Force and pressure tests of two elliptic ogive body shapes at Mach numbers 5, 6, and 8 /

Tests were conducted at Mach numbers 5, 6, and 8 to obtain force and pressure distribution data for two elliptic ogives. The results presented show the effect of Mach number and Reynolds number variation on aerodynamic forces for angles of attack from -6 to +6 deg and on pressure distributions for angles of attack from -4 to +4 deg. Shadowgraphs obtained at various angles of attack show shock wave and boundary layer phenomena."Research supported by the United States Air Force, and performed by the VKF, ARO, Inc.""ARO Project No. 321114.""Program Area 750A, Project No. 1370."AD0255762 (from http://www.dtic.mil)."April 1961."Includes bibliographical references (page 14).Tests were conducted at Mach numbers 5, 6, and 8 to obtain force and pressure distribution data for two elliptic ogives. The results presented show the effect of Mach number and Reynolds number variation on aerodynamic forces for angles of attack from -6 to +6 deg and on pressure distributions for angles of attack from -4 to +4 deg. Shadowgraphs obtained at various angles of attack show shock wave and boundary layer phenomena.Print reproduction.U.S. Air Force Contract No.Mode of access: Internet