Vendetta Final Proposal Part 1 (3.4 MB) - Cal Poly

NPFNewMeasurement = OldMeasurement( ) NPFAxial length scaling exponent = 0.4Diameter scaling exponent = 0.5Weight scaling exponent = 1.0baseexponentThe RFP engine produced a military thrust of 26,350 pounds and had a cruise thrust specific fuel consumption(TSFC) of 1.19 1/hr for Mach 1.6 flow at 50,000 ft. TSFC is calculated using the following equation:TSFC =W FNPFThe Vendetta will require two engines to perform the desired mission. The size, weight, and location of theengines have great effect on the size of the airplane. The larger the engines the wider the aft portion of the fuselage andthe longer the airplane. For the size and weight of the RFP engine, it produced too little thrust and burned too much fuelcompared to modern turbofan engines.Other engines were analyzed in an attempt to find a better performing engine that was smaller and lighter thanthat supplied. Through this research the Concorde Rolls-Royce SNECMA Olympus engine was found to be comparableto the RFP engine; however, the engine was first manufactured and flown in the Concorde in the mid ‘60’s through mid‘70’s. Table 6.II compares the RFP engine to that of the SNECMA Olympus. As can be seen, the SNECMA Olympus isvery close in size and weight to that of the RFP; however, it produces even more thrust than that of the RFP. Also theweight of the SNECMA Olympus includes that of an afterburner whereas the RFP engine is without an afterburner.Table 6.II - RFP Dimensions Compared to the SNECMA OlympusRFP SNECMAOlympusFan Face Diameter 50 in 47.5 inLength 310 in 280 inWeight 7200 lbs 7000 lbsMax Dry Thrust 26,356 lbs 31,350 lbsBased on these data the RFP engine resembled outdated technology; a more efficient and modern engine will beneeded for the design of the Vendetta. The RFP engine deck was used as a baseline for designing a newer, better engine,as it was the only full engine deck available. It was determined that an F119 engine would be the initial design engine forthe airplane. This engine is currently used in the F-22 and a derivation of the engine (the F135) is to be used in the F-35.Engine performance data for the F119 are classified except that it is in a 35,000 lbs thrust class. Several methodswere utilized to narrow in on the thrust produced by the F119. Through the use of The Integrated High Performance27