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Altitude-Wind-Tunnel Investigation of a 3000-Pound-Thrust Axial-Flow Turbojet Engine, 7, Pressure and Temperature Distributions

Description: Temperature and pressure distributions for an original and modified 3000 pound thrust axial flow turbojet engine were investigated. Data are included for a range of simulated altitudes from 5000 to 45000 feet, Mach numbers from 0.24 to 1.08, and corrected engine speeds from 10,550 to 13,359 rpm.
Date: December 10, 1948
Creator: Saari, Martin J. & Prince, William R.
Item Type: Refine your search to only Report
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An Analysis of Airspeeds and Mach Numbers Attained by Lockheed Constellation Airplanes in Transcontinental Operations During the Early Summer of 1946

Description: Report presenting airspeed and altitude data obtained from Lockheed Constellation airplanes flying between New York and San Francisco during May and June of 1946 in order to determine the probability of reaching or exceeding given values of airspeed and Mach number. Analysis indicated that the total probability of exceeding the placard "never extend" speed depends primarily on the probability of exceeding this speed in descent. The probability of exceeding the critical Mach number is very negli… more
Date: October 10, 1947
Creator: Steiner, Roy
Item Type: Refine your search to only Report
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Analysis of Iron in Thorium, Beryllium, and Cerium

Description: Introduction. the colorimetric determination of iron based on the formation of the colored ferrous-1,10-phenanthroline complex has been used successfully by a number of investigators. In this technical report, its adaptation to the routine determination of iron in cerium, thorium, and beryllium metals and their compounds is described.
Date: September 10, 1945
Creator: Ericson, R. P & Fornefeld, E. J.
Item Type: Refine your search to only Report
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Analysis of parameters for thrust control of a turbojet engine equipped with air-inlet throttle and variable-area exhaust nozzle

Description: From Introduction: "In this report, altitude, airplane velocity, exhaust-nozzle area, and turbine-inlet temperature were chosen and corresponding engine speed, fuel flow, and throttle pressure ratio were found. A detailed discussion of the engine analysis and the calculations used are presented in Appendix A. The derivations of the principal equations used are presented in appendix B."
Date: August 10, 1948
Creator: Boksenbom, Aaron S. & Feder, Melvin S.
Item Type: Refine your search to only Report
open access

Analysis of the dynamic lateral stability characteristics of the Bell X-2 airplane as affected by variations in mass, aerodynamic, and dimensional parameters

Description: Report presenting an analysis of the dynamic-lateral-stability characteristics of the Bell X-2 airplane as affected by variations in mass, aerodynamic, and dimensional parameters by means of calculations of the period and rate of damping of the lateral oscillation. Results regarding the airplane with flaps and gear retracted, airplane with flaps and gear lowered, and effects of assumed modifications to the airplane are provided.
Date: August 10, 1949
Creator: Michael, W. H., Jr. & Queijo, M. J.
Item Type: Refine your search to only Report
open access

Analytical Comparison of a Standard Turbojet Engine, a Turbojet Engine with a Tail-Pipe Burner, and a Ram-Jet Engine

Description: From Introduction: "Experimental investigations (reference 1) have shown that in some cases the thrust can be more than doubled by means of tail-pipe burning. A comparison is made of a standard turbojet engine, whose thrust is augmented by tail-pipe burning, and a ram-jet engine. The performance characteristics for the ram-jet engine were computed entirely from theoretical considerations and on the assumption that the burner-inlet velocity was constant."
Date: February 10, 1947
Creator: Krebs, Richard P. & Palasics, John
Item Type: Refine your search to only Report
open access

Automotive Antifreezes

Description: From abstract: "A report on when antifreeze should be installed, what strength should be used, and what kind of antifreeze is best suited to the service involved."
Date: November 10, 1948
Creator: Brooks, Donald B. & Streets, Ronald E.
Item Type: Refine your search to only Report
open access

Bibliography of Classified Aircraft-Fire Literature

Description: Memorandum presenting a bibliography of unclassified aircraft fire literature consisting of reports from a 20-year period ending January 1, 1949. The reports are separated into the following categories: aircraft fire accidents and statistics, combustibles, ignition sources, fire protection, fire prevention, fire resistance of materials, fire detecting, fire extinguishing, and passenger protection or rescue.
Date: November 10, 1949
Creator: Weiss, Solomon & Pesman, Gerard J.
Item Type: Refine your search to only Report
open access

Determination of average heat-transfer coefficients for a cascade of symmetrical impulse turbine blades 1: heat transfer from blades to cold air

Description: Report presenting an investigation to determine average outside surface heat-transfer coefficients for a cascade of symmetrical impulse turbine blades. Results regarding recovery factor, heat-transfer coefficients, effective gas temperature, turbine cascades, cylinders and streamline bodies, and application to rim-cooling theory are provided.
Date: November 10, 1948
Creator: Meyer, Gene L.
Item Type: Refine your search to only Report
open access

Ditching Tests of a 1/18-Scale Model of the Navy XP4M-1 Airplane in Langley Tank No. 2 and on an Outdoor Catapult, TED No. NACA 2362

Description: From Summary: "Tests with a dynamically similar model of the Navy XP4M-1 airplane were made to determine the best way to land the airplane in calm and rough water, to determine its probable ditching performance, and to determine practicable modifications which could be incorporated in the design of the airplane that would improve its ditching characteristics. The results were obtained by making visual observations, by recording longitudinal decelerations ,and by taking motion pictures of the la… more
Date: March 10, 1947
Creator: Fisher, Lloyd J. & Hoffman, Edward L.
Item Type: Refine your search to only Report
open access

Downwash in Vortex Region Behind Trapezoidal-Wing Tip at Mach Number 1.91

Description: Report presenting the results of an experimental investigation to determine the downwash in the region of the trailing vortex behind a trapezoidal-wing tip in a supersonic stream. Results regarding the downwash at spanwise stations, downwash at chordwise stations, and wake survey are provided.
Date: November 10, 1949
Creator: Cummings, J. L.; Mirels, H. & Baughman, L. E.
Item Type: Refine your search to only Report
open access

Effect of Air-Flow Distribution and Total-Pressure Loss on Performance of One-Sixth Segment of Turbojet Combuster

Description: "An investigation has been conducted on a one-sixth segment of an annular turbojet combustor to determine the effects of modification in air-flow distribution and total-pressure loss on the performance of the segment. The performance features investigated during this series of determinations were the altitude operational limits and the temperature-rise efficiency. Altitude operational limits of the combustor segment, for the 19XB engine using the original combustor-basket design were approximat… more
Date: December 10, 1947
Creator: Hill, Francis U. & Mark, Herman
Item Type: Refine your search to only Report
open access

Effect of Chordwise Vanes on Amplitude of Tail Buffeting

Description: "Flight tests have been made with a P-51D airplane to determine the effect of chordwise vanes on the amplitude of tail buffeting. The tests made during abrupt pull-ups to the buffeting boundary included strain measurements on wing and tail and tuft studies over the wing. The results indicate that the vanes tested have no appreciable effect on the amplitude of tail buffeting" (p. 1).
Date: November 10, 1947
Creator: Stokke, Allen R.
Item Type: Refine your search to only Report
open access

The Effect of Compression Ratio on Knock Limits of High-Performance Fuels in a CFR Engine 3: Blends of 2,3-Dimethylpentane With 28-R

Description: Report discussing the knock-limited performance of blends of 2,3-dimethylpentane and 23-R fuel in an F-4 engine at three sets of conditions and three compression ratios. The knock-limited performance of 2,3-dimethylpentane has about the same sensitivity to compression ratio and inlet-air temperature as 28-R fuel.
Date: February 10, 1945
Creator: Alquist, Henry E. & Tower, Leonard K.
Item Type: Refine your search to only Report
open access

Effect of leading-edge high-lift devices and split flaps on the maximum-lift and lateral characteristics of a rectangular wing of aspect ratio 3.4 with circular-arc airfoil sections at Reynolds numbers from 2.9 x 10(exp 6) to 8.4 x 10(exp 6)

Description: Report regarding the results of an investigation at high Reynolds numbers and low Mach numbers in the full-scale tunnel to determine the effect of leading-edge high-lift devices and split flaps on the maximum-lift and lateral characteristics of a rectangular wing of aspect ratio 3.4 with circular-arc airfoil section. Results regarding the maximum lift and stalling characteristics on the basic wing, effect of split-flap deflection, effect of leading-edge high-lift devices, and lateral characteri… more
Date: November 10, 1948
Creator: Lange, Roy H. & May, Ralph W., Jr.
Item Type: Refine your search to only Report
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