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Combustion of gaseous hydrogen at low pressures in a 35 degree sector of a 28-inch-diameter ramjet combustor
Report presenting testing of gaseous hydrogen fuel burned in a connected-pipe combustor with a cross section equal to 35 degrees sector of a 28-inch diameter. Eleven shrouded fuel-injector configurations were used to obtain combustion data at specified high-altitude ramjet combustor conditions. Results regarding shroud air blockage, mixing tabs, higher equivalence-ratio burning, injector size, flameholder durability, burner length, combustion efficiency, and temperature profile are provided.
Date:
April 22, 1958
Creator:
Kerslake, William R.
Object Type:
Report
System:
The UNT Digital Library
Comparison of Several Methods of Cyclic De-Icing of a Gas-Heated Airfoil
"Several methods of cyclic de-icing of a gas-heated airfoil were investigated to determine ice-removal characteristics and heating requirements. The cyclic de-icing system with a spanwise ice-free parting strip in the stagnation region and a constant-temperature gas-supply duct gave the quickest and most reliable ice removal. Heating requirements for the several methods of cyclic de-icing are compared, and the savings over continuous ice prevention are shown. Data are presented to show the relation of surface temperature, rate of surface heating, and heating time to the removal of ice" (p. 1).
Date:
June 22, 1953
Creator:
Gray, Vernon H. & Bowden, Dean T.
Object Type:
Report
System:
The UNT Digital Library
Effect of Design Variables on Performance of Mach 4.0 Hydrogen Expansion Engines
Memorandum presenting performance calculations for hypothetical hydrogen expansion engines in which only a small part of the engine airflow passes through the heat exchanger. The flight path was representative of those for long-range, high-speed aircraft. Results regarding the off-design operation and engine performance are provided.
Date:
July 22, 1958
Creator:
Dugan, James F., Jr.
Object Type:
Report
System:
The UNT Digital Library
Performance of Five Short Multielement Turbojet Combustors for Hydrogen Fuel in Quarter-Annulus Duct
Report described five short multielement turbojet combustors for use with hydrogen fuel and their performance. Information about the combustion efficiency, temperature profiles, pressure loss, durability, and comparison with previous short combustors is included.
Date:
July 22, 1958
Creator:
Jones, Robert E. & Rayle, Warren D.
Object Type:
Report
System:
The UNT Digital Library
Flight Investigation of Pentaborane Fuel in 9.75-inch-diameter Ram-jet Engine With Downstream Fuel Injection
Flight investigation of pentaborane fuel in 9.75- inch-diameter ramjet engine with downstream fuel injection.
Date:
April 22, 1957
Creator:
Disher, John H. & Jones, Merle L.
Object Type:
Report
System:
The UNT Digital Library
Performance of a Double-Ramp Side Inlet With Combinations of Fuselage, Ramp, and Throat Boundary-Layer Removal, Mach Number Range, 1.5 to 2.0
Double-ramp side inlet with combinations of fuselage, ramp, and throat boundary layer removal.
Date:
October 22, 1956
Creator:
Simon, Paul C.
Object Type:
Report
System:
The UNT Digital Library
The Effect of Compressor-Inlet Water Injection on Engine and Afterburner Performance
"A turbojet engine incorporating a conventional-type afterburner was operated over a range of afterburner pressure levels from 1000 to 2000 pounds per square foot absolute and a range of engine-inlet water-air ratios from 0 to 0.08. At each pressure level and water-air ratio, the afterburner fuel flow was varied from lean blowout to maximum burner-outlet temperature" (p. 1).
Date:
July 22, 1958
Creator:
Sivo, Joseph N.; Wanhainen, John P. & Jones, William L.
Object Type:
Report
System:
The UNT Digital Library
Methods of analyzing wind-tunnel data for dynamic flight conditions
The effects of power on the stability and the control characteristics of an airplane are discussed and methods of analysis are given for evaluating certain dynamic characteristics of the airplane that are not directly discernible from wind tunnel tests alone. Data are presented to show how the characteristics of a model tested in a wind tunnel are affected by power. The response of an airplane to a rolling and a yawing disturbance is discussed, particularly in regard to changes in wing dihedral and fin area. Solutions of the lateral equations of motion are given in a form suitable for direct computations. An approximate formula is developed that permits the rapid estimation of the accelerations produced during pull-up maneuvers involving abrupt elevator deflections.
Date:
July 22, 1941
Creator:
Donlan, C. J. & Recant, I. G.
Object Type:
Report
System:
The UNT Digital Library
Examination of Recent Lateral-Stability-Derivative Data
"In the present paper attention is directed to the aerodynamic parameters, the so-called stability derivatives, that affect the lateral behavior of airplanes and missiles. The discussion is centered on three important quantities, the effective-dihedral derivative, the directional-stability derivative, and the damping-in-roll derivative. These quantities are considered for a large angle-of-attack range at subsonic speeds" (p. 1).
Date:
October 22, 1953
Creator:
Malvestuto, Frank S., Jr. & Kuhn, Richard E.
Object Type:
Report
System:
The UNT Digital Library
An Investigation of the Downwash at the Probable Tail Location Behind a High-Aspect-Ratio Wing in the Langley 8-Foot High-Speed Tunnel
Report presenting measurements downwash angles behind a model of a high-aspect-ratio wing at points near the probable tail location at Mach numbers up to 0.89 in the high-speed tunnel. The model has an NACA 65-210 section, an aspect ratio of 9.0, a taper ratio of 2.5:1, no twist, dihedral, or sweepback. Results regarding experimental data and comparison of experimental and calculated results are provided.
Date:
April 22, 1947
Creator:
Whitcomb, Richard T.
Object Type:
Report
System:
The UNT Digital Library
Tests of a triangular wing of aspect ratio 2 in the Ames 12-foot pressure wind tunnel. 1: the effect of Reynolds number and Mach number on the aerodynamic characteristics of the wing with flap undeflected
Report presenting testing of a semispan model of a wing of triangular plan form and aspect ratio 2 in the 12-foot pressure tunnel to determine the aerodynamic characteristics of the wing as influenced by the independent effects of Reynolds number and Mach number up to Mach numbers approaching unity. Results regarding the effect of body and effect of wing-profile modification are also provided.
Date:
January 22, 1948
Creator:
Edwards, George G. & Stephenson, Jack D.
Object Type:
Report
System:
The UNT Digital Library
Pressure Distributions on the Blade Sections of the NACA 10-(3)(090)-03 Propeller Under Operating Conditions
The third report in a series of five that present unanalyzed pressure data obtained in tests of five full-scale propellers with NACA 16-series blade sections. Pressure distributions on the blade sections were measured under operating conditions to determine the aerodynamic characteristics of each blade section. This particular report presents information for nine radial stations of the NACA 10-(3)(090)-03 propeller.
Date:
March 22, 1950
Creator:
Johnson, Peter J.
Object Type:
Report
System:
The UNT Digital Library
Investigation of stage performance of X24C-2 ten-stage axial-flow compressor at design speed
The stage performance of the X24C-2 axial-flow compressor, as determined from radial distributions of total pressure and temperature measured in each stator-blade row, was investigated at design speed at weight flows corresponding to those of the maximum weight-flow, peak-efficiency, and surge points. The stage performance is presented as the measured stage pressure ratios and the calculated velocity diagrams. The average stage total-pressure ratio at the surge operating condition in the first stage was approximately 1.10; in the second stage, approximately 1.13; and in all remaining stages, approximately constant at a value of 1.15. Regions of inefficient flow are discussed so as to point out the reasons for the poor flow conditions.
Date:
May 22, 1950
Creator:
Finger, Harold B.; Cohen, Leo & Stewart, Warner L.
Object Type:
Report
System:
The UNT Digital Library
Wind-Tunnel Investigation of Horizontal Tails 1: Unswept and 35 Degrees Swept-Back Plan Forms of Aspect Ratio 3
Memorandum presenting the results of a wind-tunnel investigation of the low-speed characteristics of horizontal tails of aspect ratio 3 with unswept and swept-back plan forms. Two models were tested which had identical areas, aspect ratio, taper ratio, and airfoil section, differing only in the angle of sweepback and elevator area ratios. The major effect of sweepback was to increase the rate of change of hinge-moment coefficient with angle of attack, to reduce the rate of change with elevator deflection, and to reduce the elevator effectiveness.
Date:
April 22, 1948
Creator:
Dods, Jules B., Jr.
Object Type:
Report
System:
The UNT Digital Library
Preliminary Tank Investigation of the Use of Single Monoplane Hydrofoils for High-Speed Airplanes
Report presenting an investigation of the hydrodynamic take-off and landing characteristics of a model of a hypothetical jet- and rocket-propelled high-speed airplane fitted with various designs of a single monoplane hydrofoil mounted near the center of gravity. This testing is performed to determine the feasibility of the water-based operation of high-speed airplanes. Results regarding the general hydrodynamic characteristics, development of hydrofoils, and effects of some hydrofoil parameters are provided.
Date:
March 22, 1949
Creator:
King, Douglas A. & Rockett, John A.
Object Type:
Report
System:
The UNT Digital Library
Effects of Some Airfoil-Section Variations on Wing-Aileron Rolling Effectiveness and Drag as Determined in Free Flight at Transonic and Supersonic Speeds
Report presenting an investigation in free flight of the rolling effectiveness of plain ailerons in conjunction with wings having 0 and 45 degrees sweepback with several airfoil sections. Results regarding the rolling characteristics of rectangular and sweptback-wing configurations and drag measurements are provided.
Date:
July 22, 1949
Creator:
Sandahl, Carl A.; Bland, William M., Jr. & Strass, H. Kurt
Object Type:
Report
System:
The UNT Digital Library
Altitude-wind-tunnel investigation of compressor performance on J47 turbojet engine
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.
Object Type:
Report
System:
The UNT Digital Library
Drag characteristics of rectangular and swept-back NACA 65-009 airfoils having various aspect ratios as determined by flight tests at supersonic speeds
Report presenting tests to determine the effect of sweepback angle and aspect ratio on the drag at supersonic speeds of wings of NACA 65-009 airfoil section. The current report is part of a bigger investigation and includes results for aspect ratios of 3.8 and 5.0. Results regarding the drag coefficient and general effect of aspect ratio are provided.
Date:
April 22, 1947
Creator:
Tucker, Warren A. & Nelson, Robert L.
Object Type:
Report
System:
The UNT Digital Library
An Evaluation of Air-Borne Radar as a Means of Avoiding Atmospheric Turbulence
"Gust-velocity measurements and air-borne-radar observations obtained during a transcontinental flight in July 1947 have been analyzed as part of a general investigation of the uses of air-borne radar. The analysis indicates that some reduction in turbulence and a consequent reduction in the risk of encountering the larger gust velocities may be obtained by avoiding portions of clouds giving a radar echo" (p. 1).
Date:
November 22, 1948
Creator:
Steiner, Roy
Object Type:
Report
System:
The UNT Digital Library
Comparison of National Bureau of Standards ceramic coatings L-7C and A-417 on turbine blades in a turbojet engine
Report presenting an investigation to determine which of two ceramic coatings, L-7C and A-417, developed by the National Bureau of Standards is more suitable as a protective coating for turbine blades in a turbojet engine. Four cast Vitallium turbine blades, two coated with each of the ceramics, were installed in a turbine wheel of a turbojet engine and subjected to accelerated cyclic life tests.
Date:
December 22, 1948
Creator:
Morse, C. Robert
Object Type:
Report
System:
The UNT Digital Library
Vibration of turbine blades in a turbojet engine during operation
Report presenting an experimental investigation to determine the vibration phenomena that occur in turbine blades of a typical jet-propulsion engine during service operation; high-temperature strain gages were used to measure the turbine-blade vibrations. Results regarding modes of vibration, centrifugal stresses, and vibration of turbine blades during operation are provided.
Date:
April 22, 1948
Creator:
Morgan, W. C.; Kemp, R. H. & Manson, S. S.
Object Type:
Report
System:
The UNT Digital Library
Free-flight performance of 16-inch-diameter supersonic ram-jet units 1: four units designed for combustion-chamber-inlet Mach number of 0.12 at free-stream Mach number of 1.6 (units A-2, A-3, A-4, and A-5)
Report presenting free-flight investigations conducted on four 16-inch-diameter ramjet units to determine the performance at high subsonic and supersonic velocities. Data for evaluating the performance were obtained from radio-telemetering and radar-tracking equipment. Results regarding combustion performance, diffuser total-pressure recovery, thrust coefficient, and external drag coefficient are provided.
Date:
September 22, 1949
Creator:
Carlton, William W. & Messing, Wesley E.
Object Type:
Report
System:
The UNT Digital Library
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
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.
Object Type:
Report
System:
The UNT Digital Library
A Preliminary Experimental and Analytical Evaluation of Diborane as a Ram-Jet Fuel
Report presenting an analytical and experimental evaluation of diborane as a ram-jet fuel, which seems to offer greater flight range, thrust, and combustion stability beyond what is attainable with petroleum fuels. Results regarding ideal thrust, stability, deposits, and flight range with several blends of diborane are provided.
Date:
December 22, 1950
Creator:
Gammon, Benson E.; Genco, Russell S. & Gerstein, Melvin
Object Type:
Report
System:
The UNT Digital Library