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Flight determination of the buffeting characteristics of the Bell X-5 research airplane at 58.7 degrees sweepback

Description: Report presenting flight measurements of the buffeting characteristics of the Bell X-5 airplane at 58.7 degrees of sweepback at a range of Mach numbers and altitudes. Information about tail buffeting and wing buffeting at several angles of attack is provided. The pilot considered the buffeting to be unobjectionable throughout the entire test region.
Date: May 24, 1954
Creator: Briggs, Donald W.
Partner: UNT Libraries Government Documents Department

Flight tests of a man standing on a platform supported by a teetering rotor

Description: Report presenting a series of flight tests to determine the flying qualities of a man standing on a platform supported by a teetering rotor. The machine was tested with a free-teetering rotor, a spring-restrained rotor, and a rotor and foot platform isolated from the framework by rubber connections. Results of the different configurations during indoor and outdoor flights are presented.
Date: March 24, 1954
Creator: Hill, Paul R. & Kennedy, T. L.
Partner: UNT Libraries Government Documents Department

Free-flight-tunnel investigation of the low-speed stability and control characteristics of a model having a fuselage of relatively flat cross section

Description: Report presenting an experimental investigation in the free-flight tunnel to determine the low-speed stability and control characteristics of a model with a fuselage of relatively flat cross section. The model was found to exhibit an erratic behavior in pitch and yaw, which appeared to be due to random trim changes associated with the flow from the forward portion of the flat fuselage. Results regarding the longitudinal stability and control characteristics and lateral stability and control characteristics are provided.
Date: February 24, 1953
Creator: Paulson, John W. & Johnson, Joseph L., Jr.
Partner: UNT Libraries Government Documents Department

Investigation of a high-performance axial-flow compressor transonic inlet rotor designed for 37.5 pounds per second per square foot of frontal area 1: aerodynamic design and overall performance

Description: Report presenting an investigation of the design and tests of a transonic inlet rotor with emphasis placed on increasing the design specific weight flow while maintaining reasonably high pressure ratio and efficiency. Information regarding peak efficiency and how to best achieve it through design is provided.
Date: March 24, 1955
Creator: Savage, Melvyn & Felix, A. Richard
Partner: UNT Libraries Government Documents Department

Investigation of a canard missile configuration (NACA RM-4) in the Langley 9-inch supersonic tunnel at Mach numbers of 1.62 and 1.93

Description: Report presenting an investigation in the supersonic tunnel using a canard missile configuration designated as NACA RM-4. Measurements of lift, drag, and pitching moment were made over a range of Mach numbers and angles of attack. The data is presented without analysis.
Date: June 24, 1954
Creator: Grigsby, Carl E.
Partner: UNT Libraries Government Documents Department

Investigation of Supersonic-Compressor Rotors Designed with External Compression

Description: 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.
Partner: UNT Libraries Government Documents Department

Investigation of performance of Bumblebee 18-inch ram jet with a can-type flame holder

Description: Report presenting the results of an investigation in the altitude wind tunnel to determine the performance of a Bumblebee 18-inch ram jet equipped with a can-type flame holder. Results regarding the ramjet combustion performance and ramjet overall performance are provided.
Date: August 24, 1948
Creator: Sterbentz, W. H. & Nussdorfer, T. J.
Partner: UNT Libraries Government Documents Department

Results of initial wind-tunnel flutter experiments at low speed with a towed airplane model having a 40 degree sweptback wing of aspect ratio 3.62 equipped with pylon-mounted stores

Description: Report presenting wind-tunnel flutter testing at a range of Mach numbers conducted on a swept-wing towed airplane model equipped with an autopilot system. Results regarding the towed model tests, fixed-root tests, and a comparison between the calculated and experimental flutter characteristics are provided.
Date: March 24, 1955
Creator: Martina, Albert P. & Young, George E.
Partner: UNT Libraries Government Documents Department

Evaluation of hydrogen fuel in a full-scale afterburner

Description: Report presenting a performance investigation using hydrogen fuel in a full-scale afterburner with particular study of fuel-injector configurations and afterburner length. A total of seven fuel-injector configurations, some concentric ring and some radial bar, were investigated at a specified burner inlet velocity over a range of burner-inlet total pressures.
Date: September 24, 1957
Creator: Groesbeck, Donald E.; Prince, William R. & Ciepluch, Carl C.
Partner: UNT Libraries Government Documents Department

An experimental investigation of boundary interference on force and moment characteristics of lifting models in the Langley 16- and 8-foot transonic tunnels

Description: Report presenting testing of a wing-fuselage force model configuration and the fuselage alone at angles of attack up to 32 degrees in the 16-foot transonic tunnel. Results regarding the force and moment characteristics, base pressures, and shadowgraph pictures are provided.
Date: February 24, 1953
Creator: Whitcomb, Charles F. & Osborne, Robert S.
Partner: UNT Libraries Government Documents Department

Performance of external-compression bump inlet at Mach numbers of 1.5 and 2.0

Description: Report presenting an experimental investigation of a scale model of the forebody of a proposed supersonic fighter to determine the internal performance and configuration drag of various twin-side inlets. External-compression ramp and bump inlets with various types and combinations of boundary-layer bleed were tested. Results regarding performance charts and flow characteristics are provided.
Date: April 24, 1957
Creator: Simon, Paul C.; Brown, Dennis W. & Huff, Ronald G.
Partner: UNT Libraries Government Documents Department

Preliminary study of airplane configurations having tail surfaces outboard of the wing tips

Description: Report presenting some of the concepts and applications underlying the basic arrangement of airplane configurations with tail surfaces outboard of the wing tips. The arrangement was created to be consistent with good supersonic performance characteristics and to avoid some of the stability and trim-drag problems seen with other supersonic configurations. Results regarding stability and control characteristics, lift and drag characteristics, and an analytical study of effects of some design variables are provided.
Date: March 24, 1958
Creator: Sleeman, William C., Jr.
Partner: UNT Libraries Government Documents Department

Low-amplitude damping-in-pitch characteristics of tailless delta-wing-body combinations at Mach numbers from 0.80 to 1.35 as obtained with rocket-powered models

Description: Report of an investigation using three rocket-propelled delta-wing-body combinations for a range of Mach numbers to determine the damping-in-pitch characteristics. All models were statically stable but dynamically unstable at transonic speeds. Information about trim, lift, and drag is also provided.
Date: June 24, 1954
Creator: D'Aiutolo, Charles T.
Partner: UNT Libraries Government Documents Department

Longitudinal stability and drag characteristics of a fin stabilized body of revolution with a fineness ratio of 12 as measured by the free-fall method

Description: Report presenting measurements of longitudinal stability and drag characteristics of a fin-stabilized body of revolution with a fineness ratio 12 at low angles of attack using the free-fall method. Information about the data obtained from testing as well as the experimental coefficients related to body normal-force, total longitudinal-force, and body moment with Mach number is provided.
Date: June 24, 1954
Creator: Kurbjun, Max C.
Partner: UNT Libraries Government Documents Department

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

Description: 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.
Partner: UNT Libraries Government Documents Department

A low-speed investigation of the aerodynamic, control, and hinge-moment characteristics of two types of controls and balancing tabs on a large-scale thin delta-wing-fuselage model

Description: Report presenting a low-speed investigation of the aerodynamic and control characteristics of a 3-percent-thick, 60 degree delta-wing-fuselage configuration in the full-scale tunnel to obtain data at large scale on control configurations of general interest and to determine whether significant Reynolds number effects existed for a very thin wing subject to leading-edge vortex-type flow. Aerodynamic forces, moments, and hinge moments were obtained for several types of controls and flap deflections.
Date: March 24, 1954
Creator: Fink, Marvin P. & Cocke, Bennie W.
Partner: UNT Libraries Government Documents Department

Feasibility of nose-cone cooling by the upstream ejection of solid coolants at the stagnation point

Description: Report presenting an investigation in a chemical jet at a stagnation temperature of 4,000 degrees Fahrenheit at a Mach number of 2.8 to determine the feasibility of cooling models by the ejection of a solid coolant at the stagnation point. A series of conical models were tested with glass, Lucite, nylon, Teflon, and Texolite rods as coolants. Results regarding the cooling properties of each of the materials are provided, and all materials performed adequately with the exception of Teflon.
Date: March 24, 1958
Creator: Kinard, William H.
Partner: UNT Libraries Government Documents Department

Heat transfer to 0 degree and 75 degree swept blunt leading edges in free flight at Mach numbers from 1.90 to 3.07

Description: Report presenting an investigation of a rocket-powered model to study the heat transfer to wing leading edges in the vicinity of their juncture with a cylindrical body. Information about heat-transfer measurements, average heat transfer on cylindrical portions of leading edges, and local heat transfer is provided.
Date: March 24, 1958
Creator: O'Neal, Robert L. & Bond, Aleck C.
Partner: UNT Libraries Government Documents Department

Determination and use of the local recovery factor for calculating the effectiveness gas temperature for turbine blades

Description: In an in experimental investigation of local recovery factors for a blade having a pressure distribution similar to that of a typical reaction-type turbine blade, it a was found that the recovery factors were essentially independent of Mach number, Reynolds number, pressure gradient, and position on the blade surface except for regions where the boundary layer was probably in the transition range from laminar to turbulent. The recommended value of local subsonic recovery factor for use in calculating the effective gas temperature for gas turbine blades was 0.89.
Date: September 24, 1951
Creator: Esgar, Jack B. & Lea, Alfred L.
Partner: UNT Libraries Government Documents Department

Comparison of effects of ailerons and combinations of spoiler-slot-deflector arrangements on spin recovery of sweptback-wing model having mass distributed along the fuselage

Description: Report presenting an investigation in the free-spinning tunnel to determine the effect of lateral-control systems using various combinations of spoilers, slots, and deflectors as compared with ailerons on the spin-recovery characteristics of a model of a 35 degree swept-wing fighter loaded heavily along the fuselage. Testing indicated that the ailerons were favorable for recovery when they were deflected full with the spin. Results regarding the effect of ailerons and two spoiler-slot-deflector configurations are provided.
Date: November 24, 1954
Creator: Healy, Frederick M. & Klinar, Walter J.
Partner: UNT Libraries Government Documents Department

Behavior of some materials and shapes in supersonic free jets at stagnation temperatures up to 4,210 F, and descriptions of the jets

Description: Report presenting testing of a number of materials and shapes in two supersonic free jets at stagnation temperatures of up to 4,210 degrees Fahrenheit. Some testing was conducted in a supersonic chemical jet and some was conducted in a ceramic-heated air jet. Materials tested included aluminum alloy, copper, Inconel, magnesium, mild steel, molybdenum, stainless steel, titanium, alumina, zirconia, graphite, bakelite, and nylon.
Date: February 24, 1958
Creator: Fields, E. M.; Hopko, Russel N.; Swain, Robert L. & Trout, Otto F., Jr.
Partner: UNT Libraries Government Documents Department

Analysis of fluorine addition to the vanguard first stage

Description: From Introduction: "This report presents data pertinent to the problem of boosting rocket performance by adding up to 30 percent liquid fluorine to the liquid oxygen of an existing oxygen-hydrocarbon rocket engine."
Date: January 24, 1957
Creator: Tomazic, William A.; Schmidt, Harold W. & Tischler, Adelbert O.
Partner: UNT Libraries Government Documents Department

Effects of leading-edge slat and trailing-edge split flap on the aerodynamic characteristics of a wing-fuselage combination having a nearly triangular wing of aspect ratio 2.9 at Mach numbers from 0.60 to 0.92

Description: Report presenting an investigation to determine the effectiveness of a leading-edge slat and a trailing-edge split flap in improving the high subsonic speed aerodynamic characteristics of a model of a wing-fuselage combination with a nearly triangular wing. Results regarding the effects of Reynolds number, effects of slats, and effects of flaps are provided.
Date: January 24, 1958
Creator: Demele, Fred A.
Partner: UNT Libraries Government Documents Department

Experimental determination of aerodynamic forces normal to the chord due to rotating stall acting on compressor blading

Description: Report presenting an investigation conducted on an NACA axial-flow single-stage compressor with a 14-inch diameter and a 0.9 hub-tip ratio to determine the magnitude of the blade force variation due to the flow fluctuations caused by rotating stall. Results regarding steady-state blade forces, shapes of steady-state force curves, time variation in weight flow, oscillograms of strain-gage output, and effect of damping are provided.
Date: August 24, 1954
Creator: Johnson, Donald F. & Costilow, Eleanor L.
Partner: UNT Libraries Government Documents Department