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Force, moment, and pressure-distribution characteristics of rectangular wings at high angles of attack and supersonic speeds

Description: Report presenting experimental force and moment data for rectangular wings of aspect ratios 1, 2, and 3 at a range of angles of attack and Mach numbers. Shock-expansion theory was found to adequately predict the span load distribution in the two-dimensional flow region below the shock-detachment angle. Results regarding basic physical data, the attached regime, and the detached regime are provided.
Date: February 13, 1956
Creator: Pitts, William C.
Partner: UNT Libraries Government Documents Department

Flight determination of the longitudinal stability in accelerated maneuvers at transonic speeds for the Douglas D-558-II research airplane including the effects of an outboard wing fence

Description: The results of transonic flight measurements of the longitudinal stability characteristics of the Douglas D-558-II research airplane in the original configuration and with outboard fences mounted on the wings are presented. The levels of normal-force coefficient at which the stability decreases and pitch-up starts have been determined for both airplane configurations at Mach numbers up to about 0.94.
Date: March 13, 1953
Creator: Fischel, Jack & Nugent, Jack
Partner: UNT Libraries Government Documents Department

Exploratory materials and missile-nose-shape tests in a 4,000 degrees F supersonic air jet

Description: Report presenting some exploratory materials and nose-shape tests in a small supersonic air jet with a stagnation temperature of approximately 4000 degrees Fahrenheit. Materials considered included graphite, copper, carbon steel, and stainless steel, and the nose shapes included 90 degree total-angle cones, hemispherical-face cylinders, and flat-face cylinders. The aerodynamic heat transfer to flat-face cylinders is appreciably less than to hemispherical-face cylinders.
Date: December 13, 1956
Creator: Purser, Paul E. & Hopko, Russell N.
Partner: UNT Libraries Government Documents Department

Engineering method of ram-jet thrust determination based on experimentally obtained combustor parameters

Description: From Summary: "A parameter is introduced which simplifies the accounting for pressure losses in ram-jet combustors. This parameter, called the combustor-force coefficient, relates the jet force and the total pressure at the combustion-chamber entrance. Experimental data for several different combustors are presented for evaluation and comparison."
Date: August 13, 1953
Creator: Dettwyler, H. Rudolph & Faget, Maxime A.
Partner: UNT Libraries Government Documents Department

Effect of fuel volatility characteristics on ignition-energy requirements in a turbojet combustor

Description: Report presenting an investigation to determine the effect of fuel volatility characteristics on the minimum spark energy required to ignite a single tubular turbojet-engine combustor. Results regarding the ignition at sea-level conditions, ignition at altitude conditions, relation between distillation data and minimum ignition-energy requirements, and application of relation to data from a previous investigation are provided.
Date: January 13, 1953
Creator: Foster, Hampton H. & Straight, David M.
Partner: UNT Libraries Government Documents Department

An Investigation of Longitudinal Control Characteristics of a Wing-Tip Control Surface on a Sweptback Wing at Transonic Speeds by the NACA Wing-Flow Method

Description: Report presenting an investigation of the longitudinal control effectiveness of a full-chord wing-tip control surface on a wing with 35 degrees of sweepback, 12 percent thickness perpendicular to the quarter-chord line, an aspect ratio of 3.01, and a taper ratio of 0.605 at a range of Mach numbers. Wing-tip control was only 1/6 as effect in producing pitching moment at subsonic speeds as a flap type control and 1/2 as effect at low-supersonic speeds.
Date: June 13, 1952
Creator: Trant, James P., Jr.
Partner: UNT Libraries Government Documents Department

Investigation of interference, lift, drag, and pitching moment of a series of rectangular wing and body combinations at Mach numbers of 1.62, 1.93,and 2.41

Description: Report presenting an investigation of a series of rectangular wing and body combinations at Mach numbers 1.62, 1.93, and 2.41 to determine the effects of aspect ratio, incidence angle, and forebody length on the interference lift, drag, and pitching moment. A limited investigation to determine the effect of Reynolds number on the wings in the presence of the body was also carried out. Information regarding wing lift, basic quantities for interference evaluation, interference qualities, contributions of the various components, and the concept of wing-lift carry-over is provided.
Date: August 13, 1952
Creator: Coletti, Donald E.
Partner: UNT Libraries Government Documents Department

Reduction of wave drag of wing-body combinations at supersonic speeds through body distortions

Description: Report presenting some methods providing sizable reductions in drag for aspect ratios of current interest. The drag savings are maintained over a wide Mach number range, particularly for low-aspect-ratio wings. A significant part of the drag reduction is found to be due to the nonaxisymmetric distortion.
Date: April 13, 1956
Creator: Pitts, William C.
Partner: UNT Libraries Government Documents Department

Stability and control characteristics at low speed of a 1/10-scale model of MX-1554A design

Description: Report presenting an investigation of the low-speed stability and control characteristics of a scale model of the proposed MX-1554A design. It employs a triangular wing and triangular stabilizing surfaces. Results regarding the effect of wing incidence, tail position, fences, and chord extensions on the longitudinal characteristics are provided.
Date: January 13, 1953
Creator: Lockwood, Vernard E. & Solomon, Martin
Partner: UNT Libraries Government Documents Department

Performance of wedge-type boundary layer diverters for side inlets at supersonic speeds

Description: Report presenting an experimental investigation to determine the effect of several wedge-type boundary-layer diverters on drag and inlet pressure recovery in the 8- by 6-foot supersonic wind tunnel at Mach numbers of 1.5, 1.8, and 2.0. The model consisted of two rectangular ramp-type inlets mounted on the NACA RM-10 body of revolution. Results regarding variation of inlet pressure recovery and configuration drag with inlet mass-flow ratio, changes in the shock pattern off the inlet ramp, pressure-recovery-mass-flow characteristics, and drag coefficients are provided.
Date: May 13, 1954
Creator: Campbell, Robert C. & Kremzier, Emil J.
Partner: UNT Libraries Government Documents Department

Tests in the Ames 40- by 80-foot wind tunnel of an airplane configuration with an aspect ratio 3 triangular wing and an all-movable horizontal tail: Longitudinal and lateral characteristics

Description: Report presenting an investigation to determine the low-speed large-scale characteristics of an aspect ratio 3 triangular-wing airplane model. The model consisted of the wing in combination with a fuselage of fitness ratio 12.5, a thin, triangular vertical tail with a constant-chord rudder, and a thin, unswept, all-movable tail.
Date: April 13, 1953
Creator: Koenig, David G.
Partner: UNT Libraries Government Documents Department

Investigation of mass-flow and pressure recovery characteristics of several underslung scoop-type inlets at free-stream Mach numbers of 2.0, 1.8, 1.5, and 0.66

Description: Report presenting testing of several underslung scoop-type inlets mounted on a body of revolution at several Mach numbers through a range of angles of attack. Geometric differences between inlets included ramp angle, frontal area, splitter-plate height, and aspect ratio. Results regarding inlet stability, peak pressure recoveries, and total-pressure distortions are provided.
Date: March 13, 1957
Creator: Valerino, Alfred S. & Zappa, Robert F.
Partner: UNT Libraries Government Documents Department

Preliminary theoretical investigation of several methods for stabilizing the lateral motion of a high-speed fighter airplane towed by a single cable

Description: Report presenting a theoretical investigation of the lateral stability of a towed high-speed fighter plane using a fighter cruising at supersonic speed at 50,000 feet and a 1000-foot cable. The motion of this configuration was shown to have highly unstable oscillation caused by the towline restraint, but the configuration can be stabilized by choosing the right position for the towline connection and several types of automatic controls.
Date: March 13, 1953
Creator: Schy, Albert A. & Woodling, Carroll H.
Partner: UNT Libraries Government Documents Department

Longitudinal stability characteristics in maneuvering flight of the Convair XF-92A delta-wing airplane including the effects of wing fences

Description: Report presenting the longitudinal stability characteristics of the Convair XF-92A delta-wing airplane in maneuvering flight. The investigation included the determination of the characteristics of the basic airplane and the effects of two wing fence configurations on the characteristics.
Date: January 13, 1955
Creator: Sisk, Thomas R. & Muhleman, Duane O.
Partner: UNT Libraries Government Documents Department

Longitudinal stability characteristics of the Convair YF-102 airplane determined from flight tests

Description: Report presenting an analysis of the longitudinal stability characteristics of the cambered-wing version of the Convair YF-102 airplane at a range of Mach numbers and altitudes. Results regarding longitudinal trim, stall maneuvers, dynamic longitudinal stability, maneuvering stability, stability and control effectiveness parameters, and artificial-feel system are provided.
Date: December 13, 1956
Creator: Andrews, William H.; Sisk, Thomas R. & Darville, Robert W.
Partner: UNT Libraries Government Documents Department

Angle-of-attack-supersonic performance of a configuration consisting of a ramp-type scoop inlet located either on top or bottom of a body of revolution

Description: From Introduction: "In reference 1, in which the performance of conical supersonic scoop inlets on circular fuselages is reported, the drag of the bottom-inlet configuration was considerably higher than for the top inlet."
Date: May 13, 1954
Creator: Kremzier, Emil J. & Campbell, Robert C.
Partner: UNT Libraries Government Documents Department

Effect of fuel-air ratio concentration in combustion zone on combustion performance of a 16-inch ram-jet engine

Description: The results of fuel-air ratio and temperature surveys made in the flame stabilizing zone of a 16-inch ram-jet combustor indicated that the distribution of combustible mixture immediately downstream of a flame holder should be mechanically controlled if a preferred mixture composition is to be maintained in that zone. A sloping-baffle combustor configuration gave combustion efficiencies of 90 percent or greater over a range of fuel-air ratios from 0.010 to 0.045.
Date: April 13, 1953
Creator: Cervenka, A. J.; Bahr, D. W. & Dangle, E. E.
Partner: UNT Libraries Government Documents Department

Some observations of flow at the throat of a two-dimensional diffuser at a Mach number of 3.85

Description: Report presenting an experimental investigation at a Mach number of 3.85 in the supersonic wind tunnel to study the flow patterns at the throat of a two-dimensional single-shock diffuser and to evaluate qualitatively several schemes for improving the turning conditions. Schileren observations were made for supercritical inlet operation and conditions of maximum total-pressure recovery.
Date: November 13, 1952
Creator: Connors, James F. & Woollett, Richard R.
Partner: UNT Libraries Government Documents Department

A study of a symmetrical, circular, internal, compression inlet

Description: From Summary: "A preliminary experimental study of symmetrical, circular, internal compression inlets has shown that they attain pressure recovery equal to that measured by conical nose inlets at Mach numbers up to about 2.3. This pressure recovery was obtained with configurations having essentially zero pressure drag of the external surfaces."
Date: February 13, 1956
Creator: Mossman, Emmet A. & Pfyl, Frank A.
Partner: UNT Libraries Government Documents Department

Static-pressure error calibrations for nose-boom airspeed installations of 17 airplanes

Description: Report presenting a flight investigation to determine the static-pressure errors for nose-boom airspeed installations of 17 airplanes. Both research-type and service-type aircraft are covered in the investigation. Results indicated that the magnitude of static-pressure errors for the airspeed installations of all the airplanes is shown to vary with airplane geometric characteristics that include nose-boom length, fuselage diameter, and nose fineness ratio.
Date: March 13, 1957
Creator: Larson, Terry J.; Stillwell, Wendell H. & Armistead, Katharine H.
Partner: UNT Libraries Government Documents Department

Preliminary flight survey of fuselage and boundary-layer sound-pressure levels

Description: Report presenting preliminary flight surveys of noise inside fuselages and in the fuselage boundary layer, which were obtained in order to determine the magnitude of the noise and relative importance of engine noise and noise due to the boundary layer. Results indicated that the sound-pressure level continued to increase with airspeed to the highest airspeed obtained, although the rate of increase at supersonic speeds was less than at subsonic speeds. Testing occurred on the B-47A and D-558-II airplanes.
Date: May 13, 1958
Creator: McLeod, Norman J. & Jordan, Gareth H.
Partner: UNT Libraries Government Documents Department

Effect of design changes and operating conditions on combustion and operational performance of a 28-inch diameter ram-jet engine

Description: The results of an altitude test-chamber investigation of the effects of a number of design changes and operating conditions on altitude peformance of a 28-inch diameter ram jet engine are presented. Most of the investigation was for a simulated flight Mach number of 2.0 above the tropopause. Fuel-air distribution, gutter width, the presence of a pilot flame, cimbustion-chamber-inlet temperature, and exhaust-nozzle throat area were found to have significant effects on limits of combustion. Combustion efficiency increased with increasing combustion-chamber-inlet temperature and was adversely affected by an increase in the exhaust-nozzld area. Similiar lean limits of combustion were obtained for both Diesel fuel and normal heptane, but combustion efficiences obtained with Diesel fuel were lower than those obtained with normal heptane.
Date: February 13, 1952
Creator: Shillito, T. B. & Nakanishi, Shigeo
Partner: UNT Libraries Government Documents Department

Tables and charts for thermodynamic calculations involving air and fuels containing boron, carbon, hydrogen, and oxygen

Description: Report presenting tables and charts of gas properties for use in thermodynamic calculations for engine cycles involving the combustion of air and any fuel or combustion of fuels containing carbon, boron, hydrogen, and oxygen. Dissociation and phase changes may be accounted for with the method presented, which does not require the presentation of separate data for each fuel-air ratio.
Date: July 13, 1956
Creator: Hall, Eldon W. & Weber, Richard J.
Partner: UNT Libraries Government Documents Department

Effects of free-stream Reynolds number, engine installation, and model scale on stability characteristics of a translating-spike inlet at Mach 2.0

Description: Report presenting the effect of free-stream Reynolds number, engine installation, and model scale on inlet stability limits and on the amplitude and frequency of buzz. The data was obtained at mach number 2.0 and a range of angles of attack. Results regarding the free-stream Reynolds number effect, model scale, and effect of engine on stability are provided.
Date: November 13, 1957
Creator: Musial, Norman T. & Bowditch, David
Partner: UNT Libraries Government Documents Department