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  Partner: UNT Libraries Government Documents Department
 Collection: National Advisory Committee for Aeronautics Collection
Wind tunnel force tests in wing systems through large angles of attack

Wind tunnel force tests in wing systems through large angles of attack

Date: August 1, 1928
Creator: Wenzinger, Carl J & Harris, Thomas A
Description: Force tests on a systematic series of wing systems over a range of angle of attack from minus forty-five degrees to plus ninety degrees are covered in this report. The investigation was made on monoplane and biplane wing models to determine the effects of variations of tip shape, aspect ratio, flap setting, stagger, gap, decalage, sweepback, and airfoil profile.
Contributing Partner: UNT Libraries Government Documents Department
Wind-tunnel interference with particular reference to off-center positions of the wing and to the downwash at the tail

Wind-tunnel interference with particular reference to off-center positions of the wing and to the downwash at the tail

Date: January 1, 1937
Creator: Silverstein, Abe & White, James A
Description: The theory of wind tunnel boundary influence on the downwash from a wing has been extended to provide more complete corrections for application to airplane test data. The first section of the report gives the corrections of the lifting line for wing positions above or below the tunnel center line; the second section shows the manner in which the induced boundary influence changes with distance aft of the lifting line. Values of the boundary corrections are given for off-center positions of the wing in circular, square, 2:1 rectangular, and 2:1 elliptical tunnels. Aft of the wing the corrections are presented for only the square and the 2:1 rectangular tunnels, but it is believed that these may be applied to jets of circular and 2:1 elliptical cross sections. In all cases results are included for both open and closed tunnels.
Contributing Partner: UNT Libraries Government Documents Department
Wind-tunnel investigation and analysis of the effects of end plates on the aerodynamic characteristics of an unswept wing

Wind-tunnel investigation and analysis of the effects of end plates on the aerodynamic characteristics of an unswept wing

Date: August 1, 1951
Creator: Riley, Donald R
Description: None
Contributing Partner: UNT Libraries Government Documents Department
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 & Wimbrow, William R
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 & CORNELIUS DRIVER
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 & Paradiso, Nicholas J
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