Mission-Analysis Computer Program for Investigating Performance Effectiveness of Airbreathing Engines.
Final rept. 1 Dec 64-31 Mar 68,
AIR FORCE AERO PROPULSION LAB WRIGHT-PATTERSON AFB OH
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A mission-analysis method designed for the investigation of performance effectiveness of airbreathing propulsion systems has been developed and programmed in IBM 70907094 FORTRAN IV. Although developed primarily for evaluating turbine engines, the method is equally effective with ramjet systems by the simple substitution of launch point conditions for take-off conditions. The program requires definition of 1 airframe and external load aerodynamics, 2 uninstalled engine performance biased by inlet pressure recovery, and 3 propulsion system installation losses consisting of a inlet spillage performance, b inlet boundary layer bleed system performance, c bypass system performance, d and vehicle aft end performance thrust minus drag. If the program vehicle sizing option is exercised, weight characteristics of the vehicle and complete propulsion system are also required. These characteristics are combined into a scalable-size vehicle of constant proportions which is flown through a specified mission built up of the proper sequence of flight legs, for which the required fuel fraction is calculated by digital computer. The take-off launch gross weight can be calculated, or, optionally, a specified mission can be flown with variable leg ranges. The report includes the description and results of an application study involving a tactical aircraft with component trade-offs and the generation of sensitivity factors. Author
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