National Advisory Committee for Aeronautics (NACA) - 371 Matching Results

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Effect of airfoil profile of symmetrical sections on the low-speed static-stability and yawing derivatives of 45 degrees sweptback wing models of aspect ratio 2.61

Description: Report presenting an investigation in the stability tunnel to determine the effect of airfoil profile on symmetrical sections on the static- and yawing-stability derivatives of three untapered wings of 45 degrees sweepback. All of the wings had an aspect ratio of 2.61. Results regarding the characteristics in straight flow, yawing flow, and drag index are provided.
Date: November 9, 1948
Creator: Letko, William & Jaquet, Byron M.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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NACA Investigation of Fuels Corresponding to Specification an-F-58 : Results of Studies in Single Combustors of J-33, J-34, J-35, and Nene Turbojet Engines

Description: "The NACA is engaged in a program to evaluate the performance of fuels conforming to AN-F-58 specification in both full-scale engines and single combustors. This research memorandum constitutes an interim report on the results obtained on single cosibustors" (p. 1).
Date: November 16, 1945
Creator: Cleveland Laboratory Staff
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Aerodynamic Characteristics of Flying-Boat Hulls Having Length-Beam Ratios of 20 and 30

Description: Report discussing the aerodynamic effects of length-beam ratios 20 and 30 as compared to length-beam ratios from 6 to 15. There was slightly more longitudinal stability and slightly less directional stability than in the lower ratios and not much change in the minimum drag coefficient.
Date: November 10, 1948
Creator: Riebe, John M.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Investigation of a Thin Wing of Aspect Ratio 4 in the Ames 12-Foot Pressure Wind Tunnel 3: The Effectiveness of a Constant-Chord Aileron

Description: Report presenting a wind-tunnel investigation at a range of Mach numbers with a constant Reynolds number of a semispan model of a thin, unswept wing of aspect ratio 4 and taper ratio 0.5 with a constant-chord aileron and a modified diamond profile. Results regarding lift and rolling-moment characteristics and aileron effectiveness are provided.
Date: November 19, 1948
Creator: Johnson, Ben H., Jr. & Demele, Fred A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Preliminary Study of Use of Nonstrategic Metals for and Application of Cooling to Blades of Turbine of J35 Turbojet Engine

Description: Memorandum presenting the modifications to the J35 engine that are necessitated with the use of non-strategic materials. Two proposals for cooling the rotor disk and blades are: finned hollow blades that are air cooled and blades with circular passages for liquid cooling in which the fuel could be used as the coolant.
Date: November 17, 1948
Creator: Turbine Cooling Research Branch
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Investigation of spark gaps subjected to altitude and air velocity conditions

Description: Report presenting a study of the effects of air velocity on the energy and power of the spark in a constant ignition source and the duration of the spark discharge in the spark gap for various conditions of electrode spacing, electrode diameter, air temperature, and pressure. Energy and average power increased with pressure, velocity, and electrode spacing and electrode diameter and air temperature had negligible effect.
Date: November 24, 1948
Creator: Swett, Clyde C., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Yaw Characteristics of a 52 Degree Sweptback Wing of NACA 64(Sub 1)-112 Section With a Fuselage and With Leading-Edge and Split Flaps at Reynolds Numbers From 1.93 X 10(Exp 6) to 6.00 X 10(Exp 6)

Description: Report presenting low-speed testing in the pressure tunnel to determine the aerodynamic characteristics in yaw of a 52 degree sweptback wing with aspect ratio 2.88 and taper ratio 0.625 with NACA 64(sub 1)-112 airfoil sections. Testing included an investigation of the effects on the lateral stability of a fuselage and leading-edge and split flaps. Results regarding the lateral stability parameters of a plain wing, effect of flaps on the lateral stability parameters, effect of scale, and airflow… more
Date: November 8, 1948
Creator: Salmi, Reino J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Theoretical and Experimental Analysis of Low-Drag Supersonic Inlets Having a Circular Cross Section and a Central Body at Mach Numbers of 3.30, 2.75, and 2.45

Description: Memorandum presenting a discussion of inlets with a circular cross section and a central body designed for high Mach numbers. The optimum proportion between external and internal supersonic compression is discussed in relation to the external drag and the maximum pressure recovery. Results and analysis regarding the maximum pressure recovery as a function of the cowling position parameter, the effect of the cone angle parameter on the maximum pressure recovery obtained, the highest pressure rec… more
Date: November 10, 1948
Creator: Ferri, Antonio & Nucci, Louis M.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Static longitudinal stability and control of a convertible-type airplane as affected by articulated- and rigid-propeller operation

Description: Report presenting the results of an investigation in the full-scale tunnel of the static longitudinal stability and control of a convertible-type airplane as affected by articulated- and rigid-propeller operation. The investigation included force measurements for a large angle-of-attack range with the all-movable horizontal tail installed and removed.
Date: November 7, 1949
Creator: Lange, Roy H. & McLemore, Huel C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Low-speed static longitudinal stability characteristics of a canard model having a 60 degrees triangular wing and horizontal tail

Description: Report presenting an investigation of the low-speed, power-off static longitudinal stability and control characteristics of a canard model with a triangular wing and horizontal tail in the free-flight tunnel. Results regarding the horizontal tail used to overcome change in stability and horizontal tail used for longitudinal control are provided.
Date: November 9, 1949
Creator: Bates, William R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Analysis and Experimental Observation of Pressure Losses in Ram-Jet Combustion Chambers

Description: From Introduction: "Some experimental data on flame-holder pressure losses have been presented (reference 1 to 4). A theoretical analysis that assume a sudden enlargement of flow area was made at the NACA Lewis laboratory to determine the effect of flame-holder open area and combustion-chamber-inlet Mach number on the pressure losses across flame holders. The results of this analysis were then compared with experimental data obtained with several different flame-holder designs."
Date: November 4, 1949
Creator: Sterbentz, William H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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An Investigation of the Characteristics of an Unswept Wing of Aspect Ratio 4.01 in the Langley 8-Foot High-Speed Tunnel

Description: Report presenting an investigation of the characteristics of a low-aspect-ratio wing at high subsonic Mach numbers in the high-speed tunnel. The wing model had an NACA 65-108 airfoil section, an aspect ratio of 4.01, a taper ratio of 0.498, and no twist or dihedral. Results regarding normal-force characteristics, pitching-moment characteristics, and drag characteristics are provided.
Date: November 8, 1949
Creator: Bielat, Ralph P. & Cahn, Maurice S.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Investigation of Some Turbulent-Boundary-Layer Velocity Profiles at a Tunnel Wall with Mach Numbers up to 1.2

Description: Report presenting turbulent-boundary-layer profiles at large Reynolds numbers and with Mach numbers up to 1.2. In this investigation, velocity profile shapes were substantially unaffected by compressibility. Results regarding the temperature considerations, velocity profiles, and turbulent boundary layer under normal shock are provided.
Date: November 9, 1949
Creator: Tulin, Marshall P. & Wright, Ray H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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High-speed aerodynamic characteristics of a lateral-control model 3: section characteristics, fence studies, and tabulated pressure coefficients with modified NACA 0012-64 section, 26.6-percent-chord, plain aileron, 0 and 45 degree sweepback

Description: Report presenting wind-tunnel measurements of the pressure distribution on a semispan wing with a modified NACA 0012-64 airfoil section and a plain trailing-edge aileron with the wing unswept and also swept back 45 degrees. Adverse changes in loading and loss of aileron effectiveness developed with the wing unswept as the Mach number was increased, but did not occur at Mach numbers up to 0.925 with the swept wing. Results regarding section characteristics and effect of fences are provided.
Date: November 22, 1950
Creator: Krumm, Walter J. & Cleary, Joseph W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Investigation of the Dynamic Longitudinal Stability of Two Equal Size Models Coupled in Tandem with a Single Joint: Preliminary Model Flight Tests

Description: Report presenting an investigation in the free-flight tunnel to study the dynamic longitudinal stability of equal-size models coupled in tandem with a single joint providing freedom in pitch. Results regarding the characteristics of the model motions, effect of elevator gearing ratio, effect of weight ratio, and effect of static stability of the front model are provided.
Date: November 13, 1950
Creator: Shanks, Robert E. & Grana, David C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Comparison of Transonic Characteristics of Lifting Wings From Experiments in a Small Slotted Tunnel and the Langley High-Speed 7- by 10-Foot Tunnel

Description: Report presenting a comparison of the transonic aerodynamic characteristics of unswept and 45 degree sweptback wings in the high-speed tunnel and slotted tunnel. The purpose of the investigation was to explore the possibilities and limitations associated with transonic testing of relatively large wings in a rectangular slotted tunnel. Results regarding lift, pitching moments, drag, bending moments, and Schileren photographs are provided.
Date: November 5, 1951
Creator: Sleeman, William C., Jr.; Klevatt, Paul L. & Linsley, Edward L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Correlation of forced-convection heat-transfer data for air flowing in smooth platinum tube with long-approach entrance at high surface and inlet-air temperatures

Description: A heat-transfer investigation was conducted with air in an electrically heated platinum tube with long-approach entrance, inside diameter of 0.525 inch, and effective heat-transfer length of 24 inches over ranges of Reynolds number up to 320,000, average inside-tube-wall temperature up to 3053 degrees R, and inlet-air temperature up to 1165 degrees R. Correlation of data by the conventional Nusselt relation resulted in separation of data with tube-wall temperature. Good correlation was obtained… more
Date: November 2, 1950
Creator: Desmon, Leland G. & Sams, Eldon W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Tabulated pressure coefficients and aerodynamic characteristics measured on the wing of the Bell X-1 airplane in pull-ups at Mach numbers from 0.53 to 0.99

Description: "Tabulated pressure coefficients and aerodynamic characteristics are presented for six spanwise stations on the left wing of the Bell X-1 research airplane. The data were obtained in 10 pull-ups at Mach numbers from 0.53 to 0.99" (p. 1).
Date: November 1950
Creator: Knapp, Ronald J. & Wilken, Gertrude V.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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An investigation of three transonic fuselage air inlets at Mach numbers from 0.4 to 0.94 and at a Mach number of 1.19

Description: Report presenting an investigation of three air inlets designed for use at transonic speeds conducted in the 8-foot high-speed tunnel. The basis of the design of the inlets was the use of a nose which was shaped so that substream velocities are maintained on its surface for high-speed operating conditions. Results regarding impact pressure recovery, external pressure distributions, wake-survey drag, supersonic external pressure drag, and design considerations are provided.
Date: November 7, 1950
Creator: Pendley, Robert E.; Robinson, Harold L. & Williams, Claude V.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Fundamental flame velocities of pure hydrocarbons 2: alkadienes

Description: Data are presented for the fundamental flame velocities of 10 pure alkadienes that have isolated, conjugated, or cumulative double-bond systems. On the basis of this limited amount of data and the flame velocities previously reported, it is concluded that unsaturation changes the flame velocity in the order alkanes ? alkenes ? alkadienes with isolated double bonds ?= alkadienes with conjugated double bonds ? alkadienes with cumulative double bonds ?= alkynes. There were no significant differenc… more
Date: November 3, 1950
Creator: Levine, Oscar; Wong, Edgar L. & Gerstein, Melvin
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Effects of molding conditions on some physical properties of glass-fabric unsaturated-polyester laminates

Description: Report presenting an investigation of the effects of several molding conditions on the physical properties of laminates prepared with Fiberglass 181 glass fabric and Bakelite XRS-81 unsaturated-polyester resin. The molding variables included pressure, temperature, and time during both precuring and curing operations. The laminates were tested for several physical properties including resin content, percentage of voids, specific gravity, and flexural strength on the diagonal, both wet and dry.
Date: November 9, 1950
Creator: Wier, John E.; Pons, Dorothy C. & Axilrod, Benjamin M.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Theoretical Analyses to Determine Unbalanced Trailing-Edge Controls Having Minimum Hinge Moments Due to Deflection at Supersonic Speeds

Description: Memorandum presenting analyses based on theoretical results of NACA Report 1041 to determine the plan forms of unbalanced trailing-edge flap-type controls with minimum hinge moments due to deflection and requiring minimum work to overcome the hinge moments due to deflection at supersonic speeds. Results of the analyses for longitudinal controls show high-aspect-ratio untapered controls to possess maximum ratios of lift to hinge moment. Results regarding ratios of lift to hinge moment, ratios of… more
Date: November 19, 1952
Creator: Goin, Kennith L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

A Transonic Wing Investigation in the Langley 8-Foot High-Speed Tunnel at High Subsonic Mach Numbers and at a Mach Number of 1.2 : Wing-Fuselage Configuration Having a Wing of 35 Degrees Sweepback, Aspect Ratio 4, Taper Ratio 0.6, and NACA 65A006 Airfoil Section

Description: Report presenting an investigation to determine the aerodynamic characteristics of a wing-fuselage configuration with a wing with quarter-chord line swept back 35 degrees, an aspect ratio of 4, a taper ratio of 0.6, and an NACA 65A006 airfoil section. Lift, drag, and pitching-moment characteristics, downwash angles, and wake characteristics for various angles of attack and Mach numbers are provided.
Date: November 15, 1950
Creator: Henry, Beverly Z., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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