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269 Matching Results
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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
"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.
System:
The UNT Digital Library
Estimation of the forces and moments acting on inclined bodies of revolution of high fineness ratio
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
System:
The UNT Digital Library
Bibliography of Classified Aircraft-Fire Literature
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.
System:
The UNT Digital Library
Downwash in Vortex Region Behind Trapezoidal-Wing Tip at Mach Number 1.91
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.
System:
The UNT Digital Library
Investigation of Some Turbulent-Boundary-Layer Velocity Profiles at a Tunnel Wall with Mach Numbers up to 1.2
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.
System:
The UNT Digital Library
Low-speed static longitudinal stability characteristics of a canard model having a 60 degrees triangular wing and horizontal tail
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.
System:
The UNT Digital Library
Altitude performance and operational characteristics of 29-inch-diameter tail-pipe burner with several fuel systems and flame holders on J35 turbojet engine
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 only a slight effect on the combustion efficiency."
Date:
November 8, 1949
Creator:
Conrad, E. William & Prince, William R.
System:
The UNT Digital Library
An Investigation of the Characteristics of an Unswept Wing of Aspect Ratio 4.01 in the Langley 8-Foot High-Speed Tunnel
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.
System:
The UNT Digital Library
Model ditching investigation of the Douglas DC-4 and DC-6 airplanes
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.
System:
The UNT Digital Library
Static longitudinal stability and control of a convertible-type airplane as affected by articulated- and rigid-propeller operation
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.
System:
The UNT Digital Library
Analysis and Experimental Observation of Pressure Losses in Ram-Jet Combustion Chambers
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.
System:
The UNT Digital Library
Analytical determination of effect of water injection on power output of turbine-propeller engine
From Introduction: "Water injection at the compressor inlet has been successfully used to increase the thrust of turbojet engines. References 1 and 2 indicate that the sea-level static thrust of a centrifugal-flow-type turbojet engine may be increased about 25 percent by use of liquid injection. Reference 3 indicates that greater thrust augmentation is possible at a compressor pressure ratio of 11 than of 4."
Date:
November 3, 1949
Creator:
Ross, Albert O. & Huppert, Merle C.
System:
The UNT Digital Library
General Characteristics of a Airspeed System using Fuselage Static Vents on a Swept-Wing Airplane
"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 range of 0.7 to 1.2" (p. 1).
Date:
November 3, 1949
Creator:
Johnston, J. Ford & O'Bryan, Thomas C.
System:
The UNT Digital Library
Vibration of loosely mounted turbine blades during service operation of a turbojet engine with centrifugal compressor and straight-flow combustion chambers
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.
System:
The UNT Digital Library
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
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.
System:
The UNT Digital Library
Reduction of profile drag at supersonic velocities by the use of airfoil sections having a blunt trailing edge
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.
System:
The UNT Digital Library
Flight Investigation From High Subsonic to Supersonic Speeds to Determine the Zero-Lift Drag of a Transonic Research Vehicle Having Wings of 45 Degree Sweepback, Aspect Ratio 4, Taper Ratio 0.6, and NACA 65A006 Airfoil Sections
Report presenting rocket-powered flight tests from high subsonic to supersonic speeds and at high Reynolds numbers to determine the zero-lift drag of a transonic wing-body and body-alone configuration. The configuration tested featured a wing of 45 degree sweepback, aspect ratio 4, taper ratio 0.6, and an NACA 65A006 airfoil section, and a body of fineness ratio of 10 and a frontal area equal to 6.06 percent of the wing-plan-form area.
Date:
October 27, 1949
Creator:
Katz, Ellis
System:
The UNT Digital Library
Altitude-Chamber Performance of British Rolls-Royce Nene II Engine 2: 18.41-Inch-Diameter Jet Nozzle
Report presenting an altitude-chamber investigation to determine the altitude performance characteristics of the British Rolls-Royce Nene II turbojet engine with an 18.41-inch-diameter jet nozzles. Testing occurred at a range of simulated altitudes and ram-pressure ratios. Results regarding the simulated flight performance, generalized performance, and effect of jet-nozzle area on performance are provided.
Date:
October 26, 1949
Creator:
Armstrong, J. C.; Wilsted, H. D. & Vincent, K. R.
System:
The UNT Digital Library
Investigation of a Two-Step Nozzle in an 11-Inch Hypersonic Tunnel
Report discussing flow surveys made of several nozzles using two 2-dimensional steps at Mach number 6.98. Results regarding wall-pressure surveys, disturbance patterns in expansion, total-pressure survey, temperature recovery, and general nozzle characteristics are provided.
Date:
October 25, 1949
Creator:
McLellan, Charles H.; Williams, Thomas W. & Bertram, Mitchel H.
System:
The UNT Digital Library
Aerodynamic characteristics of a wing with unswept quarter-chord line, aspect ratio 4, taper ratio 0.6, and NACA 65A006 airfoil section
From Introduction: "This paper presents the results of the investigation of the wing-alone and of the wing-fuselage configuration employing a wing with an unswept quarter-chord line, aspect ratio 4, taper ratio 0.6, and an NACA 65A006 airfoil section parallel to the air stream. The results of closely related sweptback-wing investigations, which are part of the present transonic programs, are presented in references 1 to 3."
Date:
October 21, 1949
Creator:
Goodson, Kenneth W. & Morrison, William D., Jr.
System:
The UNT Digital Library
The Effects of Horizontal-Tail Location and Wing Modifications on the High-Speed Stability and Control Characteristics of a 01.17-Scale Model of the McDonnell XF2H-1 Airplane (TED No, NACA DE336)
"An additional series of high-speed wind-tunnel tests of a modified 0.17-scale model of the McDonnell XF2H-1 airplane was conducted to evaluate the effects of a reduction in the thickness-to-chord ratios of the tail planes, the displacement of the horizontal tail relative to the vertical tail, and the extension of the trailing edge of the wing. Two tail-intersection fairings designed to improve the flow at the tail were also tested. The pitching-moment characteristics of the model were improved slightly by the use of the thinner tail sections" (p. 1).
Date:
October 14, 1949
Creator:
Emerson, Horace F. & Axelson, John A.
System:
The UNT Digital Library
An Investigation at Low Speed of a Large-Scale Triangular Wing of Aspect Ratio Two 3: Characteristics of Wing With Body and Vertical Tail
Report presenting an investigation to determine the aerodynamic characteristics in sideslip of a triangular wing of aspect ratio 2.04 in combination with a body of fineness ratio 12.5 and a vertical tail surface. The body combined with the triangular plan-form wing caused no significant changes in the lift characteristics of the wing and only a 1-percent decrease in the static margin. Results regarding the longitudinal characteristics, lateral and directional characteristics, and estimation of tail and rudder effectiveness are provided.
Date:
October 14, 1949
Creator:
Anderson, Adrien E.
System:
The UNT Digital Library
Experimental investigation of pressure fluctuations in 3.6 inch ram jet at Mach number 1.92
Report presenting an experimental study of the pressure fluctuations at the combustion-chamber inlets of a ramjet operating a Mach number of 1.92 in the supersonic tunnel. Results are presented for two burner configurations of different operating characteristics to indicate trends in pressure magnitude, frequency, and wave form. Results regarding the perforated conical flame holder, regenerative-type burner, and diffuser total-pressure recovery are provided.
Date:
October 13, 1949
Creator:
Connors, James F. & Schroeder, Albert H.
System:
The UNT Digital Library
Longitudinal Stability and Control Characteristics of a Semispan Wind-Tunnel Model of a Tailless Airplane and a Comparison With Complete-Model Wind-Tunnel Tests and Semispan-Model Wing-Flow Tests
Report presenting an investigation of a model of a tailless airplane in a high speed tunnel at a range of Mach numbers. Results are compared to those obtained from a sting-mounted model tested in the same tunnel and a semispan model tested with the wing-flow method. Information regarding basic aerodynamic characteristics, spoiler controls, lift characteristics, drag characteristics, pitching moment at zero lift, and stability and control is provided.
Date:
October 10, 1949
Creator:
Goodson, Kenneth W. & King, Thomas J., Jr.
System:
The UNT Digital Library