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Large-scale low-speed wind-tunnel tests of a model having a 60 degree delta horizontal canard control surface and wing to obtain static-longitudinal-stability and canard surface hinge-moment data
Report presenting a wind-tunnel investigation of a model equipped with a 60 degree delta wing and a 60 degree delta horizontal all-movable canard control surface to determine the stability, control, and canard-surface hinge-moment characteristics at low speeds and at a Reynolds number of 9 x 10(exp 6). Two longitudinal positions of the canard surface were tested. Results regarding lift and pitching moment, drag, and hinge moment are provided.
Date:
June 17, 1954
Creator:
Burrows, Dale L.
System:
The UNT Digital Library
High-Altitude Performance of an Experimental Turbular Prevaporizing Combustor
Memorandum presenting an investigation of an experimental tubular combustor that provides for prevaporizing and premixing of the fuel with a part of the air before its introduction into the combustion zone. Combustion efficiency and total-pressure loss data are presented for three configurations selected from a total of 43 different modifications investigated. Results regarding the combustor development, comparison of liquid and gaseous fuel, combustor total-pressure losses, combustor-outlet temperature distribution, and evaluation of experimental prevaporizing combustors are provided.
Date:
December 9, 1954
Creator:
Butze, Helmut F.
System:
The UNT Digital Library
Investigation to Mach number 2.0 of shock-positioning control systems for a variable-geometry inlet in combination with a J34 turbojet engine
Report presenting shock-position controls designed to actuate the translating spike and variable bypass of a variable-geometry inlet in the 8- by 6-foot supersonic tunnel. The operation of the inlet was observed in combination with a J34 turbojet engine at a range of Mach numbers. Results regarding terminal-shock-positioning control systems and combination control are provided.
Date:
December 20, 1954
Creator:
Leissler, L. Abbott & Nettles, J. Cary
System:
The UNT Digital Library
Low-Amplitude Damping-in-Pitch Characteristics of Four Tailless Swept Wing-Body Combinations at Mach Numbers From 0.85 to 1.30 as Obtained With Rocket-Powered Models
Report presenting an investigation to determine the damping-in-pitch characteristics of four rocket-powered wing-body combinations for a range of Mach numbers from 0.85 to 1.30. The models were tested at the same center-of-gravity location and had identical bodies. Information about the trim, lift, static longitudinal stability, dynamic longitudinal stability, and drag is provided.
Date:
November 24, 1954
Creator:
D'Aiutolo, Charles T.
System:
The UNT Digital Library
Experimental investigation of drag of afterbodies with exiting jet at high subsonic Mach numbers
Report presenting an investigation to determine the pressure drag of various blunt-based conical afterbodies at a range of Mach numbers. A generalized series of bodies was included which incorporated convergent nozzles discharging unheated jets at various pressures from the base. Results regarding the afterbodies without the jet and afterbodies with the jet are provided.
Date:
November 29, 1954
Creator:
Salmi, Reino J.
System:
The UNT Digital Library
Investigation at Supersonic Speeds of the Effect of Jet Mach Number and Divergence Angle of the Nozzle Upon the Pressure of the Base Annulus of a Body of Revolution
Report presenting an investigation in the 9-inch supersonic tunnel to determine the jet effects for varying jet Mach number and nozzle divergence angle upon the pressure on the base annulus of a model with a cylindrical afterbody. Testing occurred over a wide range of jet static pressure ratios and Mach numbers. Results regarding sonic jets and supersonic jets are provided.
Date:
December 17, 1954
Creator:
Bromm, August F., Jr. & O'Donnell, Robert M.
System:
The UNT Digital Library
The effect of stick-force gradient and stick gearing on the tracking accuracy of a fighter airplane
Report presenting steady straight-and-level and steady turning tracking runs against an aerial target using an F-51H airplane equipped with a fixed optical sight and with various combinations of maneuvering stick-force and stick-deflection gradients. Results regarding aim wander, elevator movement, and stick-force variation for various test conditions are provided.
Date:
December 17, 1954
Creator:
Abramovitz, Marvin & Van Dyke, Rudolph D., Jr.
System:
The UNT Digital Library
Investigation of Supersonic-Compressor Rotors Designed with External Compression
Report presenting an investigation of the possibility of utilizing the relatively good characteristics of the spike-type diffuser in the supersonic compressor. Results regarding the overall performance, inlet conditions, outlet conditions, entrance flow conditions, and estimated performance of subsonic portion of rotor passage are provided.
Date:
September 24, 1954
Creator:
Jahnsen, Lawrence J. & Hartmann, Melvin J.
System:
The UNT Digital Library
The Effect of Wing Profile on the Transonic Characteristics of Rectangular and Triangular Wings Having Aspect Ratios of 3: Transonic Bump Technique
Report presenting an investigation to determine the effect of wing profile on the transonic aerodynamic characteristics of rectangular and triangular wings with aspect ratios of 3. Five wings were compared over a range of Mach and Reynolds number. Results regarding the rectangular and triangular wings and use of transonic area rule are provided.
Date:
October 27, 1954
Creator:
Nelson, Warren H. & Frank, Joseph L.
System:
The UNT Digital Library
A flight investigation at transonic speeds and small angles of attack of the aerodynamic characteristics of a model having a 45 degree sweptback wing of aspect ratio 3 with an Naca 64A006 airfoil section
Report presenting an investigation of the longitudinal aerodynamic characteristics of a model with a 45 degree sweptback wing of aspect ratio 3 and a 45 degree sweptback cruciform tail at transonic speeds and small angles of attack by a free-fall recoverable-model technique. Results regarding lift, drag, static longitudinal stability, dynamic longitudinal stability, and loading distribution over the fuselage are provided.
Date:
January 25, 1954
Creator:
Holdaway, George H.
System:
The UNT Digital Library
Effects of angle of attack and airfoil profile on the two-dimensional flutter derivatives for airfoils oscillating in pitch at high subsonic speeds
Report presenting two-dimensional aerodynamic lift and moment flutter derivatives for moderate and high angles of attack for several airfoil profiles varying in thickness and thickness distribution. The results indicate that the variables angle of attack, airfoil profile, reduced frequency, and Mach number all have significant interdependent effects.
Date:
October 15, 1954
Creator:
Wyss, John A. & Herrera, Raymond
System:
The UNT Digital Library
Sea-level static equilibrium performance of actual two-spool turbojet engine and comparison with hypothetical engine
Report presenting an evaluation of the sea-level static equilibrium performance of an early developmental two-spool turbojet engine and its components and a comparison with a hypothetical two-spool turbojet engine. Results regarding the equilibrium performance of the actual engine, including its compressor performance, turbine performance, component operation, and engine performance and a comparison of those categories with the hypothetical engine are provided.
Date:
September 15, 1954
Creator:
Dugan, James F., Jr.; Jansen, Emmert T.; Rohlik, Harold E. & Mallett, William E.
System:
The UNT Digital Library
Low-Speed Measurements of Rolling and Yawing Stability Derivatives of a 60 Degree Delta-Wing Model
Memorandum presenting an investigation in the free-flight tunnel to determine the low-speed rolling and yawing stability derivatives of a 60 degree delta-wing model from 0 to 30 degrees angle of attack. The derivatives were measured by the free-to-damp oscillation technique and by the steady-roll technique.
Date:
December 27, 1954
Creator:
Johnson, Joseph L., Jr.
System:
The UNT Digital Library
Lift and drag characteristics of the Douglas X-3 research airplane obtained during demonstration flights to a Mach number of 1.20
Report presenting lift and drag data obtained during the Douglas X-3 airplane. The data covered the Mach number range from 0.82 to 1.20 with considerable variation in lift. A comparison of the flight data with data from wind-tunnel and rocket-model tests shows that the model tests adequately predict the performance of the airplane.
Date:
December 6, 1954
Creator:
Bellman, Donald R. & Murphy, Edward D.
System:
The UNT Digital Library
Effects of Secondary-Air Flow on Annular Base Force of a Supersonic Airplane
Memorandum presenting an investigation of the effect of base bleed on the base force of a supersonic-interceptor model in the 8- by 6-foot supersonic wind tunnel. Two groups of fixed-geometry nozzles and shroud combinations simulating double-iris-type configurations were evaluated over a range of secondary to primary exit-diameter ratios.
Date:
October 11, 1954
Creator:
Vargo, Donald J.
System:
The UNT Digital Library
A preliminary investigation of the use of circulation control to increase the lift of a 45 degree sweptback wing by suction through trailing-edge slots
Report presenting an investigation to determine the effectiveness of circulation control by applying suction through trailing-edge slots on a 45 degree sweptback wing. Various chordwise extents and depths of slot were investigated with and without deflection of a trailing-edge split flap. Results regarding the correlation of two-dimensional-section results with Ehlers' theory, effectiveness of circulation control on a sweptback wing, effect of slot configuration on circulation control, effect of trailing-edge split flap on circulation control, effect of circulation control on pitching moment, and circulation control at angle of attack are provided.
Date:
December 14, 1954
Creator:
Cook, Woodrow L.; Griffin, Roy N., Jr. & Hickey, David H.
System:
The UNT Digital Library
Stabilization of 50-Percent Magnesium - JP-4 Slurries With Some Aluminum Soaps of C(Sub 8) Acids
Report presenting an exploratory investigation of three aluminum disoaps of C(sub 8) acids to determine the gelling properties and stabilizing ability in slurries of 50 percent magnesium power and JP-4 fuel. All of the soaps were found to gel the slurries satisfactorily and to exhibit adequate reproducibility of gel properties. Results regarding the soap behaviors, effects of temperature, viscosity, and formation of the gel structures are provided.
Date:
May 13, 1954
Creator:
Caves, Robert M.
System:
The UNT Digital Library
Effect on the low-speed aerodynamic characteristics of a 49 degree sweptback wing having an aspect ratio of 3.78 of blowing air over the trailing-edge flap and aileron
Report presenting an investigation in the full-scale tunnel to determine the effects on the aerodynamic characteristics of a 49.1 degree sweptback wing of blowing a high-energy stream of air over a trailing-edge flap and an aileron. The results indicated that significant increases in lift coefficient and an improvement in aileron effectiveness may be obtained by the blowing method of boundary-layer control.
Date:
April 23, 1954
Creator:
Whittle, Edward F., Jr. & Lipson, Stanley
System:
The UNT Digital Library
Wind-tunnel investigation of the effect of clipping the tips of triangular wings of different thickness, camber, and aspect ratio - transonic bumb method
Report presenting an investigation on a transonic bump to determine the aerodynamic characteristics of a series of triangular wings. Four basic triangular-wing plan forms with different aspect ratios, taper ratios, and combinations of tip clipping were tested over a range of Mach and Reynolds numbers. Results regarding angle of attack, drag coefficient, pitching-moment coefficient with lift coefficient, and various curves are provided.
Date:
February 3, 1954
Creator:
Emerson, Horace F.
System:
The UNT Digital Library
Application of Pulse Techniques to Strain Gages
Memorandum presenting pulse techniques applied to strain gages for increasing the output level and extending the usable range. Bonded and unbonded strain gages which normally operate with exciting potentials between 3.5 and 14 volts operated satisfactorily with 200-volt pulses of 1-microsecond duration and a repetition rate of 350 per second. Results regarding maximum allowable voltages, effective pulse duration, sensitivity, minimum readable signal, effects of cable capacitance and inductance, sensitivity to external noise, and linearity are provided.
Date:
May 4, 1954
Creator:
Sanders, Newell D. & Brodie, George H.
System:
The UNT Digital Library
Altitude performance of compressor, combustor, and turbine components of XT38-A-2 turboprop engine
From Introduction: "The overall performance and operational characteristics are reported in reference 1. The performance of the components (compressor, combustor, turbine) is reported herein."
Date:
August 27, 1954
Creator:
Schulze, Frederick W. & Prince, William R.
System:
The UNT Digital Library
Effect of wing flexibility on the damping roll of a notched delta-wing body combination between Mach numbers 0.6 and approximately 2.2 as determined with rocket-propelled models
Report presenting an investigation with sting-mounted rocket-propelled models in free flight at approximately zero lift to determine the effect of wing flexibility on the damping-in-roll characteristics of a wing-body combination over a range of Mach numbers.
Date:
June 18, 1954
Creator:
Bland, William M., Jr.
System:
The UNT Digital Library
Engine performance of alloy 73J turbine blades cast to predetermined grain sizes
Report presenting an investigation to determine the suitability of alloy 73J as a turbojet turbine-blade alloy and the effect of grain size on engine operating life. Blades made of alloy 73J were run in a full-scale J33-9 turbojet engine under cyclic conditions. Results regarding the macroexamination of blades, engine life, engine life against stress-rupture life, blade failures, blade elongation, metallographic results, and blade dimensions and the possible effects of overdimensions are provided.
Date:
July 2, 1954
Creator:
Johnston, James R.; Gyorgak, Charles A. & Weeton, John W.
System:
The UNT Digital Library
Some effects of aileron span, aileron chord, and wing twist on rolling effectiveness as determined by rocket-powered model tests and theoretical estimates
A determination of the variation of rolling effectiveness with spanwise aileron extent for full-chord ailerons on a sweptback wing over a range of Mach numbers. The test wings had NACA 65A006 airfoil sections, an aspect ratio of 4.0, 45 degrees sweepback at the quarter-chord line, and a taper ratio of 0.6. Results regarding ailerons and twisted wings are provided.
Date:
September 14, 1954
Creator:
Strass, H. Kurt & Tucker, Warren A.
System:
The UNT Digital Library