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Investigation of the Aerodynamic Characteristics in Pitch and Sideslip of a 45© Swept-wing Airplane Configuration with Various Vertical Locations of the Wing and Horizontal Tail
M. Leroy Spearman
其他書名
Static Lateral and Directional Stability; Mach Numbers of 1.41 and 2.01
出版National Advisory Committee for Aeronautics, 1957
URLhttp://books.google.com.hk/books?id=NOWIN479JXYC&hl=&source=gbs_api
EBookFULL_PUBLIC_DOMAIN
註釋An investigation has been conducted in the Langley 4- by 4-foot supersonic pressure tunnel to determine the effects of wing and horizontal-tail vertical location on the aerodynamic characteristics in sideslip at various angles of attack for a supersonic airplane configuration at Mach numbers of 1.41 and 2.01. The basic model was equipped with a wing and horizontal tail, each having 45 degree sweep and an aspect ratio of 4. The wing had a taper ratio of 0.2 and NACA 65A004 sections; the horizontal tail had a taper ratio of 0.4 and NACA 65A006 sections.