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- An airfoil is in a freestream where ๐
โ
= 0.61 atm, ๐
โ
= 0.819 kg/m
3
, and ๐
โ
m/s. At a point on the airfoil surface, the pressure is 0.5 atm. Assuming isentropic
flow, calculate the velocity at that point.
GIVEN:
โ
= 0. 61 atm
โ
= 0. 819 kg/m
3
โ
= 300 m/s
P = 0.5 atm
REQUIRED:
V
SOLUTION:
โ
โ
โ
โ
๐
โ
๐
โ
๐
โ
( 0. 61 ๐๐ก๐)(
101 , 325 ๐๐
1 ๐๐ก๐
)
( 0. 819
๐๐
๐
3
)( 287. 08
๐ฝ
๐๐โ๐พ
โ
๐
โ
๐ โ
๐
โ
๐
๐
โ
๐
โ
๐
๐
No.: 2
Name: ALDECOA, Mico Onil Ram
BLEN, Juliane Nicole A.
VILLARUEL, Pee-Jaye
Instructor: Engr. Roberto Renigen
Submission Date: 18 March 2024
Rating:
Problem Solving
โ
โ
๐
๐ โ
๐
โ
2
๐
2
2
- 5
[
โ
โ
2
2
2
- 5
]
1
- 5
๐
๐ โ
1
- 5
๐ โ
2
๐ 2
2
๐
๐
โ
1
- 5
2
2
โ
2
2
2
๐
โ
2
(
๐
๐
โ
)
1
- 5
2
2
๐
โ
2
(
๐
๐
โ
)
1
- 5
2
๐
โ
2
(
๐
๐
โ
)
1
- 5
2
( 0. 923 )
2
(
5
61
)
1
- 5
2
No.: 2
Problem Solving
- An air tank with a nozzle has a pressure of 196.32 Kpa and a density of 1.9 kg/m
3
Outside the converging-diverging nozzle, the pressure is atmospheric and designed
to have a Mach No. of 1.0 and 1. 5 at the throat and exit, respectively. The area at
the throat is 0.11m
2
. Calculate the following:
(a) Temperature and speed of sound at the tank
(b) Pressure, density, temperature, and speed of sound at the throat
(c) Mass flow at the exit
GIVEN:
P
o
= 196.32 KPa = 196,320 Pa
ฯ o
= 1.9 kg/m
3
Area at the throat (๐ด
๐ก
) = 0.11m
2
REQUIRED:
(a) ๐
๐
๐ 0
(b) ๐
๐
๐
๐
๐
๐
(c) แน
๐ธ
SOLUTION:
(a) ๐
๐
= ฯ o
R๐
๐
๐
๐ ๐
๐๐
196 , 320 Pa
( 1. 9
๐๐
๐
3
)( 287. 08
๐ฝ
๐๐โ๐พ
)
๐
= 359.92K
No.: 2
Problem Solving
๐
๐
๐
= 380.38 m/s
(b)
๐
๐ก
๐
0
= [
(๐
1
)
2
(๐
2
)
2
]
- 5
๐
= [
( 1 )
2
( 1. 5 )
2
]
- 5
[ 196. 32 ๐พ๐๐]
๐
= 101.23 Kpa = 101,230 Pa
๐ ๐
๐ ๐
๐ ๐
๐ ๐
1
- 4
๐
๐
๐
๐
๐
1
- 4
(๐
๐
๐
23 ๐พ๐๐
32 ๐พ๐๐
1
- 4 ( 1. 9
๐๐
๐
3
๐
๐๐
๐
3
๐
๐
๐
๐
๐
๐
๐
๐
๐
- 23 ๐พ๐๐
( 1. 184
๐๐
๐
3
) ( 287. 08
๐ฝ
๐๐โ๐พ
)
๐
Speed of Sound at that section
Va T
๐
Va T
Va T
= 346.01 m/s
No.: 2
Problem Solving
