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  Partner: UNT Libraries Government Documents Department
 Collection: National Advisory Committee for Aeronautics Collection
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
Wind-tunnel investigation at low speed of the lateral control characteristics of an unswept untapered semi-span wing of aspect ratio 3.13 equipped with various 25-percent-chord plain ailerons

Wind-tunnel investigation at low speed of the lateral control characteristics of an unswept untapered semi-span wing of aspect ratio 3.13 equipped with various 25-percent-chord plain ailerons

Date: October 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 the Pitching Stability Derivatives of a 1/9-Scale Powered Model of the Convair XFY-1 Vertically Rising Airplane, TED No. NACA DE 373

Wind-Tunnel Investigation at Low Speed of the Pitching Stability Derivatives of a 1/9-Scale Powered Model of the Convair XFY-1 Vertically Rising Airplane, TED No. NACA DE 373

Date: July 13, 1953
Creator: Queijo, M. J.; Wolhart, Walter D. & Fletcher, H. S.
Description: An experimental investigation has been conducted in the Langley stability tunnel at low speed to determine the pitching stability derivatives of a 1/9-scale powered model of the Convair XFY-1 vertically rising airplane. Effects of thrust coefficient, control deflections, and propeller blade angle were investigated. The tests were made through an angle-of-attack range from about -4deg to 29deg, and the thrust coefficient range was from 0 to 0.7. In order to expedite distribution of these data, no analysis of the data has been prepared for this paper.
Contributing Partner: UNT Libraries Government Documents Department
Wind-Tunnel Investigation at Low Speed of the Rolling Stability Derivatives of a 1/9-Scale Powered Model of the Convair XFY-1 Vertically Rising Airplane, TED No. NACA DE 373

Wind-Tunnel Investigation at Low Speed of the Rolling Stability Derivatives of a 1/9-Scale Powered Model of the Convair XFY-1 Vertically Rising Airplane, TED No. NACA DE 373

Date: May 20, 1953
Creator: Queijo, M. J.; Wolhart, Walter D. & Fletcher, H. S.
Description: An experimental investigation has been conducted in the Langley stability tunnel at low speed to determine the rolling stability derivatives of a 1/9-scale powered model of the Convair XFY-1 vertically rising airplane. Effects of thrust coefficient were investigated for the complete model and for certain components of the model. Effects of control deflections and of propeller blade angle were investigated for the complete model. Most of the tests were made through an angle-of-attack range from about -4deg to 29deg, and the thrust coefficient range was from 0 to 0.7. In order to expedite distribution of these data, no analysis of the data has been prepared for this paper.
Contributing Partner: UNT Libraries Government Documents Department
Wind-tunnel investigation at low speed of the rolling stability derivatives of a 1/10-scale model of the douglas a4d-1 airplane

Wind-tunnel investigation at low speed of the rolling stability derivatives of a 1/10-scale model of the douglas a4d-1 airplane

Date: January 1, 1954
Creator: Fletcher, H. S. & Wolhart, W. D.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Wind-tunnel investigation at low speed of the rolling stability derivatives of a 1/10-scale model of the Douglas A4D-1 airplane : TED No. NACA DE 389

Wind-tunnel investigation at low speed of the rolling stability derivatives of a 1/10-scale model of the Douglas A4D-1 airplane : TED No. NACA DE 389

Date: October 7, 1954
Creator: Wolhart, Walter D & Fletcher, H S
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Wind-Tunnel Investigation at Low Speed of the Rolling Stability Derivatives of a 1/10-Scale Model of the Grumman F9F-9 Airplane, TED No. NACA AD 3109

Wind-Tunnel Investigation at Low Speed of the Rolling Stability Derivatives of a 1/10-Scale Model of the Grumman F9F-9 Airplane, TED No. NACA AD 3109

Date: April 18, 1955
Creator: Wolhart, Walter D. & Thomas, David F., Jr.
Description: An experimental investigation has been made in the Langley stability tunnel to determine the low-speed yawing, pitching, and static stability characteristics of a 1/10-scale model of the Grumman F9F-9 airplane. Tests were made to determine the effects of duct-entrance-fairing plugs on the static lateral and longitudinal stability characteristics of the complete model in the clean condition. The remaining tests were concerned with determining tail contributions as well as the effect of duct-entrance-fairing plugs, slats, flaps, and landing gear on the yawing and pitching stability derivatives. These data are presented without analysis in order to expedite distribution.
Contributing Partner: UNT Libraries Government Documents Department
Wind-Tunnel Investigation at Low Speed of the Static Longitudinal and Lateral Stability Characteristics of a 1/9-Scale Powered Model of the Convair XFY-1 Vertically Rising Airplane

Wind-Tunnel Investigation at Low Speed of the Static Longitudinal and Lateral Stability Characteristics of a 1/9-Scale Powered Model of the Convair XFY-1 Vertically Rising Airplane

Date: February 11, 1953
Creator: Queijo, M. J.; Wolhart, W. D. & Fletcher, H. S.
Description: An experimental investigation has been made in the Langley stability tunnel at low speed to determine the static longitudinal and lateral stability characteristics of a l/9-scale powered model of the Convair XFY-1 vertically rising airplane. Effects of thrust coefficient were investigated for the complete model and for certain components of the model. Effects of control deflections and of propeller-blade angle were investigated briefly for the complete model. Most of the tests were made through an angle-of-attack range from about -4 deg. to 29 deg, and the thrust-coefficient range was from 0 t o 0.7. In order to expedite distribution of these data to interested persons, no analysis of the data has been prepared for this report,.
Contributing Partner: UNT Libraries Government Documents Department
Wind-Tunnel Investigation at Low Speed of the Yawing, Pitching, and Static Stability Characteristics of a 1/10-Scale Model of the Grumman F9F-9 Airplane, TED No. NACA AD 3109

Wind-Tunnel Investigation at Low Speed of the Yawing, Pitching, and Static Stability Characteristics of a 1/10-Scale Model of the Grumman F9F-9 Airplane, TED No. NACA AD 3109

Date: April 13, 1955
Creator: Wolhart, Walter D. & Thomas, David F., Jr.
Description: An experimental investigation has been made in the Langley stability tunnel to determine the low-speed yawing, pitching, and static stability characteristics of a 1/10-scale model of the Grumman F9F-9 airplane. Tests were made to determine the effects of duct-entrance-fairing plugs on the static lateral and longitudinal stability characteristics of the complete model in the clean condition. The remaining tests were concerned with determining tail contributions as well as the effect of duct-entrance-fairing plugs, slats, flaps, and landing gear on the yawing and pitching stability derivatives. These data are presented without analysis in order to expedite distribution.
Contributing Partner: UNT Libraries Government Documents Department
Wind-Tunnel Investigation at Low Speed of the Yawing Stability Derivatives of a 1/9-Scale Powered Model of the Convair XFY-1 Vertically Rising Airplane, TED No. NACA DE 373

Wind-Tunnel Investigation at Low Speed of the Yawing Stability Derivatives of a 1/9-Scale Powered Model of the Convair XFY-1 Vertically Rising Airplane, TED No. NACA DE 373

Date: March 1, 1953
Creator: Queijo, M. J.; Wolhart, w. D. & Fletcher, H. S.
Description: An experimental investigation has been conducted in the Langley stability tunnel at low speed to deter+nine the yawing stability derivatives of a 1/9-scale powered model of the Convair XFY-1 vertically rising airplane. Effects of thrust coefficient were investigated for the complete model and for certain components of the model. Effects of control deflections and of propeller blade angle were investigated for the complete model. Most of the tests were made through an angle-of-attack range from about -4deg to 29deg, and the thrust coefficient range was from 0 to 0.7. In order to expedite distribution of these data, no analysis of the data has been prepared for this.
Contributing Partner: UNT Libraries Government Documents Department
Wind-tunnel investigation at low speed of the yawing stability derivatives of a 1/10-scale model of the douglas a4d-1 airplane

Wind-tunnel investigation at low speed of the yawing stability derivatives of a 1/10-scale model of the douglas a4d-1 airplane

Date: January 1, 1954
Creator: Fletcher, H. S. & Wolhart, W. D.
Description: None
Contributing Partner: UNT Libraries Government Documents Department