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20,000 KW Nuclear Power Plant Study for United States Atomic Energy Commission

Description: Introduction: In September of 156, Gilbert Associates, Inc., entered into a contract with the United States of America, acting through the United States Atomic Energy Commission, for the study and preliminary design of a nuclear power plant being considered for integration into a central station power system at an overseas site.
Date: July 7, 1957
Creator: Gilbert Associates, Inc.
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

Analysis of V-g data obtained from several naval airplanes

Description: From Introduction: "V-g records supplied the NACA by the Bureau of Aeronautics in 1948 and 1949 have provided additional material. These records are analyzed statistically in this report to the frequency of large values of acceleration and airspeed, and results are compared with the design requirements."
Date: July 7, 1950
Creator: Thornton, James O.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Pressure-distribution and ram-recovery characteristics of NACA submerged inlets at high subsonic speeds

Description: Report presenting ram-recovery and mass-flow ratios for submerged inlets at four positions on the fuselage of a model of a hypothetical fighter airplane. Results related to the inlet location and effect of angle of attack are also provided.
Date: July 7, 1950
Creator: Frank, Joseph L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Low-Speed Pressure-Distribution Measurements at Reynolds Number of 3.5 X 10(Exp 6) on a Wing With Leading-Edge Sweepback Decreasing From 45 Degrees at the Root to 20 Degrees at the Tip

Description: "Results are presented of an investigation to determine the pressure distributions on a wing with leading-edge sweepback decreasing from 45 degrees at the root to 20 degrees at the tip, an aspect ratio of 4.12, taper ratio of 0.36, and NACA 64A009 airfoil section. Tests were conducted at a Reynolds number of 3.5 x 10(exp 6) and a Mach number of 0.07 on the wing with and without 0.20 chord and 0.65 span split flaps deflected 60 degrees. These pressure distributions are analysed herein to determi… more
Date: July 7, 1950
Creator: Barnett, U. Reed, Jr. & Lange, Roy H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Calibration of the Slotted Test Section of the Langley 8-Foot Transonic Tunnel and Preliminary Experimental Investigation of Boundary-Reflected Disturbances

Description: Report presenting an attempt to determine the reliability and calibration of the Langley transonic tunnel in the open slotted test section. Results regarding test-section calibration, including flow uniformity, calibration, and angularity, model testing and boundary interference, and reduction of interference are provided.
Date: July 7, 1952
Creator: Ritchie, Virgil S. & Pearson, Albin O.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

A Preliminary Investigation of the Power Requirements of Slotted Test Sections

Description: Report presenting an investigation of the power requirements for slotted tunnels and methods of reducing these requirements. All pressure losses reported occurred in the region between the upstream end of the entrance ball and the entrance to the diffuser and in handling air taken in through the slotted wall. Results regarding auxiliary pumping and ejector pumping are provided.
Date: July 7, 1953
Creator: Dennard, John S.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Comparison of normal load factors experienced with jet fighter airplanes during combat operations with those of flight tests conducted by the NACA during operational training

Description: Report presenting a comparison of normal load factors measured during combat operations with those measured during an NACA flight program conducted with fully instrumented service airplanes in operational training. Results indicated that for an equal number of maneuvers, normal load factors obtained from the NACA program are greater than those obtained during combat when based on the service-limit load factor.
Date: July 7, 1954
Creator: Hamer, Harold A.; Huss, Carl R. & Mayer, John P.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

The Hydrodynamic Planing Lift of Four Surfaces as Measured in a 200-FPS Free Jet

Description: Report presenting hydrodynamic planing lifts obtained in a free jet at speeds from 80 to 200 fps for four planing surfaces. The surfaces tested included a flat plate, a longitudinally curved model, a cylinder, and a hydro-ski with a complex-shaped bottom. Lift data was analyzed to show the effect of speed, planing-surface configuration, trim, and wetted-length-beam ratio at high speeds.
Date: July 7, 1954
Creator: McGehee, John R.; Weinflash, Bernard & Pelz, Charles A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Experimental performance of fluorine-oxygen with JP4 fuel in a rocket engine

Description: Report presenting the performance increase resulting from the addition of fluorine to the oxygen-JP4 rocket propellant combination evaluated experimentally in a 1000-pound-thrust engine with 0, 30, and 70 percent of fluorine by weight in the oxidant. Maximum specific impulse values obtained were 259, 278, and 287 pound-seconds per pound, respectively, at a combustion pressure of 600 pounds per square inch absolute.
Date: July 7, 1955
Creator: Douglass, Howard W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Acceleration Characteristics of a Turbojet Engine With Variable-Position Inlet Guide Vanes

Description: Report presenting a study of the acceleration characteristics of a turbojet engine equipped with variable-position inlet guide vanes in the altitude test chamber. Maximum acceleration values for 3 engines of the same model were also obtained during testing and were found to differ as much as 50 percent. Results regarding the effect of fuel step size and inlet guide vane on acceleration, effect of flight condition, reproducibility of engine acceleration, compressor pressure ratio in relation to … more
Date: July 7, 1955
Creator: Dobson, W. F. & Wallner, Lewis E.
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

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

Design and test of mixed-flow impellers 5: design procedure and performance results for two vaned diffusers tested with impeller model MFI-1B

Description: Report presenting the design procedure and experimental test results for a range of impeller speeds for two vaned diffusers of 24 and 40 vanes. Both sets of vanes were designed to give approximately the same prescribed velocity distribution on the vane surfaces and were tested with the same impeller. Results regarding overall performance and the total-pressure-loss coefficient for both vanes are provided.
Date: July 7, 1955
Creator: Hamrick, Joseph T. & Osborn, Walter M.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Heat Transfer Testing

Description: Several tests are being performed and others being planned to investigate the role of heat transfer in corrosion processes. These tests are measuring both corrosion rates of metals (Zr-2 and X-8001 aluminum) under heat transfer, and the temperature rise associated with the buildup of the corrosion product. A brief description of these tests is given in this report.
Date: July 7, 1959
Creator: Doman, D. R.; Hokenson, J.F. & Lobsinger, R. J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

The Shape of a Shock Wave Derived from a Spherical Shock Wave Incident on a Concave Wedge

Description: When a one-half ounce spherical charge of high explosive is detonated over a flat plane bounded by a 5 degree incline, the type of phenomenon encountered depends on the distance from ground zero to a beginning of the incline. If this distance is 48" the wave assumes a smooth contour on the plane. Detailed investigation of the shock velocity above the plane reveals that there is a pressure gradient along the shock front for a considerable region which replaces the usual triple point.
Date: July 7, 1954
Creator: Todd, Jay, Jr. & Schellenbaum, Ralph L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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