National Advisory Committee for Aeronautics (NACA) - 4,160 Matching Results

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General Characteristics of a Airspeed System using Fuselage Static Vents on a Swept-Wing Airplane

Description: "Studies have been made by the NACA wing-flow method of the use of fuselage static orifices between the wing and tail of a swept-wing airplane for possible application to service airspeed installations. The tests were made at zero angle of attack. The results indicate that, although the maximum errors are large, these locations are usable from the consideration that the local Mach numbers at the locations studied are sensitive to variation of the true Mach number within the test Mach number ran… more
Date: November 3, 1949
Creator: Johnston, J. Ford & O'Bryan, Thomas C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Vibration of loosely mounted turbine blades during service operation of a turbojet engine with centrifugal compressor and straight-flow combustion chambers

Description: Report presenting an experimental investigation to determine the vibration characteristics of loosely mounted turbine blades during service operation of a turbojet engine. High-temperature strain gages were used to measure turbine-blade vibrations. Results regarding oscillograph records, critical speeds and frequencies, vibratory-stress levels, and effect of tightening the blade mount are provided.
Date: November 3, 1949
Creator: Morgan, W. C.; Kemp, R. H. & Manson, S. S.
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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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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Altitude performance and operational characteristics of 29-inch-diameter tail-pipe burner with several fuel systems and flame holders on J35 turbojet engine

Description: From Summary: "An investigation of turbojet-engine thrust augmentation by means of tail-pipe burning has been conducted in the NACA Lewis altitude wind tunnel. Several fuel systems and flame holders were investigated in a 29-inch-diameter tail-pipe burner to determine the effect of fuel distribution and flame-holder design on tail-pipe-burner performance and operational characteristics over a range of simulated flight conditions. At an altitude of 5000 feet, the type of flame holder used had on… more
Date: November 8, 1949
Creator: Conrad, E. William & Prince, William R.
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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Model ditching investigation of the Douglas DC-4 and DC-6 airplanes

Description: Report presenting the ditching characteristics of the Douglas DC-4 and DC-6 in a water tank. Dynamically similar models of 1/16 scale were used for the investigation, which was conducted in calm and rough water. The ditching characteristics and safest ditching procedures were determined by testing at various landing attitudes, speeds, and simulated conditions of damage.
Date: November 8, 1949
Creator: Fisher, Lloyd J. & Hoffman, Edward L.
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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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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Bibliography of Classified Aircraft-Fire Literature

Description: Memorandum presenting a bibliography of unclassified aircraft fire literature consisting of reports from a 20-year period ending January 1, 1949. The reports are separated into the following categories: aircraft fire accidents and statistics, combustibles, ignition sources, fire protection, fire prevention, fire resistance of materials, fire detecting, fire extinguishing, and passenger protection or rescue.
Date: November 10, 1949
Creator: Weiss, Solomon & Pesman, Gerard J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Downwash in Vortex Region Behind Trapezoidal-Wing Tip at Mach Number 1.91

Description: Report presenting the results of an experimental investigation to determine the downwash in the region of the trailing vortex behind a trapezoidal-wing tip in a supersonic stream. Results regarding the downwash at spanwise stations, downwash at chordwise stations, and wake survey are provided.
Date: November 10, 1949
Creator: Cummings, J. L.; Mirels, H. & Baughman, L. E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Estimation of the forces and moments acting on inclined bodies of revolution of high fineness ratio

Description: Report presenting a discussion of the aerodynamic forces and moments on inclined bodies of revolution. An approximate theory to allow for the effects of viscosity is developed and applied. Results regarding the variation of lift and pitching moment, and center of gravity are provided.
Date: November 14, 1949
Creator: Allen, H. Julian
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Altitude-wind-tunnel investigation of J47 turbojet-engine performance

Description: From Introduction: "Data are presented in graphical form to show the engine performance over a range of altitudes from 5000 to 50,000 feet and flight Mach numbers from 0.21 to 0.97. Curves are presented to show the windmilling characteristics of the engine. All engine performance data obtained in the investigation are also presented in tabular form."
Date: November 15, 1949
Creator: Conrad, E. William & Sobolewski, Adam E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Hydrodynamic Qualities of a 1/10-Size Powered Dynamic Model of the XP5Y-1 Flying Boat in Smooth Water: Langley Tank Model 246, TED No. NACA DE 320

Description: "The hydrodynamic characteristics of a 1/10-size powered dynamic model of the XP5Y-1 flying boat were determined in Langley tank no. 1. Stable take-offs were possible at all practicable positions of the center of gravity and flap deflections. An increase in gross load from 123.5 to 150.0 pounds (21.5 percent) had only a slight effect on the stable range for take-off" (p. 1).
Date: November 15, 1949
Creator: Woodward, David R.; Weinstein, Irving & Whitaker, Walter E., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Study of the canard configuration with particular reference to transonic flight characteristics and low-speed characteristics at high lift

Description: Report presenting a study of the flight characteristics of the canard configuration at transonic and supersonic speeds. Known problems concerning the low-speed characteristics of the canard are also investigated.
Date: November 16, 1949
Creator: Mathews, Charles W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Low-speed pressure-distribution and flow investigation for a large pitch and yaw range of three low-aspect-ratio pointed wings having leading edge swept back 60 degrees and biconvex sections

Description: Report presenting an investigation of pressure distributions and flow characteristics at low speed through a range of yaw and angle of attack through the stall for three small-scale low-aspect-ratio pointed wings with varying degrees of trailing-edge sweep. An effort was made to correlate pressure distributions with the strong conical vortex flow observed. Results regarding chordwise pressure distributions and flow characteristics, section lift characteristics at zero yaw, spanwise-load distrib… more
Date: November 18, 1949
Creator: May, Ralph W., Jr. & Hawes, John G.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Performance of Axial-Flow Supersonic Compressor of the XJ55-FF-1 Turbojet Engine. 4 - Analysis of Compressor Operation over a Range of Equivalent Tip Speeds from 801 to 1614 Feet Per Second

Description: "An investigation was conducted to determine the performance characteristics of the axial-flow supersonic compressor of the XJ55-FF-1 turbojet engine. An analysis of the performance of the rotor was made based on detailed flow measurements behind the rotor. The compressor apparently did not obtain the design normal-shock configuration in this investigation. A large redistribution of mass occurred toward the root of the rotor over the entire speed range; this condition was so acute at design spe… more
Date: November 18, 1949
Creator: Graham, Robert C. & Hartmann, Melvin J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Altitude-wind-tunnel investigation of compressor performance on J47 turbojet engine

Description: From Introduction: "The effects of variations in altitude, flight Mach number, and exhaust-nozzle-outlet area on the compressor performance characteristics are graphically presented. A complete tabulation of the compressor performance data is also presented."
Date: November 22, 1949
Creator: Prince, William R. & Jansen, Emmert T.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Wing-tunnel investigation at low transonic speeds of the effects of number of wings on the lateral-control effectiveness of an RM-5 test vehicle

Description: Report presenting an investigation to determine the effects of number of wings on the aileron rolling effectiveness of an RM-5 test vehicle using the free-rolling wind-tunnel testing technique through a speed range to Mach number 0.9. The wings tested had neither taper nor sweepback and were equipped with full-span 20-percent-chord sealed and faired ailerons. Results indicated that increasing the number of wings resulted in a decrease in rolling effectiveness so that results obtained from the t… more
Date: November 29, 1949
Creator: Johnson, Harold S.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Effect of tunnel configuration and testing technique on cascade performance

Description: "An investigation has been conducted to determine the influence of aspect ratio, boundary-layer control by means of slots and porous surfaces, Reynolds number, and tunnel end-wall condition upon the performance of airfoils in cascades. A representative compressor-blade section (the NACA 65-(12)(10) of aspect ratios of 1, 2, and 4 has been tested at low speeds in cascades with solid and with porous side walls. Two-dimensional flow was established in porous-wall cascades of each of the three aspe… more
Date: November 30, 1949
Creator: Erwin, John R. & Emery, James C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Flight Investigations at High-Subsonic, Transonic, and Supersonic Speeds to Determine Zero-Lift Drag of Fin-Stabilized Bodies of Revolution having Fineness Ratios of 12.5, 8.91, and 6.04 and Varying Positions of Maximum Diameter

Description: Rocket-powered models were flown at high-subsonic, transonic, and supersonic speeds to determine the zero-lift drag of fin-stabilized parabolic bodies of revolution differing in fineness ratio and in position of maximum diameter. The present paper presents the results for fineness ratio 12.5, 8.91 and 6.04 bodies having maximum diameters located at stations of 20, 40, 60, and 80 percent of body length. All configurations had cut-off sterns and all had equal base, frontal, and exposed fin areas.… more
Date: November 30, 1949
Creator: Hart, Roger G. & Katz, Ellis R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Spin-Tunnel Investigation of the Jettisoning of External Fuel Tanks in Spins

Description: "A spin-tunnel investigation has been made to determine the probability of external fuel tanks striking an airplane after being jettisoned in a spin. The investigation showed that for straight-wing fighter-type designs in any case in which jettisoning of tanks in a spin might aid spin recovery the tanks would probably clear all parts of the airplane" (p. 1).
Date: November 30, 1949
Creator: Berman, Theodore
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Aerodynamic characteristics of the NACA 8-H-12 airfoil section at six Reynolds numbers from 1.8 x 10(exp 6) to 11.0 x 10(exp 6)

Description: Report presenting an investigation in the two-dimensional low-turbulence pressure tunnel to determine the aerodynamic characteristics of the NACA 8-H-12 airfoil section at four Reynolds numbers. The section lift, drag, and pitching-moment characteristics are presented for smooth and rough surface conditions. Generally, no unusual scale effects are present for either condition.
Date: December 1949
Creator: Schaefer, Raymond F. & Smith, Hamilton A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Analysis of means of improving the uncontrolled lateral motions of personal airplanes

Description: From Summary: "The purpose of this investigation was to determine whether such airplanes could be made to fly uncontrolled for an indefinite period of time without getting into dangerous attitudes and for a reasonable period of time (one to three minutes) without deviating excessively from their original course. The results of this analysis indicated that the uncontrolled motions of a personal airplane could be made safe as regards spiral tendencies and could be greatly improved as regards main… more
Date: December 1949
Creator: McKinney, Marion O., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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