-5
30,000
-46.64
9.715
1.197
E + 3
1.841 E-2
1.475 E-5
40,000
-22.80
9.684
2.871 E + 2
3.996 E-3
1.601 E-5
50,000
-2.50
9.654
7.978
E+1
1.027 E-3
1.704 E-5
60,000
-26.13
9.624
2.196 E+1
3.097 E-4
1.584 E-5
70,000
-53.57
9.594
5.221 E+0
8.283 E-5
1.438 E-5
80,000
-74.51
9.564
1.052 E+0 1.846 E-5
1.321 E-5
"Data abridged from U.S. Standard Atmosphere, 1976, U.S. Government Printing Office, Washington, D.C.](/v2/_next/image?url=https%3A%2F%2Fcontent.bartleby.com%2Fqna-images%2Fquestion%2Fccb600fb-f597-4789-a805-df5336dda19a%2F81cdfdd0-333c-4a9e-af23-8d08cf484828%2F1x9jy5t_processed.jpeg&w=3840&q=75)
Transcribed Image Text:Problem 1 (5 points): An aircraft is flying at a cruising speed of 250 m/s at an altitude
of 4000 m. The ambient air is first decelerated in a diffuser before it enters the com-
pressor. Assuming both the diffuser and the compressor to be isentropic, determine
(a) the stagnation pressure at the compressor inlet and (b) the required compressor
work per unit mass if the stagnation pressure ratio of the compressor is 8.
Table C.2
Properties of the U.S. Standard Atmosphere (SI Units)"
Altitude Temperature
(m)
(°C)
Acceleration
of Gravity,
g (m/s²)
Density,
Dynamic
Viscosity,
Pressure, p
[N/m²(abs)]
P
(kg/m³)
μ
(N-s/m²)
-1,000
21.50
9.810
15.00
9.807
1.013
1.139 E +5
E+5
1.347 E+0
1.225
1.821 E-5
E+0
1.789 E-5
1,000
8.50
9.804
8.988 E+4
1.112 E +0
1.758 E-5
2,000
2.00
9.801
7.950 E+4
1.007 E +0
1.726 E-5
3,000
-4.49
9.797
7.012
E+4
9.093 E 1
1.694 E-5
4,000
-10.98
9.794
6.166 E +4
8.194 E 1
-
1.661 E-5
5,000
-17.47
9.791
5.405
E+4
7.364 E 1
1.628 E-5
6,000
-23.96
9.788
4.722
E+4
6.601 E- 1
1.595 E-5
7,000
-30.45
9.785
4.111
E + 4
5.900 E 1
1.561 E-5
8,000
-36.94
9.782
3.565
E+4
5.258 E 1
1.527 E-5
9,000
-43.42
9.779
3.080 E+4
4.671 E 1
1.493 E-5
10,000
-49.90
9.776
2.650
E+4
4.135 E-1
1.458 E-5
15,000
-56.50
9.761
1.211 E +4
1.948 E-1
1.422 E-5
20,000
-56.50
9.745
5.529
E + 3
8.891 E-2
1.422 E-5
25,000
-51.60
9.730
2.549 E + 3
4.008 E-2
1.448 E-5
30,000
-46.64
9.715
1.197
E + 3
1.841 E-2
1.475 E-5
40,000
-22.80
9.684
2.871 E + 2
3.996 E-3
1.601 E-5
50,000
-2.50
9.654
7.978
E+1
1.027 E-3
1.704 E-5
60,000
-26.13
9.624
2.196 E+1
3.097 E-4
1.584 E-5
70,000
-53.57
9.594
5.221 E+0
8.283 E-5
1.438 E-5
80,000
-74.51
9.564
1.052 E+0 1.846 E-5
1.321 E-5
"Data abridged from U.S. Standard Atmosphere, 1976, U.S. Government Printing Office, Washington, D.C.
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