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A Preliminary Investigation of the Performance of a Short Length Turbojet Combustor Using Vaporized Hydrocarbon Fuels

Description: "Two short turbojet combustors designed for use with vaporized hydrocarbon fuels were tested in a one-quarter annular duct. The experimental combustors consisted of many small "swirl-can" combustor elements manifolded together. This design approach allowed the secondary mixing zone to be considerably reduced over that of conventional combustors" (p. 1).
Date: January 7, 1958
Creator: Jones, R. E. & Pawlik, E. V.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Some Effects of Reynolds Number on the Stability of a Series of Flared-Body and Blunted-Cone Models at Mach Numbers From 1.62 to 6.86

Description: Report discussing an investigation of the stability of a series of flared-body and blunted-cone models at a range of Mach numbers. Increasing the flare length was found to increase static stability and the damping in pitch. The Reynolds number was found to have a large effect on static stability at lower Mach numbers, but little effect on the higher end of the range covered in testing.
Date: January 7, 1958
Creator: Kehlet, Alan B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Performance of Multiple Jet-Exit Installations

Description: Memorandum presenting the results of recent exploratory investigations of the performance of clustered jet-exit installations at Mach numbers from 0.60 to 3.05. Data presented in this report were obtained with tunnel-wall-mounted models with cold-air-jet exhaust. Results regarding base pressures, effect of boattailing, effect of afterbody-nozzle geometry, and terminal fairings are provided.
Date: July 7, 1958
Creator: Swihart, John M. & Nelson, William J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Static Stability and Control of Hypersonic Gliders

Description: Memorandum presenting a study of the static stability and control problems associated with several hypersonic boost gliders. Generally, it is possible to obtain the desired trim features. Results regarding the high-lift-drag-ratio type of gliders and low-lift-drag-ratio type of gliders are provided.
Date: July 7, 1958
Creator: Rainey, Robert W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

An Investigation of the Performance of a Semielliptical Scoop Inlet at Mach Numbers of 1.60, 1.76, and 2.02

Description: Memorandum presenting an investigation of the performance of a semielliptical scoop inlet with a two-dimensional flow field at the design Mach number of 2.0. The investigation included a study of the effects of inlet-leading-edge shape and boundary-layer bleed on the pressure recovery and total-pressure distribution. Results regarding performance of inlets without boundary-layer bleed, effect of diverter boundary-layer bleed, effect of leading-edge sweep angle, effect of compression-surface ble… more
Date: January 7, 1958
Creator: Hayes, Clyde & Mackley, Ernest A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Transonic Lateral and Longitudinal Aerodynamic Characteristics of a Lateral-Control System Employing Rotatable Airfoils Mounted Vertically at the Wing Tips of an Unswept Wing-Fuselage-Tail Combination

Description: Report presenting the aerodynamic characteristics of a new type of lateral control through a range of Mach numbers. The control consisted of airfoils mounted vertically at the tips of the wing and could be rotated to induce rolling moments or lift on the wing surface. Results regarding lateral-control characteristics and lift-control characteristics are provided.
Date: January 7, 1958
Creator: Axelson, John A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Performance of multiple jet-exit installations

Description: Report presenting an investigation of the performance of clustered jet-exit installations at Mach numbers from 0.60 to 3.05. The data were obtained with tunnel-wall-mounted models with cold-air-jet exhaust. Results indicated that large base-pressure drag coefficients may be encountered in the transonic and low supersonic speed range and that the best configuration in the test was boattailed between the nacelles, had a cylindrical nacelle afterbody, and a divergent nozzle with a design pressure … more
Date: July 7, 1958
Creator: Swihart, John M. & Nelson, William J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Some Effects of Reynolds Number on the Stability of a Series of Flared-Body and Blunted-Cone Models at Mach Numbers Form 1.62 to 6.86

Description: Report presenting an investigation of some effects of Reynolds number on the stability of a series of flared-body and blunted-cone models at a range of Mach numbers in three wind tunnels. The Reynolds number had a pronounced effect on the static stability of the flared-body models at the lower Mach numbers. Results regarding the static stability and damping in pitch are provided.
Date: January 7, 1958
Creator: Kehlet, Alan B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Longitudinal stability and control characteristics at Mach numbers of 1.41 and 2.01 of a 67 degree swept-wing airplane configuration with canard control surfaces

Description: Report presenting an investigation in the 4- by 4-foot supersonic pressure tunnel at Mach numbers of 1.41 and 2.01 to determine the stability and control characteristics of a canard-controlled airplane configuration with potentially high values of lift-drag ratio. The configurations investigated included a plane and a twisted wing with approximately 67 degrees of sweep and an aspect ratio of 2.91 and three trapezoidal canard surfaces with ratios of exposed area to wing area of 0.032, 0.076, and… more
Date: July 7, 1958
Creator: Spearman, M. Leroy & Robinson, Ross B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Effects of canards on airplane performance and stability

Description: Report presenting an investigation on canard airplane configurations in preference to a trailing-edge flap or tail control. Wide ranges in control plan form, size, and position and in wing plan form were found. Interference effects between the canard and other configuration components were not serious, and those that might be can be reduced by rearrangement of the vertical tail.
Date: July 7, 1958
Creator: Hall, Charles F. & Boyd, John W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Qualitative Measurements of the Effective Heats of Ablation of Several Materials in Supersonic Air Jets at Stagnation Temperatures Up to 11,000 Degrees F

Description: Report presenting testing on the effective heats of ablation of a number of materials using supersonic arc jets at stagnation temperatures ranging from 2000 degrees F to 11,000 degrees F. Materials examined included Teflon, nylon, Lucite, polystyrene, ammonium chloride, sodium carbonate, several phenolic resins, and melamine-fiber glass laminate.
Date: July 7, 1958
Creator: Rashis, Bernard; Witte, William G. & Hopko, Russell N.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Experimental Investigation of Distortion Removal Characteristics of Several Free-Wheeling Fans

Description: Memorandum presenting an investigation of the distortion removal performance and associated total-pressure-loss characteristics of several freely rotating fans, three single-stage and two double-stage freely rotating fans over a range of radial and circumferential distortions of from 0 to 20 percent at inlet annulus Mach numbers from 0.30 to about 0.60. Results regarding individual fan performance, comparison of fan distortion removal characteristics, and fan total-pressure loss and operating s… more
Date: January 7, 1958
Creator: Valentine, Harold H. & Beale, William T.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Some Effects of Rapid Inlet Pressure Oscillation on the Operation of a Turbojet Engine

Description: "A program was conducted in an altitude facility at the NACA Lewis laboratory to investigate the effects of rapid inlet pressure oscillations on the operation of a current turbo jet engine. These pressure oscillations were approximately sinusoidal in form and were generated to cover a frequency range of 2 to 75 cycles per second and an amplitude range of 10 to 70 percent of the free-stream total pressure. As the oscillation progressed through the compressor, the amplitude was attenuated conside… more
Date: January 7, 1958
Creator: Russey, Robert E. & Lubick, Robert J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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