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Investigation at High Subsonic Speeds of Methods of Alleviating the Adverse Interference at the Root of a Swept-Back Wing
Memorandum presenting an investigation of the interference at the root of a sweptback wing at high subsonic Mach numbers by means of wind-tunnel measurements of a wing-body combination with the 50-percent-chord line of the wing either unswept or swept back 35 degrees. Results regarding body characteristics, pressure studies, tuft studies, and force studies are provided.
Date:
August 10, 1950
Creator:
Boddy, Lee E.
System:
The UNT Digital Library
Altitude performance characteristics of tail-pipe burner with variable-area exhaust nozzle
From Introduction: "Data are presented to show the effects of tail-pipe fuel-air ratio, altitude, and flight Mach number on tail-pipe-burner performance at rated engine speed and approximately constant turbine-outlet temperature. Operational characteristics of the tail-pipe burner and variable-area exhaust nozzle are also reported."
Date:
August 11, 1950
Creator:
Jansen, Emmert T. & Thorman, H. Carl
System:
The UNT Digital Library
Flight Measurements With the Douglas D-558-II (BuAero No. 37974) Research Airplane: Measurements of the Buffet Boundary and Peak Airplane Normal-Force Coefficients at Mach Numbers Up to 0.90
Report presenting measurements of the buffet boundary and peak normal-force coefficients for the Douglas D-558-II airplane up to a Mach number of 0.90. Results regarding airplane lift curves and a comparison between the maximum normal-force coefficients and buffet boundaries for this particular aircraft and the Bell X-1 airplane are also provided.
Date:
August 28, 1950
Creator:
Mayer, John P. & Valentine, George M.
System:
The UNT Digital Library
Extension of boundary-layer heat-transfer theory to cooled turbine blades
An equation for average heat transfer of a surface was derived when the boundary layer changed from laminar to turbulent. Influences on the heat transfer through a laminar boundary layer of Mach number, temperature ratio (gas temperature divided by wall temperature), and exponents of gas-property temperature relations were shown to be relatively small for air with Mach numbers less than 2 and temperature ratios between 1 and 4. Good agreement was obtained with experimental results from cylinders, an airfoil, and turbine blades.
Date:
August 11, 1950
Creator:
Brown, W. Byron & Donoughe, Patrick L.
System:
The UNT Digital Library
Investigation of Thrust Augmentation of a 1600-Pound Thrust Centrifugal-Flow-Type Turbojet Engine by Injection of Refrigerants at Compressor Inlets
Investigations were conducted to determine effectiveness of refrigerants in increasing thrust of turbojet engines. Mixtures of water an alcohol were injected for a range of total flows up to 2.2 lb/sec. Kerosene was injected into inlets covering a range of injected flows up to approximately 30% of normal engine fuel flow. Injection of 2.0 lb/sec of water alone produced an increase in thrust of 35.8% of rate engine conditions and kerosene produced a negligible increase in thrust. Carbon dioxide increased thrust 23.5 percent.
Date:
August 25, 1947
Creator:
Jones, William L. & Dowman, Harry W.
System:
The UNT Digital Library
Low-Speed Investigation of a Small Triangular Wing of Aspect Ratio 2.0 2: Flaps on Flat-Plate Models
Memorandum presenting low-speed wind-tunnel tests made of flat-plate wings with an aspect ratio of 2.0 and their leading edges swept back 63.4 degrees. Both plain and split flaps of several plan forms were investigated to provide qualitative information as to the relative merits of these flaps. The constant-chord flap was found to be the most effective and a skewed wing-tip flap the least effective.
Date:
August 9, 1948
Creator:
Rose, Leonard M.
System:
The UNT Digital Library
Analysis of parameters for thrust control of a turbojet engine equipped with air-inlet throttle and variable-area exhaust nozzle
From Introduction: "In this report, altitude, airplane velocity, exhaust-nozzle area, and turbine-inlet temperature were chosen and corresponding engine speed, fuel flow, and throttle pressure ratio were found. A detailed discussion of the engine analysis and the calculations used are presented in Appendix A. The derivations of the principal equations used are presented in appendix B."
Date:
August 10, 1948
Creator:
Boksenbom, Aaron S. & Feder, Melvin S.
System:
The UNT Digital Library
Preliminary results of natural icing of an axial-flow turbojet engine
Report presenting a flight investigation in natural icing conditions to determine the effect of ice formations on the performance of an axial-flow turbojet engine. Results regarding the tail-pipe temperature, engine jet thrust, and characteristics of ice formation are provided. No general conclusions can be reached from the data because the icing condition was relatively light.
Date:
August 6, 1948
Creator:
Acker, Loren W.
System:
The UNT Digital Library
Low-Speed Investigation of a Small Triangular Wing of Aspect Ratio 2.0 3: Static Stability With Twin Vertical Fins
"Low-speed wind-tunnel tests were made of a triangular wing with two arrangements of twin vertical fins. With these twin fins mounted either symmetrically or wholly above the wing chord plane, approximately constant effectiveness in proportion to the fin size was obtained throughout the angle-of-attack range. The addition of these fins, however, resulted in a decrease in maximum lift and a reduction in static longitudinal stability at lift coefficients above 0.4" (p. 1).
Date:
August 24, 1948
Creator:
Rose, Leonard M.
System:
The UNT Digital Library
Investigation of the I-40 jet-propulsion engine in the Cleveland altitude wind tunnel 1: performance and windmilling drag characteristics
Report presenting the performance characteristics of the I-40 jet propulsion engine and an analysis for a range of altitudes and ram pressure ratios. Results regarding the component efficiencies, engine performance, generalizing factors, and windmilling drag characteristics are provided.
Date:
August 24, 1948
Creator:
Gendler, Stanley L. & Koffel, William K.
System:
The UNT Digital Library
Investigation of the I-40 Jet-Propulsion Engine in the Cleveland Altitude Wind Tunnel 1: Performance and Windmilling Drag Characteristics
Report presenting the performance characteristics of the I-40 jet-propulsion engine for a range of altitudes and ram pressure ratios. Results regarding component efficiencies, engine performance, generalizing factors, and windmilling drag characteristics are provided.
Date:
August 24, 1948
Creator:
Gendler, Stanley L. & Koffel, William K.
System:
The UNT Digital Library
A limit pressure coefficient and an estimation of limit forces on airfoils at supersonic speeds
Report presenting the results of an estimation of the limit forces on airfoils at supersonic speeds. The limit pressure coefficient attainable on an airfoil is shown to be about 70 percent of the pressure coefficient for a vacuum over a wide range of Mach numbers.
Date:
August 23, 1948
Creator:
Mayer, John P.
System:
The UNT Digital Library
Application of one part of Von Karman's two-dimensional transonic similarity law to drag data of NACA 65-series wings
Report presenting the use of Von Karman's two-dimensional transonic similarity law as applied to drag data of three different thickness wings with NACA 65-series sections and aspect ratios of 7.6 over a range of Mach numbers. The correlation was found to be satisfactory, with results better in the subsonic range than in the supersonic range.
Date:
August 24, 1948
Creator:
Amer, Kenneth B.
System:
The UNT Digital Library
Preliminary Aerodynamic Investigation of the Effect of Camber on a 60 Degree Delta Wing with Round and Beveled Leading Edges
Memorandum presenting an exploratory investigation to determine the aerodynamic effects of camber on a 60 degree apex delta-wing model conducted in the 300 mph 7- by 10-foot tunnel. Camber variation was accomplished through the deflection of full-span round and 25 degree beveled leading-edge flaps on a flat-sided triangular plan-form wing.
Date:
August 16, 1949
Creator:
Riebe, John M. & Fikes, Joseph E.
System:
The UNT Digital Library
Experimental performance of chlorine trifluoride-hydrazine propellant combination in 100-pound-thrust rocket engine
Report presenting an investigation of the experimental performance of chlorine triflouride and hydrazine measured over a range of propellant mixtures in a 100-pound-thrust rocket engine. Experimental values of specific impulse, volume specific impulse, heat rejection per propellant weight, nozzle thrust coefficient, and characteristic velocity were obtained as functions of percent fuel by weight in the propellant mixture.
Date:
August 15, 1949
Creator:
Ordin, Paul M. & Miller, Riley O.
System:
The UNT Digital Library
Flight Investigation at High-Subsonic, Transonic, and Supersonic Speeds to Determine Zero-Lift Drag of Bodies of Revolution Having Fineness Ratio of 6.04 and Varying Positions of Maximum Diameter
Report presenting a flight investigation of rocket-powered models at high-subsonic, transonic, and supersonic speeds to determine the zero-lift drag of fin-stabilized bodies of revolution differing in maximum diameter. All bodies had 6.04 fineness ratio and cut-off sterns with equal base area. The most favorable location out of the 20-percent, 40-percent, and 60-percent positions were evaluated for different speeds.
Date:
August 31, 1949
Creator:
Katz, Ellis R.
System:
The UNT Digital Library
Preliminary Theoretical and Flight Investigation of the Lateral Oscillation of the X-1 Airplane
Report presenting the results of flight tests showing lateral oscillation in the Bell X-1 and calculations created to determine the effects of changes in several mass and aerodynamic parameters on the lateral oscillations. Calculations indicate that lateral stability should be improved by a more positive inclination of the principal axis of inertia or a reduction of the value of yawing moment of inertia.
Date:
August 12, 1949
Creator:
Drake, Hubert M. & Wall, Helen L.
System:
The UNT Digital Library
Calculative method for estimating the interference pressure field at zero lift on a symmetrical swept-back wing mounted on a circular cylindrical body
Report presenting an approximate method for calculating the interference pressure distribution at zero lift of a symmetrical sweptback wing mounted on a circular cylindrical body with the chord plane of the wing passing through the axis of the body. An example is provided using a circular cylindrical body and an untapered wing with 60 degrees of sweepback.
Date:
August 5, 1949
Creator:
Nielsen, Jack N. & Matteson, Frederick H.
System:
The UNT Digital Library
Design Factors for 4- by 8-Inch Ram-Jet Combustor
Report presenting an investigation of a series of flame holders designed with the objective of providing a high combustion efficiency in a ramjet combustor at an inlet air velocity of 200 feet per second, inlet-air pressure of 60 inches of mercury absolute, inlet air temperature of 200 degrees Fahrenheit, and near stoichiometric fuel-air ratio. Results regarding the preliminary experiments, two parallel rows of gutters, three rows of gutters, staggered gutters, simultaneous use of three rows and staggered gutters, use of molybdenum, and magnitude of pressure fluctuations are provided.
Date:
August 11, 1949
Creator:
Male, Donald W. & Cervenka, Adolph J.
System:
The UNT Digital Library
Operating Temperatures of I-40-5 Turbojet Engine Burner Liners and the Effect of Temperature Variation on Burner-Liner Service Life
Report presenting an investigation of burner liners in a turbojet engine to determine the principal factors limiting the burner-liner service life. The investigation covered a range of engine speeds and testing was conducted to determine whether bare, ceramic-coated, or shielded thermocouples would give the most correct temperature readings.
Date:
August 23, 1948
Creator:
Wilsted, H. D.; Duffy, Robert T. & Grey, Ralph E.
System:
The UNT Digital Library
Measurements of the chordwise pressure distributions over the wing of the XS-1 research airplane in flight
Report presenting measurements of the chordwise pressure distributions over the 8-percent-thick wing of the XS-1 research airplane at a section near the midspan of the left wing. Data are presented for a Mach number range and a normal-force coefficient of about 0.33. Results regarding the upper-surface pressure distribution, lower-surface pressure distributions, and total section loads are provided.
Date:
August 4, 1948
Creator:
Beeler, De E.; McLaughlin, Milton D. & Clift, Dorothy C.
System:
The UNT Digital Library
Experimental Investigation of the Effects of Sweepback on the Flutter of a Uniform Cantilever Wing With a Variably Located Concentrated Mass
Report presenting data from 95 subsonic flutter tests conducted in the flutter research tunnel on untapered cantilever wings with sweepback angles of 0, 45, and 60 degrees and carrying a single concentrated weight. The primary purpose of the investigation was to present experimental information to be used to evaluate analytical procedures for determining the flutter speed of weighted sweptback wings. The dynamic pressure, flutter velocity, Mach number, natural and flutter frequencies, and phase-angle relationships of the stresses for the natural and flutter frequencies are presented.
Date:
August 31, 1949
Creator:
Nelson, Herbert C. & Tomassoni, John E.
System:
The UNT Digital Library
Aerodynamic Study of a Wing-Fuselage Combination Employing a Wing Swept Back 63 Degrees: Characteristics Throughout the Subsonic Speed Range With the Wing Cambered and Twisted for a Uniform Load at a Lift Coefficient of 0.25
Report presenting wind-tunnel testing to determine the independent effects of Mach and Reynolds numbers on the aerodynamic characteristics of a wing-fuselage combination with a wing with the leading edge swept back 63 degrees and with camber and twist. Results regarding the fuselage alone and the effects of camber and twist are also provided.
Date:
August 15, 1949
Creator:
Jones, J. Lloyd & Demele, Fred A.
System:
The UNT Digital Library
Effect of an Increase in Hull Length-Beam Ratio From 15 to 20 on the Hydrodynamic Characteristics of Flying Boats
Report presenting an investigation of the effect of hull length-beam ratio on the hydrodynamic characteristics of flying boats that extend to a length-beam ratio of 20. The results are compared with flying boats having a length-beam ratio of 15. Results regarding longitudinal stability, spray characteristics, take-off performance, taxiing and take-off behavior in waves, landing behavior in waves, and a summary chart are provided.
Date:
August 24, 1949
Creator:
Carter, Arthur W. & Whitaker, Walter E., Jr.
System:
The UNT Digital Library