An experimental effort was accomplished to measure the aerodynamic forces that act upon a crewman's flight helmet during use of an aircraft emergency escape system. Tests were accomplished within a low speed wind tunnel using volunteer subjects seated within an ACES II escape system. The wind velocity was varied to produce dynamic pressures ranging from 10 to 50 lb per sq ft. The pitch angle of the seat and subject were varied -2 to +73 degs. The yaw angle was varied from 0 to 30 degs. (Author)


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    Title :

    Wind Tunnel Tests of a USAF Flight Helmet and Loss Preventer


    Contributors:

    Publication date :

    1975


    Size :

    15 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English





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