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Altitude performance investigation of two flame-holder and fuel-system configurations in short afterburner

Description: From Introduction: "The results of this complete evaluation of the altitude performance and operational characteristics of the two types of flame-holder and fuel-system configurations are reported herein.The starting limits of both configurations at a flight Mach number of 0.6 are also discussed."
Date: May 6, 1952
Creator: Huntley, S C & Wilsted, H D

Altitude performance and operational characteristics of an XT38-A-2 turboprop engine

Description: From Introduction: "Reported herein are the over-all engine performance and the starting and windmilling characteristics. Data are presented in the form of performance maps at each flight condition to show the effects of altitude and flight Mach number on various engine-performance variables. The effect of engine deterioration with operating time on performance is also discussed."
Date: March 12, 1954
Creator: Essig, R H & Schulze, F W

Altitude performance characteristics of tail-pipe burner with convergingconical burner section on J47 turbojet engine

Description: From Introduction: "The effect of flame-holder and fuel-system design on the burner performance and the effect of altitude and flight Mach number on over-all performance with a fixed-area exhaust nozzle are reported in reference 1 to 4. Altitude performance characteristics of a tail-pipe burner having a converging conical burner section are presented in this report. Tail-pipe burner performance at several flight conditions is given in both tabular and graphical forms and compared with performance of the standard engine and of the tail-pipe burner reported in reference 2."
Date: December 19, 1950
Creator: Prince, William R & Mcaulay, John E

Analysis of flight-determined and predicted effects of flexibility on the steady-state wing loads of the B-52 airplane

Description: From Introduction: "This paper presents the results obtained during the phase of the B-52 flight investigation concerned with the steady-state wing loads. Where possible, the effects of Mach number and flexibility on the measured load are analyzed and presented."
Date: April 23, 1958
Creator: Kuhl, Albert E; Rogers, John T & Little, Mary V

Altitude performance of pentaborane - JP-4 fuel blends in a modified J47 combustor

Description: From Introduction: "Experimental investigations of the combustion characteristics of diborane, pentaborane, and pentaborane-hydrocarbon blends in modified turbojet combustors have been conducted at this laboratory at the request of the Bureau of Aeronautics, Department of the Navy, as part of Project Zip. Results of these single-combustor tests are presented in references 2 to 5."
Date: April 17, 1957
Creator: Branstetter, J Robert & Kaufman, Warner B

An analysis of available data on effects of wing-fuselage-tail and wing-nacelle interference on the distribution of the air load among components of airplanes

Description: From Introduction: "The purpose of the present paper is to summarize the available data on the effects of wing-fuselage-tail and wing-nacelle interference on the distribution of the air load among aircraft components. Some discussion is also given of the effects of center-of-gravity position."
Date: April 11, 1949
Creator: Wollner, Bertram C

Analysis of stage matching and off-design performance of multistage axial-flow compressors

Description: From Introduction: "The present report is intended to give a qualitative picture of the operation of each stage of a multistage compressor over a range of actual operating conditions from 50 to 100 percent design speed and to point out some means of achieving improved off-design performance. The method used in the report is primarily analytical and is based on single-stage-performance results."
Date: June 27, 1952
Creator: Finger, Harold B & Dugan, James F , Jr

Analysis of several methods of pumping cooling air for turbojet engine afterburners

Description: From Introduction: "Afterburning is well established as an effective means of increasing the thrust of a turbojet engine. In order to obtain the maximum thrust from an afterburner, it is necessary to burn to the highest temperatures possible (reference 1). At these high temperatures, material limitations (reference 2) necessitate the installation of cooling systems to permit safe and reliable operation."
Date: February 2, 1953
Creator: Samuels, John C & Yanowitz, Herbert

Analysis of heat transfer and fluid friction for fully developed turbulent flow of supercritical water with variable fluid properties in a smooth tube

Description: From Summary: "Calculated velocity and temperature distributions, as well as relations among Nusselt number, Reynolds number, and friction factor, are presented. The effect of variation of fluid properties across the tube on the Nusselt number and friction factor correlations can be eliminated by evaluating the properties at a reference temperature which is a function of both the wall temperature and the ratio of wall-to-bulk temperatures."
Date: April 9, 1953
Creator: Deissler, Robert G & Taylor, Maynard F

Analysis of transonic rotor-blade passage loss with hot-wire anemometers

Description: From Introduction: "This report presents data from measurements of the flow in a single-stage research compressor, which supports the model of reference 1. A calculated shock technique similar to that of reference 1 is incorporated with these experimental results. Another approach for estimating passage shock loss given a flow rate and blade geometry was reported in reference 2."
Date: June 5, 1958
Creator: Lewis, George W; Tysl, Edward R & Fessler, Theodore E

Analysis of turbojet and ram-jet engine cycles using various fuels

Description: From Introduction: "These data have been collected for presentation in this report to illustrate the performance of turbojet and ram-jet cycles utilizing several of the more promising high-energy fuels. Results are presented in terms of engine over-all efficiency and thrust per pound of airflow as functions of flight Mach number."
Date: November 27, 1956
Creator: Tower, L. K.; Weber, R. J. & Wilcox, E. C.

Analysis of turbine stator adjustment required for compressor design-point operation in high Mach number supersonic turbojet engines

Description: From Introduction: "An investigation of the variation in turbine-entrance equivalent weight flow for a two-stage turbine equipped with an adjustable turbine stator is presented in reference 1. A general analytical investigation of turbine stator adjustment is presented in reference 2. In reference 2, the effect of stator adjustment on turbine off-design performance is also investigated by analytically computing the performance of a particular single-stage turbine."
Date: October 9, 1953
Creator: English, Robert E & Cavicchi, Richard H