Technical Report Archive & Image Library (TRAIL) - 34 Matching Results

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Experimental Determination at Subsonic Speeds of the Oscillatory and Static Lateral Stability Derivatives of a Series of Delta Wings With Leading-Edge Sweep From 30 to 86.5 Degrees

Description: Memorandum presenting a determination of the static lateral stability of six delta wings at subsonic speeds. In addition, two of the wings with 82.5 degree and 75 degree sweep of the leading edge were oscillated in yaw about the 50-percent point of the root chord in order to determine the effects of frequency and amplitude on the combination lateral stability derivatives resulting from the motion. Results regarding the static characteristics and oscillatory characteristics are provided.
Date: April 12, 1957
Creator: Letko, William
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Hinge-moment characteristics for a series of controls and balancing devices on a 60 degree delta wing at Mach numbers of 1.61 and 2.01

Description: Report presenting an investigation to determine the control hinge-moment characteristics at two Mach numbers for a series of 18 controls, including the effects of various tabs and fences, on a 60 degree delta wing. Testing covered a range of angles of attack, control deflection, and tab deflection. Results regarding the basic variation of hinge-moment coefficients, tip controls, and trailing-edge controls are provided.
Date: April 12, 1957
Creator: Lord, Douglas R. & Czarnecki, K. R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Investigation of a High-Performance Axial-Flow Compressor Transonic Inlet Rotor Designed for 37.5 Pounds Per Second Per Square Foot of Frontal Area: Detailed Blade-Element Performance

Description: Report presenting detailed blade-element-performance plots for a high-flow transonic inlet rotor. Information provided includes the effects of Mach number, blade loading, and angle of attack on element performance is provided.
Date: April 12, 1957
Creator: Felix, A. Richard & Savage, Melvyn
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Jet effects on the drag of conical afterbodies for Mach numbers of 0.6 to 1.28

Description: Report presenting an investigation at Mach numbers from 0.6 to 1.28 to determine the drag characteristics of a series of conical afterbodies with a cold sonic jet issuing from the base. Models investigated had boattail angles from 3 to 45 degrees, ratios of jet diameter to base diameter of 0.65 and 0.75, and values of the ratios of the base diameter to maximum diameter of 0.55, 0.70, and 0.85. Results regarding afterbody pressure distributions and afterbody drag are provided.
Date: April 12, 1957
Creator: Cubbage, James M., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

A Review of NACA Research Through 1954 on Boron Compounds as Fuels for Jet Aircraft (Project Zip)

Description: Report discussing a project to determine a high-energy fuel suitable for turbojet-powered aircraft. Components of the project include thermal and combustion properties, experiments with combustors using boron compounds, evaluation of boron fuels in full-scale turbojets with and without afterburners, and boron fuel use in ramjet flights. The most promising fuel found in the report is pentaborane.
Date: April 12, 1957
Creator: Olson, Walter T.; Breitwieser, Roland & Gibbons, Louis C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

A review of NACA research through 1954 on boron compounds as fuels for jet aircraft (Project Zip)

Description: Report presenting NACA work through 1954 on a high-energy fuel suitable for turbojet-powered aircraft. The work includes thermal and combustion properties, experiments with combustors designed to use boron compounds, evaluation of boron fuels in full-scale turbojets with and without afterburners, and ramjet flights on boron fuels. Satisfactory combustion of pentabornae and high-concentration blends of pentaborane has been demonstrated in a turbojet, an afterburner, and a ram jet.
Date: April 12, 1957
Creator: Olson, Walter T.; Breitwieser, Roland & Gibbons, Louis C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Analytical Study of the Comparative Pitch-Up Behavior of Several Airplanes and Correlation With Pilot Opinion

Description: From Introduction: "An extension of the work presented in reference 2, the method was applied to six swept-wing airplanes for which the pilot opinion was well documented. The analytical results obtained are used herein to illustrate how wind-tunnel data may be used to predict the pitching motions and the comparative pitch-up behavior of new airplane designs or to assess the effects of modifications on existing airplanes."
Date: June 12, 1957
Creator: Sadoff, Melvin; Stewart, John D. & Cooper, George E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Cascade investigation of cooling characteristics of a cast-finned air-cooled turbine blade for use in a turboprop engine

Description: Report presenting an experimental investigation of the cooling characteristics of a small air-cooled turbine blade for use in a turboprop engine in a static cascade facility. Three test blades of the same size and chord were tested at several different combustion-gas temperatures. Results regarding the gas-flow conditions in cascade test section, correlation of temperature data and application of correlated data to typical engine are provided.
Date: June 12, 1957
Creator: Stepka, Francis S.; Richards, Hadley T. & Hickel, Robert O.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Cascade Investigation of Cooling Characteristics of a Castfinned Air-Cooled Turbine Blade for Use in a Turboprop Engine

Description: Memorandum presenting an experimental investigation of the cooling characteristics of a small air-cooled turbine blade for use in a turboprop engine in a static cascade facility. Three test blades were studiued at three combustion-gas temperatures. Results regarding gas-flow conditions in cascade test section, correlation of temperature data, and application of correlated data to the typical engine are provided.
Date: June 12, 1957
Creator: Stepka, Francis S.; Richards, Hadley T. & Hickel, Robert O.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Effects of Some Configuration Changes on Afterburner Combustion Performance

Description: Report presenting an experimental investigation in a simulated afterburner test rig to determine the effects of some configuration variations on afterburner combustion performance. Results regarding the reduced-diameter flameholder, inclined radial-gutter flameholder, tapered-shell afterburner, and turbulence generators are provided.
Date: June 12, 1957
Creator: Nakanishi, Shigeo & King, Charles R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Effects of Some Configuration Changes on Afterburner Combustion Performance

Description: Memorandum presenting an experimental investigation conducted in a 25.75-inch-diameter simulated-afterburner test rig to determine the effects of some configuration variations on afterburner combustion performance. The variations included a V-gutter flameholder with the maximum gutter-ring diameter reduced from 20 to 17 inches, but with equal projected blockage; an inclined radial-gutter flameholder; a tapered-shell afterburner; and a V-gutter flameholder with turbulence generators added.
Date: June 12, 1957
Creator: Nakanishi, Shigeo & King, Charles R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Theoretical analysis of one-stage windmills for reducing flow distortion

Description: Report presenting an analysis of two windmills for reducing flow distortion. Results regarding the windmill design, flow conditions, velocity distortions, total-pressure distortions, total-temperature distortions, and design value of the ratio of axial velocity to blade tip speed are provided.
Date: June 12, 1957
Creator: English, Robert E. & Yohner, Peggy L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Experimental investigation of effects of moderate sideslip on the flow fields near a 45 degree swept-wing-fuselage combination at low speed

Description: The flow fields near a 45 degree swept-wing-fuselage combination at moderate angles of sideslip (plus-or-minus 8 degrees), as determined experimentally at low speed, are presented as variations with chordwise distance for various spanwise and vertical locations and angles of attack. The results indicated that for positions close to the fuselage (on and near the plane of symmetry) changes in the angle of sideslip caused large changes in the flow-field characteristics and particularly in the loca… more
Date: July 12, 1957
Creator: Alford, William J., Jr. & King, Thomas J., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

The Frequency Content of the Control Input and Airplane Response Obtained During Service Operations of Fighter Airplanes

Description: "The frequency content of the control input and resulting airplane motions is presented as power spectral densities for one operational flight of the fighter airplane (Republic F-84G). The frequency content, which is described by the shape of the spectrum, may be useful in providing inputs for the design of power control systems. For normal load factors, the results presented for the operational flight considered are in general agreement with the results of more complete data on three fighter a… more
Date: July 12, 1957
Creator: Mayer, John P. & Hamer, Harold A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Local Heat Transfer to Blunt Noses at High Supersonic Speeds

Description: Memorandum presenting a brief summary of the recent theoretical and experimental work on local heat-transfer rates on blunt-nose bodies. Results regarding the calculation of local flow conditions, prediction of stagnation-point heating rates, and calculation of heating rates over entire nose are provided.
Date: July 12, 1957
Creator: Stoney, William E., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Some Factors Affecting the Static Longitudinal and Directional Stability Characteristics of Supersonic Aircraft Configurations

Description: Memorandum presenting a survey of the problems introduced by the increased longitudinal stability and reduced directional stability of aircraft operating in the low supersonic speed range. Information regarding longitudinal stability and directional stability are provided.
Date: July 12, 1957
Creator: Spearman, M. Leroy
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Some Factors Affecting the Static Longitudinal and Directional Stability Characteristics of Supersonic Aircraft Configurations

Description: Memorandum presenting a survey of the problems introduced by the increased longitudinal stability and the reduced directional stability of aircraft operating in the low supersonic speed range. The longitudinal stability increases markedly at supersonic speeds and results in high drags due to trimming and in limited control for maneuvering. The vertical-tail contribution is shown to be affected by many factors including the wing position, the fuselage shape, and the horizontal-tail position.
Date: July 12, 1957
Creator: Spearman, M. Leroy
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Effect of Nose Shape on Subsonic Aerodynamic Characteristics of a Body of Revolution Having a Fineness Ratio of 10.94

Description: Memorandum presenting a determination of the effect of nose shape on the normal-force, pitching-moment, and axial-force coefficients of a body of revolution with a fineness ratio of 10.94 as determined at subsonic speeds. Six nose shapes were investigated, which included flat-faced noses with various corner radii, a hemispherical nose, and two ogival noses.
Date: August 12, 1957
Creator: Polhamus, Edward C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Jet effects on base pressures of conical afterbodies at Mach 1.91 and 3.12

Description: Report presenting data showing the effect of a jet on base pressure for a series of conical afterbody-jet-nozzle combinations with a range of boattail angles and base-to-jet diameter ratios. Generally, base pressure increased for increasing values of boattail angle, nozzle angle, jet temperature, and jet total pressure and for decreasing values of base-to-jet diameter ratio, jet Mach number, and free-stream Mach number.
Date: August 12, 1957
Creator: Baughman, L. Eugene & Kochendorfer, Fred D.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Rocket-Model Investigation of Hinge-Moments on a Trailing-Edge Control on a 52.5 Degree Swept Wing Between Mach Numbers of 0.70 and 1.80

Description: Report presenting a free-flight investigation to determine the hinge-moment characteristics of a trailing-edge control on a swept and tapered wing using a rocket-powered model. Results regarding normal force and pitching moments are also provided.
Date: August 12, 1957
Creator: Martz, C. William
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Transonic Flutter Investigation of a 64 Degree Delta Wing Constructed With Spars Along Constant-Percent Chord Lines and Streamwise Ribs

Description: Report presenting an investigation of the transonic flutter characteristics of a 64 degree delta wing with spars along constant-percent chord lines and streamwise ribs. The data was compared to a previously published report on a similar wing with spanwise spars and orthogonal streamwise ribs.
Date: August 12, 1957
Creator: Jones, George W., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

The Use of Cones as Stabilizing and Control Surfaces at Hypersonic Speeds

Description: Report discussing the use of cones as stabilizing and control surfaces, which seems to be promising. Information about preliminary considerations, range of cone angles of probable interest, effects of Mach number on the shift in lift advantage from flat plate to cone, comparison of cone with more competitive lifting surfaces, and comparison in terms of producing the same restoring force for complete configuration is presented.
Date: August 12, 1957
Creator: Love, Eugene S.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Effect of Conical and Flat Sting-Mounted Windshields on the Zero-Lift Drag of a Flare-Stabilized Bluff Body at Mach Numbers From 0.6 to 1.15

Description: Report presenting zero-lift drag data for a flare-stabilized bluff body of fineness ratio 4.4 alone and with conical and flat windshields at a range of Mach and Reynolds numbers. The model with the flat windshield was found to have the lowest drag at Mach numbers up to 1.05, but there was little difference in drag among the models above 1.05.
Date: September 12, 1957
Creator: Blanchard, Willard S., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Effect of Frequency of Sideslipping Motion on the Lateral Stability Derivatives of a Typical Delta-Wing Airplane

Description: Report presenting an investigation to determine the effect of frequency of sideslipping motion on the lateral stability derivatives of a 60-degree delta-wing airplane configuration. Results regarding the steady-state tests, oscillation-in-sidestep tests, comparison of oscillation data for delta wings with a round edge versus a sharp edge, and effect of sideslip oscillatory derivatives are provided.
Date: September 12, 1957
Creator: Lichtenstein, Jacob H. & Williams, James L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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