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 Collection: National Advisory Committee for Aeronautics Collection
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 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