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  Partner: UNT Libraries Government Documents Department
 Collection: National Advisory Committee for Aeronautics Collection
Wind-tunnel investigation at a Mach number of 1.53 of an airplane with a triangular wing

Wind-tunnel investigation at a Mach number of 1.53 of an airplane with a triangular wing

Date: January 23, 1948
Creator: Scherrer, Richard
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Wind-tunnel investigation at a Mach number of 2.01 of forebody strakes for improving directional stability of supersonic aircraft

Wind-tunnel investigation at a Mach number of 2.01 of forebody strakes for improving directional stability of supersonic aircraft

Date: May 26, 1958
Creator: Driver, Cornelius
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Wind-Tunnel Investigation at a Mach Number of 2.01 of the Aerodynamic Characteristics in Combined Angles of Attack and Sideslip of Several Hypersonic Missile Configurations with Various Canard Controls

Wind-Tunnel Investigation at a Mach Number of 2.01 of the Aerodynamic Characteristics in Combined Angles of Attack and Sideslip of Several Hypersonic Missile Configurations with Various Canard Controls

Date: March 10, 1958
Creator: Robinson, R. B.
Description: An investigation of the aerodynamic characteristics of several hypersonic missile configurations with various canard controls for an angle-of-attack range from 0 deg to about 28 deg at sideslip angles of about 0 deg and 4 deg at a Mach number of 2.01 has been made in the Langley 4- by 4-foot supersonic pressure tunnel. The configurations tested were a body alone which had a ratio of length to diameter of 10, the body with a 10 deg flare, the body with cruciform fins of 5 deg or 15 deg apex angle, and a flare-stabilized rocket model with a modified Von Karman nose. Various canard surfaces for pitch control only were tested on the body with the 10 deg flare and on the body with both sets of fins. The results indicated that the addition of a flared afterbody or cruciform fins produced configurations which were longitudinally and directionally stable. The body with 5 deg fins should be capable of producing higher normal accelerations than the flared body. A l l of the canard surfaces were effective longitudinal controls which produced net positive increments of normal force and pitching moments which progressively decreased with increasing angle of attack.
Contributing Partner: UNT Libraries Government Documents Department
Wind-tunnel investigation at a Mach number of 2.01 of the aerodynamic characteristics in combined pitch and sideslip of some canard-type missiles having cruciform wings and canard surfaces with 70 degree delta plan forms

Wind-tunnel investigation at a Mach number of 2.01 of the aerodynamic characteristics in combined pitch and sideslip of some canard-type missiles having cruciform wings and canard surfaces with 70 degree delta plan forms

Date: August 23, 1954
Creator: Spearman, M Leroy
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Wind-tunnel investigation at high and low subsonic Mach numbers of a thin sweptback wing having an airfoil section designed for high maximum lift

Wind-tunnel investigation at high and low subsonic Mach numbers of a thin sweptback wing having an airfoil section designed for high maximum lift

Date: February 26, 1952
Creator: Racisz, Stanley F
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Wind-tunnel investigation at high and low subsonic Mach numbers of two unswept wings having NACA 2-006 and NACA 65A006 airfoil sections

Wind-tunnel investigation at high and low subsonic Mach numbers of two unswept wings having NACA 2-006 and NACA 65A006 airfoil sections

Date: December 4, 1953
Creator: Racisz, Stanley F
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Wind-tunnel investigation at high subsonic speeds of a spoiler-slot deflector combination on an NACA 65A006 wing with quarter-chord line swept back 32.6 degrees

Wind-tunnel investigation at high subsonic speeds of a spoiler-slot deflector combination on an NACA 65A006 wing with quarter-chord line swept back 32.6 degrees

Date: May 29, 1953
Creator: Vogler, Raymond D
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Wind tunnel investigation at high subsonic speeds of drag at 0 deg angle of attack of swept-wing fuselage models with pylon mounted and semisubmerged missiles

Wind tunnel investigation at high subsonic speeds of drag at 0 deg angle of attack of swept-wing fuselage models with pylon mounted and semisubmerged missiles

Date: October 8, 1956
Creator: King, T. J., Jr.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Wind-tunnel investigation at high subsonic speeds of some effects of fuselage cross-section shape and wing height on the static longitudinal and lateral stability characteristics of a model having a 45 degree swept wing

Wind-tunnel investigation at high subsonic speeds of some effects of fuselage cross-section shape and wing height on the static longitudinal and lateral stability characteristics of a model having a 45 degree swept wing

Date: February 3, 1956
Creator: King, Thomas J , Jr
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Wind-tunnel investigation at high subsonic speeds of spoilers of large projection on an NACA 65A006 wing with quarter-chord line swept back 32.6 degrees

Wind-tunnel investigation at high subsonic speeds of spoilers of large projection on an NACA 65A006 wing with quarter-chord line swept back 32.6 degrees

Date: January 17, 1952
Creator: Vogler, Raymond D
Description: None
Contributing Partner: UNT Libraries Government Documents Department