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open access

Accelerations in fighter-airplane crashes

Description: From Introduction: "This report describes some measurements of these quantities obtained by crashing fighter aircraft under circumstances approximating those observed in service."
Date: November 4, 1957
Creator: Acker, Loren W.; Black, Dugald O. & Moser, Jacob C.
open access

An active particle diffusion theory of flame quenching for laminar flames

Description: An equation for quenching distance based on the destruction of chain carriers by the surface is derived. The equation expresses the quenching distance in terms of the diffusion coefficients and partial pressures of the chain carriers and gas phase molecules, the efficiency of the surface as a chain breaker, the total pressure of the mixture, and a constant which depends on the geometry of the quenching surface. Quenching distances measured by flashback for propane-air flames are shown to be con… more
Date: March 4, 1952
Creator: Simon, Dorothy M. & Belles, Frank E.
open access

Aerodynamic Characteristics at a Mach Number of 6.8 of Two Hypersonic Missile Configurations, One With Low-Aspect-Ratio Cruciform Fins and Trailing-Edge Flaps and One With a Flared Afterbody and All-Movable Controls

Description: Report presenting an investigation to determine the aerodynamic characteristics in pitch at a Mach number of 6.8 of hypersonic missile configurations with cruciform trailing-edge flaps and all-movable control surfaces. Testing indicated that all-movable controls on the flared-afterbody model should be capable of producing much larger values of trim lift and of normal acceleration than the trailing-edge-flap configuration. Some of the configurations tested include body alone, body with 5 degree … more
Date: August 4, 1958
Creator: Robinson, Ross B. & Bernot, Peter T.
open access

Aerodynamic Characteristics at a Mach Number of 6.8 of Two Hypersonic Missile Configurations, One With Low-Aspect-Ratio Cruciform Fins and Trailing-Edge Flaps and One With a Flared Afterbody and All-Movable Controls

Description: Report discussing an investigation to determine the aerodynamic characteristics of hypersonic missile configurations with cruciform trailing-edge flaps with all-movable control surfaces. The all-movable controls were found to produce much larger values of trim lift and normal acceleration than the trailing-edge-flap configuration.
Date: August 4, 1958
Creator: Robinson, Ross B. & Bernot, Peter T.
open access

Aerodynamic characteristics of a 6-percent-thick symmetrical double-wedge airfoil at transonic speeds from tests by the NACA wing-flow method

Description: From Introduction: "The investigation covered a range of Mach numbers from 0.66 to 1.12 and included measurements of angle of attack, pitching moment, normal force, and chord force. The drag at zero lift obtained in this investigation was reported in reference 1, but without the correction for tare of the end plate."
Date: March 4, 1949
Creator: Lina, Lindsay J.
open access

Aerodynamic Characteristics of a 45 Degree Swept-Back Wing With Aspect Ratio of 3.5 and NACA 2S-50(05)-50(05) Airfoil Sections

Description: From Introduction: "The present paper presents the scale effect on the longitudinal aerodynamic characteristics, the aerodynamic characteristics in yaw, and the tuft studies for 0^o and 3.7^o yaw. The results of the effect of leading-edge and trailing-edge flaps on the aerodynamic characteristics of the wing will be presented in later reports."
Date: August 4, 1947
Creator: Proterra, Anthony J.
open access

The Aircraft Nuclear Propulsion Project Quarterly Progress Report for Period Ending August 31, 1950

Description: Technical report outlining various experiments that took place in the Oak Ridge Area Critical Mass Laboratory until August 31, 1950. Experiments took place in categories of critical experiments, experimental engineering, heat transfer, radiation damage, nuclear measurements, reactor physics, ARE reactor design, circulating fuel reactors, and circulating moderator reactors. [From Summary]
Date: December 4, 1950
Creator: Ellis, C. B. & Thompson, W. E.
open access

Aircraft Nuclear Propulsion Project Quarterly Progress Report for Period Ending June 10, 1956 [Declassified Version]

Description: Progress report of the Oak Ridge National Laboratory Aircraft Nuclear Propulsion Project providing updates on various projects, experiments, and other work. This report includes summaries of project activities in: aircraft reactor test design, ART physics, ART instruments and controls, component development and testing, procurement and construction, ART, ETU, and in-pile loop operations, phase equilibrium studies, chemical reactions in molten salts, physical properties of molten materials, prod… more
Date: September 4, 1956
Creator: Jordan, W. H.; Cramer, S. J.; Miller, A. J. & Savelainen, A. W.
open access

Aircraft Nuclear Propulsion Project Quarterly Progress Report for Period Ending June 10, 1956 [Secret Version]

Description: Progress report of the Oak Ridge National Laboratory Aircraft Nuclear Propulsion Project providing updates on various projects, experiments, and other work. This report includes summaries of project activities in: aircraft reactor test design, ART physics, ART instruments and controls, component development and testing, procurement and construction, ART, ETU, and in-pile loop operations, phase equilibrium studies, chemical reactions in molten salts, physical properties of molten materials, prod… more
Date: September 4, 1956
Creator: Jordan, W. H.; Cromer, S. J.; Miller, A. J. & Savelainen, A. W.
open access

Altitude-Wind-Tunnel Investigation of a 4000-Pound-Thrust Axial-Flow Turbojet Engine 5 - Analysis of Turbine Performance

Description: "Performance characteristics of the turbine of a 4000-pound-thrust axial-flow turbojet engine was determined in investigations of the complete engine in the NACA Cleveland altitude wind tunnel. Characteristics are presented as functions of the total-pressure ratio across the turbine and of turbine speed and gas flow corrected to sea-level conditions. Three turbine nozzles of different areas were used to determine the area that gave optimum performance" (p. 1).
Date: August 4, 1948
Creator: Krebs, Richard P. & Hensley, Reece V.
open access

Altitude-Wind-Tunnel Investigation of a 4000-Pound-Thrust Axial-Flow Turbojet Engine 6: Combustion-Chamber Performance

Description: "An analysis of the performance of the types A, B, and C combustion chambers of the 4000-pound-thrust axial-flow turbojet engine is presented. The data were obtained from investigations of the complete engine over a range of pressure altitudes from 5000 to 40,000 feet and ram pressure ratios from 1.00 to 1.86. The combustion-chamber pressure losses, the effect of the losses on cycle efficiency, and the combustion efficiency are discussed" (p. 1).
Date: August 4, 1948
Creator: Pinkel, I. Irving & Shames, Harold
open access

Altitude-Wind-Tunnel Investigation of Performance Characteristics of a J47D Prototype (RX1-1) Turbojet Engine With Fixed-Area Exhaust Nozzle

Description: Report presenting an investigation to determine the overall performance of a prototype model of the J47D (RX1-1) turbojet engine with a fixed-area exhaust nozzle. Data was obtained for a range of engine speeds, altitudes, and Mach numbers. Results regarding the effect of those variables and generalization in terms of pumping characteristics are provided.
Date: September 4, 1951
Creator: Saari, M. J. & Wintler, J. T.
open access

Amplitude-Probability Distributions for Atmospheric Radio Noise

Description: Report providing detail measurements and percentages in charts, using three statistical parameters, for amplitude-probability distributions of atmospheric radio noise.
Date: November 4, 1960
Creator: Crichlow, W. Q.; Spaulding, A. D.; Roubique, C. J. & Disney, R. T.
open access

Analysis and Experimental Observation of Pressure Losses in Ram-Jet Combustion Chambers

Description: From Introduction: "Some experimental data on flame-holder pressure losses have been presented (reference 1 to 4). A theoretical analysis that assume a sudden enlargement of flow area was made at the NACA Lewis laboratory to determine the effect of flame-holder open area and combustion-chamber-inlet Mach number on the pressure losses across flame holders. The results of this analysis were then compared with experimental data obtained with several different flame-holder designs."
Date: November 4, 1949
Creator: Sterbentz, William H.
open access

An analysis of a highly compounded two-stroke-cycle compression-ignition engine

Description: This report presents an analysis of a compound engine operating with manifold pressures ranging from 60 to 110 lb/sq in. absolute and discusses the effects of engine limits (peak cylinder pressure and turbine-inlet temperature) and component efficiency.
Date: April 4, 1949
Creator: Tauschek, Max J.; Sather, Bernard I. & Biermann, Arnold E.
open access

Analysis of Off-Design Operation of High Mach Number Supersonic Turbojet Engines

Description: From Introduction: "Because of the lack of data on compressor characteristics at 130 or 145 percent of design equivalent rotational speed, several simplifying assumptions were made regarding the compressor characteristics during operation at equivalent rotational speeds above the design value (hereinafter called "compressor overspeeding"). In addition to results based on these assumptions, the effect of deviation from these assumptions is discussed."
Date: February 4, 1954
Creator: English, Robert E. & Cavicchi, Richard H.
open access

Analysis of part-speed operation for high-pressure-ratio multistage axial-flow compressors

Description: From Introduction: "For the analysis reported herein, the same hypothetical 12-stage compressor discussed in reference 6 was chosen, and the effects of inlet-stage stall characteristics and stage interactions were estimated by arbitrary adjustment of the stall characteristics and stage interactions were estimated by arbitrary adjustment of the stalled characteristics of the individual stages."
Date: December 4, 1953
Creator: Benser, William A.
open access

Analytical study of losses at off-design conditions for a fixed geometry turbine

Description: From Introduction: "The purpose of this report is to present the results of the analytical investigation of the turbine of reference 1 to indicate the extent to which the various turbine losses affect the turbine efficiency over the range of performance."
Date: February 4, 1954
Creator: Stewart, Warner L. & Evans, David G.
open access

Application of a Windshield-Display System to the Low-Altitude Bombing Problem

Description: From Introduction: "The design and flight evaluation of an airborne target simulator for use in tracking studies of fighter-type airplanes equipped with optical gunsights have recently been reported (ref. 1). In this equipment the target airplane was represented by a movable dot of light projected on the windshield of the test airplane."
Date: January 4, 1957
Creator: Barnett, Robert M.; Kauffman, William M. & Fulcher, Elmer C.
open access

Application of Pulse Techniques to Strain Gages

Description: Memorandum presenting pulse techniques applied to strain gages for increasing the output level and extending the usable range. Bonded and unbonded strain gages which normally operate with exciting potentials between 3.5 and 14 volts operated satisfactorily with 200-volt pulses of 1-microsecond duration and a repetition rate of 350 per second. Results regarding maximum allowable voltages, effective pulse duration, sensitivity, minimum readable signal, effects of cable capacitance and inductance,… more
Date: May 4, 1954
Creator: Sanders, Newell D. & Brodie, George H.
open access

APPR-1 Type Absorber Rod Irradiation Test -- Irradiation Request ORNL MTR-29

Description: In order to evaluate the behavior of an APPR type absorber rod, an irradiation test program has been established. Approximately 21 more samples are planned for testing under this request. The request proposes testing a full size APPR-1 type control rod in the MTR. The objective of the test is to better evaluate the neutron absorbing material proposed for the APPR-1 control rod.
Date: January 4, 1957
Creator: Gross, E. E. & Schaffter, L. D.
open access

A Brief Hydrodynamic Investigation of a 1/24-Scale Model of the DR-77 Seaplane

Description: From Summary: "A limited investigation of a 1/24-scale dynamically similar model of the Navy Bureau of Aeronautics DR-77 design was conducted in Langley tank no. 2 to determine the calm-water take-off and the rough-water landing characteristics of the design with particular regard to the take-off resistance and the landing accelerations. During the take-off tests, resistance, trim, and rise were measured and photographs were taken to study spray. During the landing tests, motion-picture records… more
Date: June 4, 1953
Creator: Fisher, Lloyd J. & Hoffman, Edward L.
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