Consider a turbojet in an airplane flying at standard sea level with a velocity of 800 . The pressure ratio across the compress 01 r is 12.5:1. The fuel-to-air ratio (by mass) is 0.05. If the nozzle exhausts the flow to ambient pressure, calculate the gas temperature at the exit (In solving this problem, assume that the air in the diffuser is slowed to a very low velocity before entering the compressor. Also assume that the heat released per pound of fuel is 1.4 x 107 · .,.)
. .
The post calculate the gas temperature at the exit appeared first on Unified Papers.
“Looking for a Similar Assignment? Get Expert Help at an Amazing Discount!”
The post calculate the gas temperature at the exit appeared first on UNIFIED PAPERS.
calculate the gas temperature at the exit was first posted on February 6, 2019 at 9:10 pm.
©2019 "UNIFIED PAPERS". Use of this feed is for personal non-commercial use only. If you are not reading this article in your feed reader, then the site is guilty of copyright infringement. Please contact me at admin@unifiedpapers.com
Recent Comments