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Effect of air distribution on radial temperature distribution in one-sixth sector of annular turbojet combustor
Report presenting an experimental investigation in a one-sixth sector of an annular turbojet combustor to determine a method of controlling radial exhaust-gas-temperature distribution in a gas-turbine combustion chamber. The adjustment in controlling air was made by ducting the dilution air into the combustion zone in a predetermined manner through hollow radial struts or by modifying the basket-wall open-hole area. Results regarding the temperature distribution, temperature-rise efficiency, total-pressure loss, and altitude operating limits are provided.
Date:
April 5, 1950
Creator:
Mark, Herman & Zettle, Eugene V.
System:
The UNT Digital Library
Flight-Test Measurements of Aileron Control Surface Behavior at Super Critical Mach Numbers
Report presenting measurements of the behavior at supercritical Mach numbers of ailerons on a jet-propelled fighter plane. Results regarding aileron upfloat and aileron oscillations are provided.
Date:
April 23, 1947
Creator:
Brown, Harvey H.; Rathert, George A., Jr. & Clousing, Lawrence A.
System:
The UNT Digital Library
Ditching Tests of a 1/18-Scale Model of the Lockheed Constellation Airplane
"Tests were made of a 1/18-scale dynamically similar model of the Lockheed Constellation airplane to investigate its ditching characteristics and proper ditching technique. Scale-strength bottoms were used to reproduce probable damage to the fuselage. The model was landed in calm water at the Langley tank no. 2 monorail. Various landing attitudes, speeds, and fuselage configurations were simulated" (p. 1).
Date:
April 20, 1950
Creator:
Fisher, Lloyd J. & Morris, Garland J.
System:
The UNT Digital Library
An analysis of a highly compounded two-stroke-cycle compression-ignition engine
This report presents an analysis of a compound engine operating with manifold pressures ranging from 60 to 110 lb/sq in. absolute and discusses the effects of engine limits (peak cylinder pressure and turbine-inlet temperature) and component efficiency.
Date:
April 4, 1949
Creator:
Tauschek, Max J.; Sather, Bernard I. & Biermann, Arnold E.
System:
The UNT Digital Library
Investigation of carbon deposition in an I-16 jet-propulsion engine at static sea-level conditions
Report presenting a study of the effect of fuel properties on carbon deposition in jet-propulsion engine combustors using seven fuels: kerosene, Diesel fuel oil, toluene, xylene, 62-octane gasoline, a commercial solvent, and AN-F-32 (JP-1) in an I-16 engine at static sea-level conditions and constant rotor speed. Results regarding the reproducibility of data, reduced exhaust-jet-nozzle area, and fuel comparison are provided.
Date:
April 29, 1947
Creator:
Jonash, Edmund R.; Barnett, Henry C. & Stricker, Edward G.
System:
The UNT Digital Library
Effect of Number of Fins on the Drag of a Pointed Body of Revolution at Low Supersonic Velocities
Report presenting the results of flight tests conducted to determine the effect of number of fins on the drag of a pointed body moving at low supersonic velocities. The data indicated that the interference drag increased with increased number of ins up to a Mach number of 1.35, but above that value, the effect is reversed to the end of the test Mach number.
Date:
April 7, 1947
Creator:
Mastrocola, N.
System:
The UNT Digital Library
Application of an ultraviolet spectrophotometric method to the estimation of alkylnaphthalenes in 10 experimental jet-propulsion fuels
Report presenting the combustion efficiencies of 10 experimental jet-propulsion fuels that are approximately 200 degrees Fahrenheit cuts of five selected crudes available in large quantities in a turbojet engine combustor at altitude conditions.
Date:
April 30, 1947
Creator:
Cleaves, Alden P. & Carver, Mildred S.
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.
System:
The UNT Digital Library
Wind-Tunnel Investigation of Air Loads Over a Double Slotted Flap on the NACA 65(216)-215, a = 0.8 Airfoil Section
Report presenting an investigation at low speed and high Reynolds number to determine the air loads over a double slotted flap on the NACA 65(216)-215, a = 0.8 airfoil section. Results indicated that the loads on the flap change slowly with variation of angle of attack but quickly with the flap deflected. The main effect of the double-slotted flap is that it causes the airfoil to carry a greater load without stalling.
Date:
April 9, 1947
Creator:
Visconti, Fioravante
System:
The UNT Digital Library
Experimental investigation of the effects of viscosity on the drag of bodies of revolution at a Mach number 1.5
Report presenting testing to determine the effects of viscosity on the drag and base pressure characteristics of various bodies of revolution at a Mach number of 1.5. The models were tested with smooth surfaces and roughness to evaluate the effects of Reynolds number for both laminar and turbulent boundary layers. Results regarding the reduction of data, precision, effects of support interference, Schileren photographs, and theoretical calculations are provided.
Date:
April 3, 1947
Creator:
Chapman, Dean R. & Perkins, Edward W.
System:
The UNT Digital Library
Altitude performance of AN-F-58 fuels in J33-A-21 single combustor
Report discussing three fuels conforming to AN-F-58 specification were investigated in order to determine the influence of boiling temperatures and aromatic content on altitude performance in single combustor of a 4600-pound-thrust turbojet engine.
Date:
April 8, 1949
Creator:
Dittrich, Ralph T. & Jackson, Joseph L.
System:
The UNT Digital Library
Experimental study of loop-scavenged compression-ignition cylinder for gas-generator use
Report presenting an investigation of the performance and general operating characteristics of a small single-cylinder, two-stroke-cycle, loop-scavenged engine using compression ignition at low compression ratios, high inlet-manifold temperatures and high inlet-manifold and exhaust-gas pressures. Results regarding the scavenging characteristics, power output, cylinder pressures, thermal efficiency, and exhaust measurements are provided.
Date:
April 4, 1949
Creator:
Foster, Hampton H.; Schuricht, F. Ralph & Tauschek, Max J.
System:
The UNT Digital Library
A Study of Several Parameters Controlling the Trajectories of a Supersonic Antiaircraft Missile Powered With Solid- or Liquid-Fuel Rockets
Memorandum presenting a calculation of the trajectories for a supersonic antiaircraft missile by a step-by-step integration method for a number of different conditions. The effects of changing drag, initial thrust ratio, and weight ratio, which are the principal variables controlling the trajectory for a fixed launching angle, were investigated.
Date:
April 24, 1947
Creator:
Huntsberger, Ralph F.
System:
The UNT Digital Library
Comparison of flight performance of AN-F-58 and AN-F-32 fuels in J35 turbojet engine
Report presenting a flight investigation to determine the comparative performance of AN-F-58 and AN-F-32 fuels in a 4000-pound-thrust turbojet engine. The fuels were equivalent over the range of conditions investigated. Results regarding corrected net thrust, corrected jet-fuel consumption, variation of corrected tail-pipe temperature, combustor blow-out speeds, and visual observations of the jet exhaust are provided.
Date:
April 7, 1949
Creator:
Acker, Loren W. & Kleinknecht, Kenneth S.
System:
The UNT Digital Library
The interaction of boundary layer and compression shock and its effect upon airfoil pressure distributions
Report presenting an investigation of the mechanism of interaction of compression shock with boundary layer. Shockless pressure distributions at supercritical Mach numbers were found to be accounted for by a marked thickening of the boundary layer for some distance ahead of a shock wave.
Date:
April 10, 1947
Creator:
Allen, H. Julian; Heaslet, Max A. & Nitzberg, Gerald E.
System:
The UNT Digital Library
Fuel Tests on an I-16 Jet-Propulsion Engine at Static Sea-Level Conditions
Memorandum presenting an investigation of the effect of fuel composition and boiling point on the performance of the type of I-16 jet-propulsion engine. Testing occurred with 14 fuels embodying different types of hydrocarbon and with a range of boiling points. The results indicated that fuel composition and boiling range have a negligible effect on engine thrust, rotor speed, and gas temperatures for the principal types of hydrocarbon fuel when used for short periods of time.
Date:
April 29, 1947
Creator:
Bolz, Ray E. & Meigs, John B.
System:
The UNT Digital Library
Flight Tests to Determine the Drag of Fin-Stabilized Parabolic Bodies at Transonic and Supersonic Speeds
Report presenting testing on parabolic bodies of revolution of two fineness ratios in the transonic and supersonic range. One had a body fineness ratio of 7.87 and one had a ratio of 12 and were tested under different Mach number ranges. Experimental results and drag estimates of various portions of the body are provided.
Date:
April 21, 1948
Creator:
Alexander, Sidney R.; Chauvin, Leo T. & Rumsey, Charles B.
System:
The UNT Digital Library
Results Obtained During Accelerated Transonic Tests of the Bell XS-1 Airplane in Flights to a Mach Number of 0.92
Results are presented of tests up to a Mach number of 0.92 at altitudes around 30,000 feet. The data obtained show that the airplane can be flown to this Mach number above 30,000 feet. Longitudinal trim changes have been experienced but the forces involved have been small. The elevator effectiveness decreased about one-half with increase of Mach number from 0.70 to 0.87.
Date:
April 19, 1948
Creator:
Drake, Hubert M.; McLaughlin, Milton D. & Goodman, Harold R.
System:
The UNT Digital Library
Stability Results Obtained With Douglas D-558-1 Airplane (BuAero No. 37971) in Flight Up to a Mach Number of 0.89
Memorandum presenting measurements of some of the high-speed characteristics of the D-558-1 airplane up to Mach number 0.89. The results of the tests showed that the stabilizer incidence drastically affected the longitudinal trim characteristics above a Mach number of 0.80.
Date:
April 22, 1949
Creator:
Barlow, William H. & Lilly, Howard C.
System:
The UNT Digital Library
Analytical and experimental investigation of thrust augmentation of axial- and centrifugal-compressor turbojet engines by injection of water and alcohol in combustion chambers
Report presenting an investigation of thrust augmentation by injection of water and water-alcohol mixtures in the combustion chambers at sea-level zero-ram flight conditions on 4000-pound-thrust axial-flow and centrifugal-flow turbojet engines. Thrust augmentation, compressor characteristics, fuel flow, and turbine-outlet-temperature distributions are presented for various injection rates and water-alcohol mixtures.
Date:
April 13, 1950
Creator:
Gabriel, David S.; Dowman, Harry W. & Jones, William L.
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.
System:
The UNT Digital Library
Effect of a pilot's canopy on the drag of an NACA RM-2 drag research model in flight at transonic and supersonic speeds
Report presenting data from two experiments. One used the NACA RM-2 drag research model equipped with a pilot's canopy to determine the effect on aerodynamics. The other was conducted with the same configuration and returned similar results.
Date:
April 20, 1948
Creator:
Purser, Paul E.
System:
The UNT Digital Library
Analysis of the Effects of Various Mass, Aerodynamic, and Dimensional Parameters on the Dynamic Lateral Stability of the Douglas D-558-2 Airplane
Report presenting an investigation of the effects of various mass, aerodynamic, and dimensional parameters on the dynamic lateral stability of the Douglas D-558-2 airplane. Results regarding an airplane with the flaps and gear retracted, airplane at sea level with flaps deflected 50 degrees and landing gear lowered, and effect of assumed modifications to airplane are provided.
Date:
April 15, 1949
Creator:
Queijo, M. J. & Michael, W. H., Jr.
System:
The UNT Digital Library
Study of compressor systems for a gas-generator engine
Report presenting various methods of providing compressor-capacity and pressure-ratio control in the gas-generator type of compound engine over a range of altitudes. The analytical results indicated that the best method of control is that in which the first stage of compression is carried out in a variable-speed supercharger driven by a hydraulic slip coupling. Results regarding the constant-pressure-ratio compressor, constant-volume compressor, comparison of piston-type and rotary compressors, effect of variable-area turbine nozzle, and effect of designing for high altitudes are provided.
Date:
April 13, 1949
Creator:
Sather, Bernard I. & Tauschek, Max J.
System:
The UNT Digital Library