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open access

Experimental Performance of a 5000-Pound-Thrust Rocket Chamber Using a 20-Percent-Fluorine - 80-Percent-Oxygen Mixture With RP-1

Description: Memorandum presenting an evaluation of the performance increase resulting from the addition of 20 percent fluorine to the oxygen-RP-1 propellant combination in a 5000-pound-thrust rocket engine at a chamber pressure of 650 pounds per square inch absolute. Runs were made with the engine water cooled and regeneratively cooled.
Date: April 24, 1957
Creator: Tomazic, William A.; Kutina, Franklin J., Jr. & Rothenberg, Edward A.
open access

Interference Effects of Fuselage-Stored Missiles on Inlet Duct Model of an Interceptor-Type Aircraft at Mach Numbers 1.5 to 1.9

Description: Memorandum presenting the effect of missile armament on the performance of an interceptor-type aircraft model at Mach numbers 1.5, 1.7, and 1.9 and at angles of attack up to 19 degrees. The aircraft model was characterized by triangular-shaped normal-shock inlets located at wing roots. Results regarding force measurements, effect of armament on inlet-duct performance, fuselage boundary-layer survey, and total-pressure contours at inlet throat and diffuser exit are provided.
Date: April 24, 1957
Creator: Piercy, Thomas G. & Davis, Owen H.
open access

Aerodynamic Loads on an External Store Adjacent to a 60 Degree Delta Wing at Mach Numbers From 0.75 to 1.96

Description: Report presenting an investigation to determine separately the aerodynamic characteristics of a Douglas Aircraft Company store and a semispan delta-wing-fuselage configuration in the presence of one another. The store was located at the 50-percent-semispan station with the store nose both ahead of and behind the wing leading edge for two longitudinal and three vertical positions.
Date: April 24, 1956
Creator: Hadaway, William M.
open access

Investigation at low speed of the effectiveness and hinge moments of a constant-chord elevator on a large-scale triangular wing with section modification

Description: Report presenting an investigation in the full-scale tunnel to determine the low-speed longitudinal, lateral, and hinge-moment control characteristics of a basic 60 degree delta wing of aspect ratio 2.31 with 10-percent-thick biconvex symmetrical airfoil sections. The wing was tested with a nose glove using NACA 65-010 section ordinates and a constant-chord plain semispan ailavator with two segments.
Date: April 24, 1951
Creator: Hawes, John G. & May, Ralph W., Jr.
open access

Flight measurements of the wing-dropping tendency of a straight-wing jet airplane at high subsonic Mach numbers

Description: From Summary: "Flight tests were conducted on a straight-wing fighter-type jet airplane to investigate the lateral-control characteristics associated with a wing-dropping tendency encountered at high subsonic Mach numbers. The chief factors found to account directly for the wing-dropping tendency were a progressive reduction in aileron-control effectiveness with increasing Mach number, and an increase in effective dihedral above a Mach number of 0.8 which made the lateral trim particularly sens… more
Date: April 24, 1951
Creator: Anderson, Seth B.; Ernst, Edward A. & Van Dyke, Rudolph D., Jr.
open access

Intensity, scale, and spectra of turbulence in mixing region of free subsonic jet

Description: Report presents the results of the measurements of intensity of turbulence, the longitudinal and lateral correlation coefficients, and the spectra of turbulence in a 3.5-inch-diameter free jet measured with hot-wire anemometers at exit Mach numbers from 0.2 to 0.7 and Reynolds numbers from 192,000 to 725,000.
Date: April 24, 1956
Creator: Laurence, James C.
open access

Application of supersonic vortex-flow theory to the design of supersonic impulse compressor- or turbine-blade sections

Description: From Introduction: "The purpose of this paper is to present an analytical method for the design of two-dimensional related selection of a blade for particular rotor conditions may be made quickly and easily and its performance deduced from tests of representative sections in cascade."
Date: April 24, 1952
Creator: Boxer, Emanuel; Sterrett, James R. & Wlodarski, John
open access

Instrumentation of the Ames Supersonic Free-Flight Wind Tunnel

Description: Memorandum presenting a description of the equipment used in the Ames supersonic free-flight wind tunnel to obtain the data necessary to measure the aerodynamic characteristics of free-flying models. The model is fired from a gun into the supersonic air stream of a blowdown-type wind tunnel. The action resulting from aerodynamic forces is computed from a time-distance-attitude record of the model flight through the test section.
Date: April 24, 1952
Creator: Briggs, Robert O.; Kerwin, William J. & Schmidt, Stanley F.
open access

Performance and operational characteristics of pentaborane fuel in 48-inch-diameter ram-jet engine

Description: Report presenting testing of pentaborane as a fuel in a 48-inch-diameter ram-jet engine in a free-jet facility. Each test lasted about 50 seconds and used fast-response instrumentation and prescheduled fuel-flow variation for a range of fuel-air ratios. Results regarding combustion performance, ignition, oxide deposits, and fuel-injector performance are provided.
Date: April 24, 1957
Creator: Rayle, Warren D.; Reilly, Dwight H., Jr. & Farley, John M.
open access

An analog study of the relative importance of various factors affecting roll coupling

Description: From Introduction: "In this study wide variations in many of the pertinent aerodynamic were investigated at subsonic and supersonic speeds. The effects of large changes in principal axis inclination and mass distribution are also included. The primary purpose of this paper is to summarize the information obtained from the analog calculations and to compare the results with the trends predicted from a slightly modified version of reference 2."
Date: April 24, 1956
Creator: Weil, Joseph & Day, Richard E.
open access

A Brief Investigation of the Effect of Waves on the Take-Off Resistance of a Seaplane

Description: Report presenting testing to determine the resistance of a model of a seaplane with a length-beam ratio of 15 and a wing loading of 120 pounds per square foot was determined in smooth water and three wave heights under various conditions of load, speed, elevator setting, angle of dead rise, and center-of-gravity position.
Date: April 24, 1956
Creator: Mottard, Elmo J.
open access

Experimental performance of a 5000-pound-thrust rocket chamber using a 20-percent-fluorine-80-percent-oxygen mixture with RP-1

Description: An investigation of the performance increase resulting from the addition of 20 percent fluorine to the oxygen-RP-1 propellant combination in a 5000-pound-thrust rocket engine at a chamber pressure of 650 pounds per square inch absolute.
Date: April 24, 1957
Creator: Tomazic, William A.; Kutina, Franklin J., Jr. & Rothenberg, Edward A.
open access

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.
open access

Full-Scale Free-Jet Investigation of a Two-Shock Side-Inlet Diffuser at Mach 2.75 and a Comparison With a Single-Shock Diffuser

Description: Memorandum presenting a full-scale free-jet investigation of a two-shock side-inlet diffuser at Mach umber 2.75 in an altitude test chamber. Data were obtained over ranges of free-stream total pressure and temperature. Results regarding diffuser mass-flow ratio, critical pressure recovery, diffuser static-pressure variation, and diffuser-outlet flow conditions are provided.
Date: April 24, 1957
Creator: McAulay, John E.
open access

Elevated-Temperature Fatigue Properties of Two Titanium Alloys

Description: Report presenting an investigation to evaluate the unnotched fatigue properties of two titanium alloys at elevated temperatures. A variety of temperatures were tested and the results are provided in tabular form and as curves of stress versus cycles to failure for each test temperature. Both alloys were found to have potential use at the temperature ranges investigated.
Date: April 24, 1956
Creator: Rey, William K.
open access

The System Zirconium-Iron-Tin. Status Report No. 4 for July 1, 1957- March 31, 1958

Description: A study of the solubility limits of iron and tin in alpha zirconium at temperatares below 500 deg C is in progress. Dilute alloys were prepared by arc- melting using the highest purity materials. Heat treatment of the alloys involves homogenizntion at 800 deg C followed by severe cold work prior to extended anneals at temperatures between 200 and 500 deg C in 50-degree intervals. Metallographic examination of annealed and quenched structures is the primary mode of investigation. Some magnetic s… more
Date: April 24, 1958
Creator: Tanner, L. E.
open access

RATES OF CORROSION PRODUCT REMOVAL FROM CIRCULATING SYSTEM BY FILM FORMATION AND SETTLING

Description: Iron oxide deposits removed from high pressure system of HRT after the first power run will be annlyzed for Fe/sup 59/ in an attempt to determine the time these deposits were circulated prior to deposition (settling or film formation). Deposits available are film from corrosion specimens (stainless steel, zirconium and titanium) and settled particles. (auth)
Date: April 24, 1958
Creator: Suddath, J.C.
open access

Estimate of Hazard Produced by Accidental Release of Gaseous Fission Products from an ORR Fused Salt Capsule Experiment

Description: An accidental release of gaseous fission products from an ORR fused salt capsule, containing 26 mg. of U/sup 235/, was postulated and the resuiting hazard estimated by calculating the maximum external and internal dose an individual could receive from exposure to the gaseous fission products and their decay products. Assuming all the contained gaseous fission produets are released, the resulting external and internal dosc, to organs other than the thyroid, arc insignificant. The dose to the thy… more
Date: April 24, 1959
Creator: Adams, R. E. & Browning, W. E.
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