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)
Wind Tunnel Tests of a USAF Flight Helmet and Loss Preventer
1975
15 pages
Report
Keine Angabe
Englisch
Aircraft , Flight helmets , Ejection seats , Aerodynamic forces , Flight crews , Losses , Retention(General) , Pilots , Blast , Wind velocity , Escape systems , Spoilers , Pitch(Motion) , Yaw , Wind tunnel tests , Volunteers , Aerodynamic loading , Flailing , ACES(Advanced Concept Ejection Seat) , Advanced concept ejection seat
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