Design of the Helicopter Escape and Personnel Survival System for large helicopters requires that rocket exhaust plumes pass in close proximity to the helicopter body. In this report, an engineering analysis is performed to determine the severity of the problem, with emphasis on taking worst-case examples. Two computer plume prediction techniques were used and three subscale tests using live rocket motors and a helicopter model were performed. A complete study of the problem should include developing equations describing the flow field of the plume about the helicopter body and the heat transfer to the fuselage based on this flow field, but was not performed in this study due to funding shortages. Results indicated that the helicopter body should be able to survive the environment. In the future, it is recommended that an instrumented helicopter cross-section be placed in the exhaust plume of a heavyweight retro motor to verify the safety of the system. (Author)


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    Helicopter Personnel Escape and Survival System

    Wiseman, Ryland D. | SAE Technical Papers | 1970


    Helicopter Personnel Escape, Protection and Survival System

    Thomasson, F. Terry | SAE Technical Papers | 1967


    Exhaust-Plume Impingement Characteristics

    Smith, S. D. / Wojciehowski, C. J. | NTRS | 1983



    Numerical Study of Base Flow Induced by Exhaust Plume Impingement

    Webster, R. S. / American Institute of Aeronautics and Astronautics / Society of Automotive Engineers et al. | British Library Conference Proceedings | 1998