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  Partner: UNT Libraries Government Documents Department
 Collection: National Advisory Committee for Aeronautics Collection
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
Wind-tunnel investigation at high subsonic speeds of the effects of wing-mounted external stores on the loading and aerodynamic characteristics in pitch of a 45 degree sweptback wing combined with a fuselage

Wind-tunnel investigation at high subsonic speeds of the effects of wing-mounted external stores on the loading and aerodynamic characteristics in pitch of a 45 degree sweptback wing combined with a fuselage

Date: March 23, 1954
Creator: Silvers, H Norman & King, Thomas J , Jr
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Wind-tunnel investigation at high subsonic speeds of the effects on static stability characteristics of various modifications to a swept-wing fighter-type airplane model

Wind-tunnel investigation at high subsonic speeds of the effects on static stability characteristics of various modifications to a swept-wing fighter-type airplane model

Date: April 30, 1957
Creator: Goodson, K. W.
Description: Wind tunnel investigations of effect on static stability of modifications to swept wing fighter aircraft model.
Contributing Partner: UNT Libraries Government Documents Department
A wind-tunnel investigation at high subsonic speeds of the lateral control characteristics of various plain spoiler configurations on a 3-percent-thick 60 degree delta wing

A wind-tunnel investigation at high subsonic speeds of the lateral control characteristics of various plain spoiler configurations on a 3-percent-thick 60 degree delta wing

Date: May 26, 1954
Creator: Wiley, Harleth G
Description: Results are presented of wind-tunnel investigations at Mach numbers of 0.60 to 0.94 and angles of attack of -2 degrees to about 24 degrees to determine the lateral control characteristics of spoilers with various wing chord-wise and spanwise locations and spoiler spans and deflections on thin 60 degree delta wing of NACA 65a003 airfoil section parallel to free stream.
Contributing Partner: UNT Libraries Government Documents Department
Wind-tunnel investigation at high subsonic speeds of the stability characteristics of a complete model having sweptback-,M-,W-,and cranked-wing plan forms and several horizontal-tail locations

Wind-tunnel investigation at high subsonic speeds of the stability characteristics of a complete model having sweptback-,M-,W-,and cranked-wing plan forms and several horizontal-tail locations

Date: May 14, 1954
Creator: Goodson, Kenneth W & Becht, Robert E
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Wind-Tunnel Investigation at High Subsonic Speeds of the Static Longitudinal and Static Lateral Stability Characteristics of a Wing-Fuselage Combination Having a Triangular Wing of Aspect Ratio 2.31 and an NACA 65A003 Airfoil

Wind-Tunnel Investigation at High Subsonic Speeds of the Static Longitudinal and Static Lateral Stability Characteristics of a Wing-Fuselage Combination Having a Triangular Wing of Aspect Ratio 2.31 and an NACA 65A003 Airfoil

Date: August 28, 1953
Creator: Wiggins, James W
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Wind-tunnel investigation at low and transonic speeds of the feasibility of self-actuating spoilers as a lateral-control device for a missile

Wind-tunnel investigation at low and transonic speeds of the feasibility of self-actuating spoilers as a lateral-control device for a missile

Date: January 28, 1954
Creator: Wiley, Harleth G & Hayes, William C JR
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Wind-tunnel investigation at low speed of a 45 degree sweptback untapered semispan wing of aspect ratio 1.59 equipped with various 25-percent chord plain flaps

Wind-tunnel investigation at low speed of a 45 degree sweptback untapered semispan wing of aspect ratio 1.59 equipped with various 25-percent chord plain flaps

Date: August 1, 1950
Creator: Johnson, Harold S & Hageman, John R
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Wind-tunnel investigation at low speed of a wing having 63 degree sweepback and a drooped tip

Wind-tunnel investigation at low speed of a wing having 63 degree sweepback and a drooped tip

Date: April 7, 1955
Creator: Blackaby, James R
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Wind-tunnel investigation at low speed of a wing swept-back 63 degrees and twisted and cambered for a uniform load at a lift coefficient of 0.5

Wind-tunnel investigation at low speed of a wing swept-back 63 degrees and twisted and cambered for a uniform load at a lift coefficient of 0.5

Date: May 9, 1950
Creator: Weiberg, James A & Carel, Hubert C
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Wind-tunnel investigation at low speed of a wing swept back 63 degrees and twisted and cambered for uniform load at a lift coefficient of 0.5 and with a thickened tip section

Wind-tunnel investigation at low speed of a wing swept back 63 degrees and twisted and cambered for uniform load at a lift coefficient of 0.5 and with a thickened tip section

Date: November 21, 1950
Creator: Weiberg, James A & Carel, Hubert C
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Wind Tunnel Investigation at Low Speed of Aerodynamic Characteristics of Army Chemical Corps Model E-112 Bomblets with Span Chord Ratio of 2 - 1

Wind Tunnel Investigation at Low Speed of Aerodynamic Characteristics of Army Chemical Corps Model E-112 Bomblets with Span Chord Ratio of 2 - 1

Date: December 26, 1956
Creator: Letko, W.
Description: An experimental investigation has been made in the Langley stability tunnel to determine the aerodynamic characteristics of the Army Chemical Corps model E-112 bomblets with span-chord ratio of 2:1. A detailed analysis has not been made; however, the results showed that all the models were spirally unstable and that a large gap between the model tips and end plates tended to reduce the instability.
Contributing Partner: UNT Libraries Government Documents Department
Wind-tunnel investigation at low speed of an unswept untapered semispan wing of aspect ratio 3.13 equipped with various 25-percent-chord plain flaps

Wind-tunnel investigation at low speed of an unswept untapered semispan wing of aspect ratio 3.13 equipped with various 25-percent-chord plain flaps

Date: April 1, 1950
Creator: Johnson, Harold S & Hagerman, John R
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Wind-tunnel investigation at low speed of effect of size and position of closed air ducts on static longitudinal and static lateral stability characteristics of unswept-midwing models having wings of aspect ratio 2, 4, and 6

Wind-tunnel investigation at low speed of effect of size and position of closed air ducts on static longitudinal and static lateral stability characteristics of unswept-midwing models having wings of aspect ratio 2, 4, and 6

Date: September 1, 1955
Creator: Jaquet, Byron M & Williams, James L
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Wind-tunnel investigation at low speed of effects of sideslip on static longitudinal trim and static lateral stability characteristics of three fighter-type airplane models

Wind-tunnel investigation at low speed of effects of sideslip on static longitudinal trim and static lateral stability characteristics of three fighter-type airplane models

Date: September 11, 1956
Creator: Jaquet, Byron M & Fletcher, H S
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Wind-tunnel investigation at low speed of sideslipping, rolling, yawing, and pitching characteristics for a model of a 45 degree swept-wing fighter-type airplane

Wind-tunnel investigation at low speed of sideslipping, rolling, yawing, and pitching characteristics for a model of a 45 degree swept-wing fighter-type airplane

Date: September 1, 1955
Creator: Jaquet, Byron M & Fletcher, H S
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Wind-tunnel investigation at low speed of static and yawing characteristics of a 0.085-scale model of the Chance Vought XF8U-1 airplane : TED No. NACA DE 392

Wind-tunnel investigation at low speed of static and yawing characteristics of a 0.085-scale model of the Chance Vought XF8U-1 airplane : TED No. NACA DE 392

Date: January 19, 1954
Creator: Jaquet, Byron M & Williams, James L
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Wind Tunnel Investigation at Low Speed of the Aerodynamic Characteristics of the Army Chemical Corps Model E112 Bomblets

Wind Tunnel Investigation at Low Speed of the Aerodynamic Characteristics of the Army Chemical Corps Model E112 Bomblets

Date: November 4, 1955
Creator: Letko, W. & Williams, J. L.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Wind-tunnel investigation at low speed of the aerodynamic characteristics of the Army Chemical Corps model E112 bomblets

Wind-tunnel investigation at low speed of the aerodynamic characteristics of the Army Chemical Corps model E112 bomblets

Date: November 4, 1955
Creator: Letko, William & Williams, James L
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Wind-tunnel investigation at low speed of the effects of chordwise wing fences and horizontal-tail position on the static longitudinal stability characteristics of an airplane model with a 35 degree sweptback wing

Wind-tunnel investigation at low speed of the effects of chordwise wing fences and horizontal-tail position on the static longitudinal stability characteristics of an airplane model with a 35 degree sweptback wing

Date: January 1, 1954
Creator: Queijo, M J; Jaquet, Byron M & Wolhart, Walter D
Description: Low-speed tests of a model with a wing swept back 35 degrees at the 0.33-chord line and a horizontal tail located well above the extended wing-chord plane indicated static longitudinal instability at moderate angles of attack for all configurations tested. An investigation therefore was made to determine whether the longitudinal stability could be improved by the use of chordwise wing fences, by lowering the horizontal tail, or by a combination of both. The results of the investigation showed that the longitudinal stability characteristics of the model with slats retracted could be improved at moderate angles of attack by placing chordwise wing fences at a spanwise station of about 73 percent of the wing semispan from the plane of symmetry provided the nose of the fence extended slightly beyond or around the wing leading edge.
Contributing Partner: UNT Libraries Government Documents Department
Wind-tunnel investigation at low speed of the effects of symmetrical deflection of half-delta tip controls on the damping in roll and yawing moment due to rolling of a triangular-wing model

Wind-tunnel investigation at low speed of the effects of symmetrical deflection of half-delta tip controls on the damping in roll and yawing moment due to rolling of a triangular-wing model

Date: April 6, 1951
Creator: Wolhart, Water D
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Wind-tunnel investigation at low speed of the lateral control characteristics of ailerons having three spans and three trailing-edge angles on a semispan wing model

Wind-tunnel investigation at low speed of the lateral control characteristics of ailerons having three spans and three trailing-edge angles on a semispan wing model

Date: November 1, 1948
Creator: Schneiter, Leslie E & Naeseth, Rodger L
Description: None
Contributing Partner: UNT Libraries Government Documents Department