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Author: Harold Mirels Publisher: ISBN: Category : Aerodynamic load Languages : en Pages : 28
Book Description
An investigation was conducted at a Mach number of 1.90 to determine spanwise pressure distribution over a wing tip in a region influenced by a sharp subsonic trailing edge. The wing section was a symmetrical wedge of 5 degrees 43 minutes total included angle in the free-stream direction. The investigation was conducted over a range of angles of attack from -10 to 10 degrees at a Reynolds number of 3,400,000 per foot.
Author: Harold Mirels Publisher: ISBN: Category : Aerodynamic load Languages : en Pages : 28
Book Description
An investigation was conducted at a Mach number of 1.90 to determine spanwise pressure distribution over a wing tip in a region influenced by a sharp subsonic trailing edge. The wing section was a symmetrical wedge of 5 degrees 43 minutes total included angle in the free-stream direction. The investigation was conducted over a range of angles of attack from -10 to 10 degrees at a Reynolds number of 3,400,000 per foot.
Author: Harold Mirels
Author: Harold Mirels
Author: Lowell E. Hasel
Author: Stavros A. Hartofilis
Author: W. Douglas Morris
Author: 
Author: Hill, Jr. (William A.)
Author: 
Author: United States. National Advisory Committee for Aeronautics
Author: United States. Air Force. Office of Scientific Research
Author: