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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

Description: 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.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Distribution of losses behind a compressor rotor as measured by a rotating rake

Description: Report presenting a rotating total-pressure survey rake to obtain wake measurements of a compressor rotor. Results indicated that there was a considerable radial flow of the inboard-blade boundary layer and little radial flow of the inner casing boundary layer. Results regarding the variation in total-pressure-loss distribution with Mach number, variation in total-pressure-loss distribution with angle of attack, contour plots, spanwise variation in total-pressure-loss coefficient, variation of … more
Date: January 17, 1956
Creator: Godwin, William R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

An experimental study of a method for designing fuselage side air inlets for high performance at transonic and low supersonic speeds

Description: Report presenting a brief experimental investigation of a method for designing fuselage side air inlets with high internal total-pressure recovery and zero spillage drag at a specified design inlet mass-flow ratio. With a scoop designed according to the concept, near-zero spillage drag can be attained at the design inlet mass-flow ratio through a range of Mach numbers. Results regarding pressure recovery and drag due to the scoop are provided.
Date: January 17, 1955
Creator: Howell, Robert R. & Trescot, Charles D., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Effect of large negative dihedral of the horizontal tail on longitudinal and lateral stability characteristics of a swept-wing configuration at transonic speeds

Description: Report presenting the longitudinal and lateral stability characteristics of a 40 degree swept-wing fighter model with and without horizontal tails of 0 degrees and 22.5 degrees negative dihedral for a range of Mach numbers, angles of attack, and sideslip.
Date: January 17, 1956
Creator: Arabian, Donald D.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Comparison of Performance and Component Frontal Areas of Hypothetical Two-Spool and One-Spool Turbojet Engines

Description: For constant-mechanical-speed operation, the two-spool thrust values are as great as or greater than the one-spool thrust values over the entire flight range considered, while the specific fuel consumption for the two engines agrees within 1 percent. The maximum difference in thrust occurs at Mach 2.8 in the stratosphere, where the two-spool thrust advantage is about 9 percent for operation with the after burning.
Date: January 17, 1956
Creator: Dugan, James F., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Effects of compressor interstage bleed and adjustable inlet guide vanes on compressor stall characteristics of a high-pressure-ratio turbojet engine at altitude

Description: Report presenting the stall characteristics of the J71-A2(X-29) turbojet engine as determined in an altitude test chamber. When the normal high-speed configuration of bleeds closed, inlet guide vanes open was operated in the low-speed range, the stall-limit line intersected the operating line at 4067 and 4630 rpm. Results regarding compressor performance at steady state and stall and fuel flow at steady state and stall are provided.
Date: January 17, 1956
Creator: Mallett, William E. & Groesbeck, Donald E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

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

Description: 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.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

The effect of stick-force gradient and stick gearing on the tracking accuracy of a fighter airplane

Description: 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.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

An Investigation of the Effects of Jet Exhaust and Reynolds Number Upon the Flow Over the Vertical Stabilizer and Rudder of the Douglas D-558-II Research Airplane at Mach Numbers of 1.62, 1.93, and 2.41

Description: Memorandum presenting an investigation to determine the effects of jet exhaust and Reynolds number on the flow over the vertical stabilizer and rudder of the Douglas D-558-II research airplane with special attention to an understanding of the rudder reversals experienced in flight on the full-scale airplane. Tests were made at Mach numbers of 1.62, 1.93, and 2.41 over a range of ratios of jet static pressure to stream static pressure from the jet-off ratio to about 40 and for a maximum range of… more
Date: June 17, 1954
Creator: Grigsby, Carl E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Thrust and pumping characteristics of a series of ejector-type exhaust nozzles at subsonic and supersonic flight speeds

Description: Report presenting an investigation conducted in the 8- by 6-foot supersonic wind tunnel to determine the thrust and pumping characteristics of a series of ejector exhaust nozzles. Data were obtained for various ejector diameter and spacing ratios at a range of Mach numbers, pressure-ratio ranges, and secondary-primary weight-flow ratios. Results regarding the primary-nozzle mass-flow coefficients, performance comparison of configurations, effect of free-stream Mach number on the ejectors, net t… more
Date: November 17, 1954
Creator: Hearth, Donald P. & Valerino, Alfred S.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Thrust and Pumping Characteristics of a Series of Ejector-type Exhaust Nozzles at Subsonic and Supersonic Flight Speeds

Description: Report presenting an investigation in the supersonic wind tunnel to determine the thrust and pumping characteristics of a series of ejector exhaust nozzles. Results indicated that the free-stream Mach number had no effect on those characteristics of the ejectors in the range for which the secondary flow was choked.
Date: November 17, 1954
Creator: Hearth, Donald P. & Valerino, Alfred S.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Compatibility of Metals with Liquid Fluorine at High Pressures and Flow Velocities

Description: Report presenting testing of specimens of various metals in selected geometric configurations exposed to liquid fluorine under controlled conditions of flow and pressure. None of the samples eroded, decomposed, or exhibited any measurable physical or chemical changes.
Date: April 17, 1958
Creator: Schmidt, Harold W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Transonic Aerodynamic and Trim Characteristics of a Multi-Engine Delta-Wing Airplane Model

Description: Memorandum presenting an investigation of three models of a delta-wing airplane designed for a long-range subsonic cruise and a supersonic dash. Results regarding the aerodynamic characteristics of the models and effect of elevon deflection on aerodynamic characteristics of the four-engine model are provided.
Date: February 17, 1956
Creator: Swihart, John M. & Foss, Willard E., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Some Interference Effects That Influence Vertical-Tail Loads at Supersonic Speeds

Description: Memorandum presenting three types of aerodynamic interference originating from forward components of airplanes, which are shown to contribute to decreased vertical-tail effectiveness. The vorticity originating from a slender fuselage ahead of the wing resulted in a marked reduction in vertical-tail effectiveness with angle of attack for one model.
Date: February 17, 1956
Creator: Edwards, S. Sherman
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Aerodynamic Performance and Static Stability and Control of Flat-Top Hypersonic Gliders at Mach Numbers From 0.6 to 18

Description: Memorandum presenting a study of aerodynamic performance and static stability and control at hypersonic speeds. In the first part of the study, the effect of interference lift is investigated by tests of asymmetric models with conical fuselages and arrow plan-form wings. In the second part, the aerodynamic performance and static stability and control characteristics of a hypersonic glider are investigated in somewhat greater detail.
Date: September 17, 1958
Creator: Syvertson, Clarence A.; Gloria, Hermilo R. & Sarabia, Michael F.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Investigation of the possibility of simplifying missile guidance systems by the use of free-floating flaps and spring-mounted control surfaces

Description: Report presenting an investigation of the use of aerodynamic and mechanical devices for improving the response of guided missiles. An analysis indicates that the use of free-floating flaps and spring-mounted control surfaces should be able to increase maneuverability to the point that electronic automatic stabilization and gain-adjusting devices can be eliminated.
Date: May 17, 1956
Creator: Hikido, Katsumi; Hayashi, Paul H. & Lessing, Henry C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Aerodynamic Loads on an External Store Adjacent to an Unswept Wing at Mach Numbers Between 0.75 and 1.96

Description: Report presenting an investigation to determine the aerodynamic characteristics of a sting-mounted Douglas Aircraft Company store in the presence of an unswept semispan cantilevered wing of aspect ratio 4.0. Results regarding wing loads and store loads are provided.
Date: February 17, 1956
Creator: Hadaway, William M.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Evaluation of Some Aerodynamic Controls for a Low Aspect Ratio Missile

Description: "Results of a static stability controls investigation carried out with a very low-aspect-ratio delta-winged missile are presented. Control effectiveness comparisons are made for tail, canard, and nose control configurations with respect to angle of attack, angle of bank, and Mach number. Trim capabilities of the various configurations are also presented" (p. 1).
Date: July 17, 1958
Creator: Winovich, Warren & Higdon, Nancy S.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Method for Estimating Pitching-Moment Interference of Wing-Body Combinations at Supersonic Speed

Description: Report presenting an investigation into the effects of interference at supersonic speeds on the aerodynamic properties of wing-body combinations to determine the pitching moments. The correlation points of various wing-body shapes are provided and suggestions for modifications are made.
Date: April 17, 1952
Creator: Kaattari, George E.; Nielsen, Jack Norman & Pitts, William C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

An Analog Study of the Influence of Internal Modifications to a Wing Leading Edge on Its Transient Temperature Rise During Highspeed Flight

Description: Memorandum presenting an investigation made with an electrical heat-flow analog to determine the effect of internal modifications to a wing leading edge on the surface-temperature rise and temperature distribution for conditions of transient aerodynamic heating at high supersonic speeds. Results regarding the leading-edge temperature rise, influence of conduction on leading-edge temperature for skins of uniform thickness, and surface-temperature distribution are provided.
Date: March 17, 1958
Creator: Neel, Carr B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Aerodynamic Loads on an External Store Adjacent to an Unswept Wing at Mach Numbers Between 0.75 and 1.96

Description: Memorandum presenting an investigation in the blowdown tunnel of the pressure tunnel to determine the aerodynamic characteristics of a sting-mounted Douglas Aircraft Company store in the presence of, but not attached to, an unswept semispan cantilevered wing of aspect ratio 4.0. The influence of the store on the aerodynamic characteristics of the wing was also obtained.
Date: February 17, 1956
Creator: Hadaway, William M.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Investigation of a 0.6 Hub-Tip Radius-Ratio Transonic Turbine Designed for Secondary-Flow Study 3 - Experimental Performance With Two Stator Configurations Designed to Eliminate Blade Wakes and Secondary-Flow Effects and Conclusions From Entire Stator Investigation

Description: Memorandum presenting two turbine stator configurations designed to investigate the effect on turbine performance of either reducing or eliminating stator-blade wakes, secondary-flow loss accumulations, and circumferential variations in total pressure at the stator exits. Results regarding stator surveys, overall performance with the semivaneless stator, overall performance with the standard stator with spacer, rotor-exit surveys, and rotor-blade momentum loss are provided.
Date: September 17, 1957
Creator: Rohlik, Harold E.; Wintucky, William T. & Moffitt, Thomas P.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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