National Advisory Committee for Aeronautics (NACA) - 743 Matching Results

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Wind-Tunnel Investigation of the Stability and Control Characteristics of a Complete Model Equipped With a Vee Tail

Description: Note presenting a wind-tunnel investigation to determine the low-speed stability and control characteristics of a complete model equipped with a vee tail. Tail dihedral angles of 35, 47, and 55 degrees were tested and the results were compared with results of tests of a conventional-tail arrangement used with the same wing-fuselage combination. The 47 degree vee tail was found to be the best-performing when lateral and longitudinal stability were concerned, and it contributed 40 percent more st… more
Date: November 1947
Creator: Polhamus, Edward C. & Moss, Robert J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Wind-tunnel investigation of unshielded horn balances on a horizontal tail surface

Description: Report presenting a wind-tunnel investigation to determine the aerodynamic characteristics of a horizontal tail surface with various amounts of unshielded horn balance and with the surface condition similar to that of a typical fabric-covered elevator.
Date: July 1947
Creator: Lowry, John G. & Crandall, Stewart M.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Wind-Tunnel Investigation of Wing Inlets for a Four-Engine Airplane

Description: Report presenting an investigation in the propeller-research tunnel to develop wing-leading-edge inlets for locations between the inboard and outboard nacelles on each wing of a four-engine airplane. Testing was performed on the basic wing and original inlet as well as NACA-developed inlets for two versions of the airplane.
Date: March 11, 1947
Creator: Bartlett, Walter A., Jr. & Goral, Edwin B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Wind-Tunnel Investigations on a Changed Mustang Profile with Nose Flap Force and Pressure-Distribution Measurements

Description: "Measurements are described which were taken in the large wind tunnel of the AVA on a rectangular wing "Mustang 2" with nose flap of a chord of 10 percent. Besides force measurements the results of pressure-distribution measurements are given and compared with those on the same profile "without" nose flap" (p. 1).
Date: September 1947
Creator: Krüger, W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Wind-Tunnel Tests of a 0.182-Scale Model of an F4U-1 Airplane with External Stores

Description: Tests were made in the Langley 7- by 10-foot tunnel on a 0.182-scale model of an F4U-1 airplane with external stores. This paper is concerned mainly with presenting the data obtained in this investigation and with a comparison of some of these data with flight-test results determining the feasibility of estimating flight buffet Mach number from tunnel data. The results of this investigation indicate that the incremental drag coefficient due to external stores may be used to estimate the maximum… more
Date: June 5, 1947
Creator: Silvers, H. Norman & Spreemann, Kenneth P.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Wind-Tunnel Tests of a 1/4-Scale Model of the Naval Aircraft Factory Float-Wing Convoy Interceptor, TED No. NACA 2314

Description: A 1/4 - scale model of the Naval Aircraft Factory float-wing convoy interceptor was tested in the Langley 7-by 10-foot tunnel to determine the longitudinal and lateral stability characteristics. The model was tested in the presence of a ground board to determine the effect of simulating the ground on the longitudinal characteristics.
Date: January 16, 1947
Creator: Wells, Evalyn G. & McKinney, Elizabeth G.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Wind-Tunnel Tests of a 1/8-Scale Powered Model of the XTB3F-1 Airplane, TED No. NACA 2382

Description: "A 1/8 scale model of the Grumman XTB3F-1 airplane was tested in the Langley 7- by 10-foot tunnel to determine the stability and control characteristics and to provide data for estimating the airplane handling qualities. The report includes longitudinal and lateral stability and control characteristics of the complete model, the characteristics of the isolated horizontal tail, the effects of various flow conditions through the jet duct, tests with external stores attached to the underside of th… more
Date: August 1947
Creator: McKee, John W. & Vogler, Raymond D.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Wind-Tunnel Tests of the 1/25-Scale Powered Model of the Martin JRM-1 Airplane. 4 - Tests with Ground Board and with Modified Wing and Hull - TED No. NACA 232, Part 4, Tests with Ground Board and with Modified Wing and Hull, TED No. NACA 232

Description: From Summary: "Wind-tunnel tests were made of a 1/25 scale model of the Martin JRM-1 airplane to determine: (1) The longitudinal stability and control characteristics of the JRM-1 model near the water and lateral and directional stability characteristics with power while moving on the surface of the water, the latter being useful for the design of tip floats; (2) The stability and stalling characteristics of the wing with a modified airfoil contour; (3) Stability characteristics of a hull of la… more
Date: September 4, 1947
Creator: Lockwood, Vernard E. & Smith, Bernard J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Wing-flow tests of a triangular wing of aspect ratio two 1: effectiveness of several types of trailing-edge flaps on flat-plate models

Description: Report presenting an investigation of the problem of applying controls to low-aspect-ratio wings of triangular plan form by using the NACA wing-flow method with parallel-sided models with sharp leading and trailing edges. Results regarding the data analysis, Reynolds number and separation effects, flap effectiveness, plan-form characteristics, angle of zero lift, and triangular plan-form flying-wing characteristics are provided.
Date: November 14, 1947
Creator: Rathert, George A., Jr. & Cooper, George E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Wing plan forms for high-speed flight

Description: From Summary: "It is pointed out that, in the case of an airfoil of infinite aspect ratio moving at an angle of sideslip, the pressure distribution is determined solely by that component of the motion in a direction normal to the leading edge. It follows that the attachment of plane waves to the airfoil at near-sonic or supersonic speeds (Ackeret theory) may be avoided and the pressure drag may be reduced by the use of plan forms in which the angle of sweepback is greater than the Mach angle."
Date: 1947
Creator: Jones, Robert T.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Wing Pressure-Distribution Measurements Up to 0.866 Mach Number in Flight on a Jet-Propelled Airplane

Description: Report presenting flight testing to determine scale and compressibility effects on the pressure distributions over a wing with an NACA low-drag profile. No compressibility effects on spanwise wing loading were noted below Mach number 0.75, but above that number, an inboard lateral shift of load occurred that is primarily due to the upfloating of the ailerons.
Date: March 1947
Creator: Brown, Harvey H. & Clousing, Lawrence A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Yaw Characteristics and Sidewash Angles of a 42 Degree Sweptback Circular-Arc Wing With a Fuselage and With Leading-Edge and Split Flaps at a Reynolds Number of 5,300,000

Description: Report presenting testing of the low-speed aerodynamic characteristics in yaw of a 42 degree sweptback wing of circular-arc airfoil sections in the pressure tunnel. The wing had an aspect ratio of 3.94, taper ratio of 0.625, and no dihedral or twist. Results regarding lateral-stability parameters of plain wing, effect of wing flaps on lateral-stability parameters, effect of fuselage on lateral-stability parameters, a comparison with the NACA 64(sub 1)-112 wing, characteristics in the extended y… more
Date: December 10, 1947
Creator: Salmi, Reino J. & Fitzpatrick, James E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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