Determine the mach number at the duct exit

Reference no: EM131036210

Repeat Prob. 17-109 for a heat transfer rate of 300kJ/s.

Prob. 17-109

Compressed air from the compressor of a gas turbine enters the combustion chamber at T1 =550 K, P1=600 kPa, and Ma1 =0.2 at a rate of 0.3 kg/s. Via combustion, heat is transferred to the air at a rate of 200 kJ/s as it flows through the duct with negligible friction. Determine the Mach number at the duct exit and the drop in stagnation pressure P01 - P02 during this process.

Reference no: EM131036210

Questions Cloud

Determine the highest rate of heat transfer to the air : Disregarding frictional losses, determine the highest rate of heat transfer to the air in the duct without affecting the inlet conditions.

What did you learn after watching the clip : You work for a Public Relations agency. Currently what company (organization, institution, or person) needs your agency's help most? What specific steps will you take to improve this company's image? Go through all of the 10 steps in the link below..

Goal setting-mary corey case : David Brooks was one of the most liked managers at the Financial Security Investments. In an industry known for its cutthroat competitiveness, high employee turnover, low loyalty, and high employee mobility, the 20 brokers who reported to Brooks h..

Design and implement dynamic web pages using javascript : Design and implement dynamic web pages using JavaScript and design and evaluate websites and Traffic & Suggestions to improve the system

Determine the mach number at the duct exit : Determine the Mach number at the duct exit and the drop in stagnation pressure P01 - P02 during this process.

Determine the highest rate of heat transfer to the argon : Argon gas enters a constant cross-sectional-area duct at Ma1= 0.2, P1= 320 kPa, and T1 =400 K at a rate of 0.8 kg/s.

Plot the mass flow parameter m : Plot the mass flow parameter m. 0(AP0) versus the Mach number for k =1.2, 1.4, and 1.6 in the range of 0 ≤ Ma ≤ 1.

Calculate the speed of the airplane : Calculate the speed of the airplane and the flight Mach number

Derive an expression for the speed of sound on van der waals : The van der Waals constants for carbon dioxide are a = 364.3 kPa · m6/kmol2 and b= 0.0427 m3/kmol.

User Account

All Pages