184 Matching Results

Search Results

Results: 1 - 24 next
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.
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.
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.
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
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.
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.
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.
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.
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.
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.
Partner: UNT Libraries Government Documents Department
open access

Analysis of a Nuclear-Powered Liquid-Metal Ducted-Fan Cycle

Description: From Introduction: "The results are presented for flight Mach numbers of 0.9 to 1.5 at an altitude of 50,000 feet. The effect of flight altitude on optimum engine design-point airplane performance is also shown."
Date: December 17, 1952
Creator: Rom, F. E. & Wachtl, W. W.
Partner: UNT Libraries Government Documents Department
open access

Investigation of Ejection Releases of an MB-1 Rocket From a 0.04956-Scaled Model of the Convair F-106A Airplane at Several Mach Numbers and Simulated Altitudes

Description: "As a continuation of an investigation of the ejection release characteristics of an internally carried MB-1 rocket in the Convair F-106A airplane, fin modifications at additional Mach numbers and simulated altitudes have been studied in the 27- by 27-inch preflight jet of the Langley Pilotless Aircraft Research Station at Wallops Island, Va. The MB-1 rocket was ejected with fins open, fins closed, fins closed with a shroud around the fins, and fins folded with a "boattail" placed in between th… more
Date: September 17, 1957
Creator: Lee, John B. & Basford, Robert C.
Partner: UNT Libraries Government Documents Department
open access

Influence of Automatic Control of Roll Coupling and Pitch-Up on Tail Loads

Description: Memorandum presenting a study of the effects of automatic augmentation or controlling systems on the tail loads experienced in rolling maneuvers and in pitch-up. The results were calculated on an analog computer and the equations of five degrees of freedom were used for the rolling maneuvers and three degrees of freedom for pitch-up.
Date: June 17, 1957
Creator: Stone, Ralph W., Jr.
Partner: UNT Libraries Government Documents Department
open access

Total-Pressure Distortion and Recovery of Supersonic Nose Inlet With Conical Centerbody in Subsonic Icing Conditions

Description: Memorandum presenting an investigation of ice formation on a full-scale unheated supersonic nose inlet in the icing tunnel to determine its effect on compressor-face total-pressure distortion and recovery. Inlet angle of attack was varied from 0 to 12 degrees, free-stream Mach number from 0.17 to 0.28, and compressor-face Mach number from 0.10 to 0.47. The addition of ice to the inlet components was found to increase total-pressure-distortion levels and decreased recovery values compared with c… more
Date: September 17, 1957
Creator: Gelder, Thomas F.
Partner: UNT Libraries Government Documents Department
open access

Investigation of Wingless Missile Configurations with Folding Controls and Low-Aspect-Ratio Stabilizing Surfaces

Description: Results regarding a wind-tunnel investigation of wingless missile configurations with cylindrical bodies and conical or hemispherical noses, extensible control surfaces aft of the nose, and tails consisting of eight low-aspect-ratio triangular or rectangular fins. Normal-force, axial-force, and pitching-moment coefficients were obtained for several control deflections for Mach numbers 1.2 and 1.9.
Date: September 17, 1958
Creator: Lazzeroni, Frank A.
Partner: UNT Libraries Government Documents Department
open access

Aerodynamics of Oscillating Control Surfaces at Transonic Speeds

Description: Memorandum presenting a discussion of oscillating flap-type and all-movable controls with particular emphasis on the aerodynamic forces and moments at transonic speeds. Hinge-moment results from recent wind-tunnel and rocket-powered-model tests are summarized for trailing-edge flap-type controls to illustrate the effects of control hinge-line position and profile shape on one-degree-of-freedom flutter of this type of control.
Date: June 17, 1957
Creator: Thompson, Robert F. & Clevenson, Sherman A.
Partner: UNT Libraries Government Documents Department
open access

Heat-Transfer Measurements on a Concave Hemispherical Nose Shape With Unsteady-Flow Effects at Mach Numbers of 1.98 and 4.95

Description: Memorandum presenting heat-transfer rates and pressure fluctuations at Mach numbers of 1.98 and 4.95 measured at the stagnation point of a concave hemisphere for a range of Reynolds numbers based on free-stream conditions and model diameter. Results regarding heat-transfer characteristics, heat-transfer data, and schileren photographs and stagnation point pressure measurements are provided.
Date: July 17, 1958
Creator: Cooper, Morton; Beckwith, Ivan E.; Jones, Jim J. & Gallagher, James J.
Partner: UNT Libraries Government Documents Department
open access

A Method for Predicting the Stability in Roll of Automatically Controlled Aircraft Based on the Experimental Determination of the Characteristics of an Automatic Pilot

Description: Report presenting a method for predicting the stability of automatically controlled aircraft by comparing the calculated frequency-response curves for the aircraft and experimentally determined frequency-response curves for the automatic pilot. The method is applicable only to stabilization in roll. It can be used to establish the specifications of performance required for the automatic control device for pilotless aircraft designed as missiles.
Date: January 17, 1947
Creator: Jones, Robert T. & Sternfield, Leonard
Partner: UNT Libraries Government Documents Department
open access

Investigation of shock diffusers at Mach number 1.85 2: projecting double-shock cones

Description: Report presenting an investigation in the 18- by 18-inch supersonic tunnel to determine the total-pressure recovery obtainable at Mach number 1.85 with a shock diffuser with projective cones designed to produce two oblique shocks ahead of the diffuser inlet. The variation of total-pressure recovery with tip projection was investigated for four cones with different included angles. A maximum total-pressure recovery of 94.5 percent was attained with the best configuration at an angle of 0 degrees. more
Date: June 17, 1947
Creator: Moeckel, W. E.; Connors, J. F. & Schroeder, A. H.
Partner: UNT Libraries Government Documents Department
open access

Analytical Investigation of Turbines With Adjustable Stator Blades and Effect of These Turbines on Jet-Engine Performance

Description: From Introduction: "A comparison is also made of the actual performance of two contemporary jet engines with estimated performance, assuming the engines were equipped with adjustable-angle stators and adjustable exhaust nozzles. Charts are presented that aid in estimating the performance of adjustable-stator turbines."
Date: July 17, 1950
Creator: Silvern, David H. & Slivka, William R.
Partner: UNT Libraries Government Documents Department
open access

Low-Speed Aerodynamic Characteristics of a Series of Swept Wings Having NACA 65A006 Airfoil Sections (Revised)

Description: Report presenting an investigation to determine the effect of sweep, taper ratio, and aspect ratio on the aerodynamic characteristics of nine semispan wings with NACA 65A006 airfoil sections with and without split flaps. Lift, drag, pitching-moment, and wing-root bending-moment characteristics are presented for a range of Reynolds numbers.
Date: October 17, 1950
Creator: Cahill, Jones F. & Gottlieb, Stanley M.
Partner: UNT Libraries Government Documents Department
open access

The effect of tip tanks on the rolling characteristics at high subsonic Mach numbers of a wing having an aspect ratio of 3 with quarter-chord line swept back 35 degrees

Description: Report presenting an investigation of the effect of wing-tip mounted tanks on the rolling characteristics of a wing, aspect ratio 3 with the quarter-chord line swept back 35 degrees, through a range of Mach numbers and angles of attack using the free-roll method.
Date: January 17, 1950
Creator: Kuhn, Richard E. & Myers, Boyd C., II
Partner: UNT Libraries Government Documents Department
open access

Preliminary Investigation of a Submerged Air Scoop Utilizing Boundary-Layer Suction to Obtain Increased Pressure Recovery

Description: Report presenting an investigation of a submerged air scoop consisting of a conventional scoop located in a dimple in the fuselage surface at low speeds. Results regarding a study of the basic inlet without suction, a comparison of arrangements using boundary-layer control, the performances of the most desirable configurations with a certain boundary layer, and variation of boundary-layer thickness are provided.
Date: March 17, 1950
Creator: Nichols, Mark R. & Pierpont, P. Kenneth
Partner: UNT Libraries Government Documents Department
Back to Top of Screen