M Goodarzi - Department of Mechanical Engineering, Faculty of Engineering, University of Malaya, Kuala Lumpur Malaysia
B Rahmanian - Department of Mechanical Engineering, Payam Noor University, Jahrom Branch, Jahrom, Iran
M Dahari - Department of Mechanical Engineering, Faculty of Engineering, University of Malaya, Kuala Lumpur Malaysia
M.R Safaei - Department of Mechanical Engineering, Faculty of Engineering, University of Malaya, Kuala Lumpur Malaysia

Efficiency of a turboprop engine equipped by Clark-Y 5868-R9 propeller is studied numerically at ondesignconditions. To obtain the efficiency of the propeller, the thrust and power coefficients and alsoperformance of the propeller are calculated. At on-design condition, the object of cycle analysis is to obtainestimates of the performance in terms of design limitations such as flight conditions, and design choices. Theprovided house-made code predict some performance parameters such as overall thermal efficiency, compressorpressure ratio, fuel flow rate, specific fuel consumption and turbine inlet temperature versus various altitudes andflight Mach numbers. It can be seen that in a specified altitude and also due to increasing flight Mach number thecompressor pressure ratio will be abate and the specific thrust will be decreased. As a result of increasing flightMach number and in a given elevation, the specific fuel consumption (SFC) will be increase. Also, reducing thetemperature of air at entry to a turboprop engine will increase the specific thrust. So, liquid injection methodused to increase temperature of the air which entry to the turboprop engine.

Turboprop Engine, Off-design Condition, Mach number, thrust augmentation