00:01
Our question is a turbojit is flying with a velocity of 900 feet per second and at an altitude of 20 ,000 feet.
00:07
Here the velocity is given that is v1 is equal to 900 feet per second at an altitude of 20 ,000 feet where the ambient conditions are 7 pcia and 10 degrees fahrenheit.
00:24
Here temperature is 10 degree fahrenheit and we will convert it into rankie by adding 469 .67.
00:33
And the answer would be 470.
00:40
So the pressure ratio across the compressor, that is, rp, is 13.
00:47
And the temperature at the turbine end result is 2400.
00:50
This is a t5 temperature that is 2400 ranking.
00:55
Assuming ideal operations for all components in specific heats at room temperature, determine the pressure at the turbine exit.
01:03
A, we have to find the pressure at the turbine exit.
01:06
Exit, velocity of the exhaust gases and the propulsion efficiency.
01:21
Propulsive efficiency.
01:35
So here study operating conditions exist.
01:37
First we will draw the tnh diagram.
01:58
1, 2, 3.
02:02
This is the heat input.
02:05
4, 5 and 6.
02:09
This is the heat output.
02:16
Here, the properties of air at room temperature are also given that.
02:20
Is cp is equal to 0 .24 british thermal unit divided by ibm .r.
02:31
And k is equals to 1 .4.
02:35
For convenience, we assume the aircraft is stationary and the air is moving towards the aircraft of the velocity of 900 feet per second...