National Advisory Committee for Aeronautics (NACA) - 18 Matching Results

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Characteristics of a Sealed Internally Balanced Aileron from Tests of a 1/4-Scale Partial-Span Model of the Republic XF-12 Airplane in the Langley 19-Foot Pressure Tunnel

Description: This paper presents the results of the aileron investigation and includes rolling-moment, yawing-moment, and aileron hinge-moment coefficients and pressure coefficients across the aileron-balance seal through a range of angle of attack, tab deflection, and aileron deflection with flaps neutral and deflected 20 degrees and 55 degrees. Some of the effects of wing roughness and balance seal leakage on the aileron and tab characteristics are also presented.
Date: November 1, 1946
Creator: Graham, Robert R.; Martina, Albert P. & Salmi, Reino J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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An Estimation of the Flying Qualities of the Kaiser Fleetwing All-Wing Airplane from Tests of a 1/7-Scale Model, TED No. NACA 2340

Description: "An investigation of a 1/7-scale powered model of the Kaiser Fleetwing all-wing airplane was made in the Langley full-scale tunnel to provide data for an estimation of the flying qualities of the airplane. The analysis of the stability and control characteristics of the airplane has been made as closely as possible in accordance with the requirements of the Bureau of Aeronautics, Navy Department's specifications, and a summary of the more significant conclusions is presented as follows. With th… more
Date: November 1, 1946
Creator: Brewer, Gerald W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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An empirically derived method for calculating pressure distribution at supercritical Mach numbers and moderate angles of attack

Description: Report presenting a procedure for calculating pressure distributions over airfoils at supercritical Mach numbers. Only the forward portion of the airfoil, where interaction between local boundary-layer thickness and local-pressure distribution is negligible, is considered in detail. The method cannot be considered definitive because it requires that certain characteristics regarding pressure distributions and geometric properties be known.
Date: April 1, 1947
Creator: Nitzberg, Gerald E. & Sluder, Loma E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Cooling of Gas Turbines 6 - Computed Temperature Distribution Through Cross Section of Water-Cooled Turbine Blade

Description: "A theoretical analysis of the cross-sectional temperature distribution of a water-cooled turbine blade was made using the relaxation method to solve the differential equation derived from the analysis. The analysis was applied to specific turbine blade and the studies icluded investigations of the accuracy of simple methods to determine the temperature distribution along the mean line of the rear part of the blade, of the possible effect of varying the perimetric distribution of the hot gas-to… more
Date: May 1, 1947
Creator: Livingood, John N. B. & Sams, Eldon W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Flight Measurements of the Flying Qualities of a Lockheed P-80A Airplane (Army No. 44-85099): Longitudinal-Stability and -Control Characteristics

Description: This report contains the flight-test results of the longitudinal-stability and -control phase of a general flying qualities investigation of the Lockheed P-80A airplane (Army No. 44-85099). The tests were conducted at indicated airspeeds up to 530 miles per hour (0.76 Mach number) at low altitude and up to 350 miles per hour (0.82) Mach number) at high altitude. These tests showed that the flying qualities of the airplane were in accordance with the requirements of the Army Air Forces Stability… more
Date: July 1, 1947
Creator: Anderson, Seth B.; Christofferson, Frank E. & Clousing, Lawrence A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Fuel investigation in a tubular-type combustor of a turbojet engine

Description: A series of 11 fuels ranging in volatility and including various types of hydrocarbons were tested in a single tubular combustion chamber of a turbojet engine under inlet-air conditions simulating engine operation at two speeds at an altitude of 40,000 feet. Temperature-rise data at various fuel-air ratios were obtained for each set of air-flow conditions. Results regarding the effect of combustor inlet-air conditions on temperature rise, four different series of tests, and a review of some gen… more
Date: August 1, 1947
Creator: Tischler, Adelbert O. & Dittrich, Ralph T.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Flight Tests of Rocket-Powered "Tin-Can" Models of AAF Project MX-800

Description: Flight tests were made of six noninstrumented rocket-powered "Tin Can" models of AAF Project MX-800. Velocity and drag data were obtained by use of CU Doppler radar. The existence of stability and adequate structural strength for flight near zero lift was checked by visual and photographic observation. Drag data obtained during the tests agreed reasonably well with estimates based on experimental data from NACA RM-2 rocket-powered drag research models.
Date: December 1, 1947
Creator: Purser, Paul E. & Stone, David G.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Pressure recovery at supersonic speeds through annular duct inlets situated in a region of appreciable boundary layer 1: addition of energy to the boundary layer

Description: Report presenting a model with a nozzle upstream of an annular duct inlet for the purpose of ejecting high-velocity air into the boundary layer of the flow along the forebody tested between Mach numbers of 1.36 and 2.01. Results wind-tunnel data, equivalent pressure recovery, and scale effects are provided.
Date: April 1, 1948
Creator: Davis, Wallace F. & Brajnikoff, George B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The Influence of Dimensional Modifications upon the Spin and Recovery Characteristics of a Tailless Airplane Model Having Its Wings Swept Forward 15 Degrees (Cornelius XFG-1)

Description: "An investigation has been conducted in the Langley 20-foot free- spinning tunnel scale model of the Cornelius XFG-1 glider, a tailless design having its wings swept forward 15 degrees. It was previously found to possess erratic spin and recovery characteristics, and tests were made to determine modifications which would lead to normal steady spins with consistently good recoveries. The results of the investigation indicated that modifications that aid not appreciably alter the basic design aid… more
Date: September 1, 1948
Creator: Stone, Ralph W., Jr. & Daughtridge, Lee T., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Investigation of Flow Conditions and the Nature of the Wall-Constriction Effect Near and at Choking by Means of the Hydraulic Analogy

Description: Report presenting an investigation of the closed wind-tunnel phenomenon of choking and the wall-constriction effects in the subsonic Mach number range where supersonic Mach numbers appear using the hydraulic analogy. Application of the results to wind tunnel testing, the subsonic choking phenomena, and effects of the walls are described.
Date: September 1, 1948
Creator: Matthews, Clarence W. & Wright, Ray H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Aerodynamic characteristics at high speeds of a two-blade NACA 10-(3)(062)-045 propeller and of a two-blade NACA 10-(3)(08)-045 propeller

Description: From Introduction: "The aerodynamic characteristics of a series of 10-foot-diameter propellers are being investigated in the Langley 16-foot high-speed tunnel in a comprehensive propeller research program. Using high-critical-speed NACA 16-series airfoil sections (reference 1), these propellers are designed to have Betz minimum induced-energy loss loading (reference 2) for a blade angle of 45^o at the 0.7 radius, when used as a four-blade propeller operating at an advance ratio of approximately… more
Date: October 1, 1948
Creator: Solomon, William
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Investigation of downwash and wake characteristics at a Mach number of 1.53 1: rectangular wing

Description: The results of an experimental investigation of the downwash and wake characteristics behind a rectangular plan-form wing of aspect ratio 3.5 are presented. The airfoil section was a 5-percent-thick, symmetrical double wedge. The tests were made at a Mach number of 1.53 and a Reynolds number of 1.25 million. A comparison between experimental and theoretical values of the downwash angles is made.
Date: March 1, 1949
Creator: Perkins, Edward W. & Canning, Thomas N.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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An Experimental Investigation at Large Scale of Single and Twin Naca Submerged Side Intakes at Several Angles of Sideslip

Description: Report presenting the results of an experimental investigation to determine the pressure-recovery and mass-flow characteristics of single and twin NACA submerged intakes on the sides of a fuselage at various angles of sideslip. Tests were conducted with single and twin submerged intakes on a model of a fighter-type airplane.
Date: August 1, 1949
Creator: Martin, Norman J. & Holzhauser, Curt A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Experimental investigation of rim cracking in disks subjected to high temperature gradients

Description: Report presenting the results of an experimental investigation of rim cracking in a welded-blade composite gas-turbine wheel, in two carbon-steel disks, and five tool-steel disks. Various characteristics were investigated, including the effectiveness of holes in preventing crack propagation and the influence of hardness and various types of notch on rim cracking.
Date: September 1, 1949
Creator: Wilterdink, P. I.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Investigation of Internal Regenerative Fuel-Heating System for 20-Inch Ram Jet

Description: Memorandum presenting an investigation conducted to evaluate the effectiveness of a simple internal regenerative fuel preheater for a 20-inch-diameter ram jet. Data obtained at subsonic sea-level conditions indicated that fuel could be successfully preheated in this manner.
Date: September 1, 1949
Creator: Baker, Sol & Perchonok, Eugene
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Aerodynamic Characteristics of a Wing With Quarter-Chord Line Swept Back 45 Degrees, Aspect Ratio 6, Taper Ratio 0.6, and NACA 65A006 Airfoil Section

Description: Report discussing a wing-alone and wing-fuselage configuration with particular characteristics as part of a series of tests of wings using the transonic-bump test technique. Lift, drag, pitching moment, and root bending moment were obtained for the configurations. The effective downwash angles and dynamic-pressure characteristics in the tail region are also described.
Date: November 1, 1949
Creator: Goodson, Kenneth W. & Few, Albert G., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Reduction of profile drag at supersonic velocities by the use of airfoil sections having a blunt trailing edge

Description: Report presenting a preliminary theoretical and experimental investigation of the supersonic characteristics of blunt-trailing-edge airfoils. Results regarding the drag measurements at zero lift, measurements at angle of attack, and a general discussion of the theoretical and experimental results is provided.
Date: November 1, 1949
Creator: Chapman, Dean R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Effect of airfoil section and tip tanks on the aerodynamic characteristics at high subsonic speeds of an unswept wing of aspect ratio 5.16 and taper ratio 0.61

Description: Report presenting an investigation of the effect of two wing sections and a tip tank on the aerodynamic characteristics of a rigid unswept wing in the high-speed tunnel over a Mach number range of 0.60 to 0.90. Results regarding the effect of original airfoil sections, effect of modifications to Section B, effect of tip tank, and characteristics of the tip tank in the presence of the wing are provided.
Date: December 1, 1949
Creator: Silvers, H. Norman & Spreeman, Kenneth P.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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