National Advisory Committee for Aeronautics (NACA) - 13,806 Matching Results

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

Description: Report discussing an experimental investigation to determine the aerodynamic characteristics of the Army Chemical Corps model E112 bomblets. From Summary: "A detailed analysis has not been made; however, the results showed that a gap between model tips and the end plates or increasing the end-plate size for a solid model could result in a spirally stable configuration." A large amount of data collected from testing and photographs of the model are provided.
Date: November 4, 1955
Creator: Letko, William & Williams, James L.
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

Description: From Summary: "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."
Date: November 24, 1954
Creator: Queijo, M. J.; Jaquet, Byron M. & Wolhart, Walter D.
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

Description: Report presenting a low-speed investigation in the stability tunnel to determine the effects of symmetrical deflection of half-delta tip controls on the damping in roll and yawing moment due to rolling of a model with triangular wings. Triangular wings have numerous aerodynamic advantages, but it is difficult to obtain adequate longitudinal and lateral control with acceptable control forces when using them. Results regarding the lift characteristics and rolling characteristics are provided.
Date: April 6, 1951
Creator: Wolhart, Water D.
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

Description: Report presenting a wind-tunnel investigation at low speed to determine the lateral control characteristics of an unswept untapered semispan wing of aspect ratio 3.13 equipped with 25-percent-chord plain unsealed ailerons with various spans and spanwise locations. Results regarding wing aerodynamic characteristics and aileron control characteristics are provided.
Date: October 1950
Creator: Johnson, Harold S. & Hagerman, John R.
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

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.
Date: July 23, 1953
Creator: Queijo, M. J.; Wolhart, Walter D. & Fletcher, H. S.
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

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.
Date: May 20, 1953
Creator: Queijo, M. J.; Wolhart, Walter D. & Fletcher, H. S.
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

Description: Report discussing an experimental investigation of the low-speed rolling stability derivatives of a model of the Douglas A4D-1. The model was tested under a variety of conditions, including in clean and landing configurations and with the horizontal and vertical tails on and off, and the study also explored the effects of slats and flaps on the derivatives of the wing. No analysis of the data is provided.
Date: October 7, 1954
Creator: Wolhart, Walter D. & Fletcher, H. S.
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

Description: Report presenting an experimental investigation to determine the low-speed rolling stability derivatives of a scale model of the Douglas A4D-1. The model was tested in clean and landing configurations with horizontal and vertical tails on and off. The data is presented without analysis.
Date: October 7, 1954
Creator: Wolhart, Walter D. & Fletcher, H. S.
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

Description: From Summary: "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."
Date: May 2, 1955
Creator: Wolhart, Walter D. & Thomas, David F., Jr.
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

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,.
Date: February 11, 1953
Creator: Queijo, M. J.; Wolhart, W. D. & Fletcher, H. S.
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

Description: From Summary: "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."
Date: April 13, 1955
Creator: Wolhart, Walter D. & Thomas, David F., Jr.
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

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.
Date: March 31, 1953
Creator: Queijo, M. J.; Wolhart, W. D. & Fletcher, H. S.
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

Description: Report discussing testing of a model of the Douglas A4D-1 to determine its low-speed yawing stability derivatives. The model was tested in clean and landing configurations with horizontal and vertical tails on and off and an investigation into the effect of slats and flaps on the wing-alone derivatives.
Date: August 25, 1954
Creator: Wolhart, Walter D. & Fletcher, H. S.
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: TED No. NACA DE 389

Description: Report presenting an experimental investigation to determine the low-speed yawing stability derivatives of a model of the Douglas A4D-1 airplane. The model was tested in clean and landing configurations with horizontal and vertical tails on and off. Results are provided without analysis.
Date: September 13, 1954
Creator: Wolhart, Walter D. & Fletcher, H. S.
Partner: UNT Libraries Government Documents Department

A wind-tunnel investigation at low speed of various lateral controls on a 45 degree swept-back wing

Description: Report discussing an investigation into chord-extension controls, conventional ailerons, and spoilers on a 45 degree swept-back wing of aspect ratio 4.5 and taper ratio 0.5. Measurements of the lift, drag, pitching moments, rolling moments, and rates of roll produced by the various controls are described. The results on a semispan model and a full-span model are described.
Date: April 9, 1948
Creator: Hopkins, Edward J.
Partner: UNT Libraries Government Documents Department

Wind-tunnel investigation at low speeds of flight characteristics of a sweptback-wing jet-transport airplane model equipped with an external-flow jet-augmented slotted flap

Description: Report presenting a wind-tunnel investigation at low speeds to determine the flight characteristics of a model of a sweptback-wing jet-transport airplane equipped with an external-flow jet-augmented slotted flap. Results regarding the longitudinal stability characteristics, longitudinal control characteristics, lateral stability characteristics, and lateral control characteristics are provided.
Date: July 1958
Creator: Johnson, Joseph L., Jr.
Partner: UNT Libraries Government Documents Department

A wind-tunnel investigation at low speeds of the aerodynamic characteristics of various spoiler configurations on a thin 60 degrees delta wing

Description: Report presenting an investigation in the 300 mph tunnel to determine the applicability of spoilers as lateral-control devices on thin delta wings. The wing used in testing had a thickness ratio of 1.5 percent at the root and a maximum ratio of 4.5 percent at 66.7 percent wing semispan, 60 degree sweepback at the leading edge, 0 degree sweep of the trailing edge, an aspect ratio of 2.31, and a taper ratio of 0. Results regarding the effect of spoiler location and angular placement, effect of spanwise location, effect of spoiler projection, and effect of slots and perforations are presented.
Date: November 19, 1952
Creator: Wiley, Harleth G. & Solomon, Martin
Partner: UNT Libraries Government Documents Department

Wind-tunnel investigation at low speeds of the pitching derivatives of untapered swept wings

Description: Report presenting a wing-tunnel investigation in straight and pitching flow to determine the effects of independently varying aspect ratio and angle of sweep on the longitudinal rotary stability characteristics of a series of ten untapered wings. The investigation showed that an interdependent relationship existed between the effects of aspect ratio and sweep. Results regarding pitching moment due to pitching velocity and lift due to pitching velocity are provided.
Date: September 29, 1948
Creator: MacLachlan, Robert & Fisher, Lewis R.
Partner: UNT Libraries Government Documents Department

Wind-tunnel investigation at low speeds of various plug-aileron and lift-flap configurations on a 42 degree sweptback semispan wing

Description: Report presenting a wind-tunnel investigation on a 42 degree sweptback-wing model to determine the lateral control characteristics of a plug-aileron configuration. The configuration consisted of six segments extending from the wing 20-percent-span to the wing 80-percent-span stations and with the center of each plug on the wing 70-percent-chord line. Results regarding wing aerodynamic characteristics and lateral control characteristics are provided.
Date: January 26, 1949
Creator: Schneiter, Leslie E. & Watson, James M.
Partner: UNT Libraries Government Documents Department

Wind-tunnel investigation at low speeds to determine flow-field characteristics and ground influence on a model with jet-augmented flaps

Description: Report presenting a wind-tunnel investigation at low speeds to determine the flow-field characteristics and ground influence on an airplane model with an untapered, unswept wing with an aspect ratio of 8.3 equipped with jet-augmented flaps. Results regarding the effect of ground-board distance and flow-field characteristics are provided.
Date: September 1957
Creator: Vogler, Raymond D. & Turner, Thomas R.
Partner: UNT Libraries Government Documents Department

Wind-tunnel investigation at Mach 1.9 of multijet-missile base pressures

Description: From Summary: "An experimental wind-tunnel investigation was conducted at Mach 1.9 to determine the pressures acting on the base of a multijet missile using unheated air and carbon dioxide as jet fluids. The variation of base pressure with jet static-pressure ratio was compared with results estimated for an axisymmetric single-jet model and some correlation was observed."
Date: March 3, 1955
Creator: Baughman, L. Eugene
Partner: UNT Libraries Government Documents Department

Wind-tunnel investigation at Mach numbers from 0.6 to 1.4 of several ejected pilot-seat models

Description: From Summary: "The results are presented of an experimental investigation conducted to determine the static longitudinal and lateral-direction aerodynamic characteristics of basic and modified versions of a conventional upward ejected pilot-seat combination, a sled-type upward ejected pilot-seat combination, and a downward ejected pilot-seat combination." The drag coefficient, lift coefficient, rolling-moment coefficient, pitching-moment coefficient, yawing-moment coefficient, and side-force coefficient are provided.
Date: September 10, 1958
Creator: Summers, James L.
Partner: UNT Libraries Government Documents Department