Question

Consider an ideal turbojet at flight conditions: To =220 K, PO = 20 kPa, and Mo= 0.8. Calculate and plot: 1) the specific thrust, 2) f, and 3) ISP versus the compressor stagnation pressure ratio (πc). Perform calculations for Tt,A=1600 K and 1800 K and for πc from 1 to 50. The fuel heat of combustion is hf= 42,800 kJ/kg. What πc maximizes thrust at the two peak stagnation temperatures?

Answer 1

i) specific thrust = 11.065

ii) F = attached below

iii) Isp vs
`\pi`c = attached below

iv)
`\pi c1 = 16.38* 10^8\\\pi c2 = 24.47 * 10^8`

Step-by-step explanation:

Given data :

To = 220k

Po = 20 kPa

Mo = 0.8

Hf = 42800 KJ/kg