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Aerodynamic principles for the design of jet-engine induction systems

Description: From Introduction: "It is the purpose of this report to assemble principles of induction-system design for flight to a Mach number of 2 and to use existing data to show the consequences of compromising them."
Date: February 27, 1956
Creator: Davis, Wallace F. & Scherrer, Richard
open access

Comparison of Combustion Reactivity of Ethyldecaborane Fuels With Typical Hydrocarbon Fuels on Basis of Spray Flammability Limits of Fuel-Rich Mists and Calculated Lean-Limit Flame Temperatures for Fuel Vapor-Air Systems

Description: From Summary: "The spray flammability limits of various high-energy fuels and hydrocarbon fuels were determined experimentally in an apparatus which measured the minimum percent of oxygen by volume that would permit the ignition of a particular fuel. The fluids investigated were ethyldecaboranes, aliphatic hydrocarbons, olefins, aromatic hydrocarbons, and esters."
Date: February 27, 1957
Creator: Wise, Paul H. & Lipschitz, Abraham
open access

Comparison of Turbojet-Engine Altitude Performance Characteristics and Ignition Limits With MIL-F-5624A Fuel, Grades JP-3 and JP-4

Description: The performance of MIL-F-5624A fuels, grades JP-3 and JP-4, was investigated in an axial-flow turbojet engine over a range of altitude conditions of 10,000 to 55,000 feet. Examination of the fuel flow, combustion efficiency, and net thrust specific fuel consumption showed the grade JP-4 fuel to be slightly inferior to the grade JP-3 fuel, although the altitude ignition limits were essentially equal for the two fuels over a range of flight Mach numbers and fuel-inlet temperatures.
Date: February 27, 1952
Creator: Braithwaite, Willis M. & Renas, Paul E.
open access

Design and test of mixed-flow impellers 8: comparison of experimental results for three impellers with shroud redesigned by rapid approximate method

Description: Report presenting a comparison of three centrifugal impellers with parabolic, circular, and skewed-parabolic blading that were modified using a recently developed design procedure to reduce velocity gradients along the hub from inlet to outlet. All of the original dimensions except for the shroud contours were retained. Results regarding a comparison of the original and modified parabolic-bladed, circular-bladed, and skewed-parabolic bladed impeller are provided.
Date: February 27, 1957
Creator: Osborn, Walter M.; Smith, Kenneth J. & Hamrick, Joseph T.
open access

Experimental investigation of ejector-nozzle metal temperatures

Description: Metal temperatures were obtained on a full-scale ejector nozzle installed on an afterburner operating at exhaust-gas temperatures up to 3450 degrees R. A favorable afterburner-outlet temperature profile helped keep the primary-jet nozzle components cool. The ejector shroud temperatures were much more sensitive to secondary airflow than were temperatures on the primary-jet nozzle.
Date: February 27, 1957
Creator: Shillito, Thomas B. & Koffel, William K.
open access

Preliminary Investigation of the Combustion of Pentaborane and Diborane in a Turbojet Combustor at Simulated Altitude Conditions

Description: Report presenting an investigation to determine the combustion characteristics of pentaborane and diborane in a turbojet combustor. Four different test conditions were explored, which varied in inlet total pressure, temperature, and simulated flight conditions. Results regarding the combustor itself and performance of diborane fuel at high altitude are provided.
Date: February 27, 1957
Creator: Gibbs, J. B.; Kaufman, W. B. & Branstetter, J. R.
open access

Pressure Recovery, Drag, and Subcritical Stability Characteristics of Conical Supersonic Diffusers With Boundary-Layer Removal

Description: A study of two 20 degrees half-angle, low mass-flow ratio conical supersonic inlets with cone boundary-layer bleed was made on a 16-inch ram-jet engine in the Lewis 8- by 6-foot supersonic wind tunnel. A greater stable subcritical range of operation was obtained with the bleed inlets than with the corresponding inlet without boundary-layer bleed. The drag added by the bleed system was small.
Date: February 27, 1952
Creator: Obery, Leonard J.; Englert, Gerald W. & Nussdorfer, Theodore J.
open access

Pressure Recovery, Drag, and Subcritical Stability Characteristics of Three Conical Supersonic Diffusers at Stream Mach Numbers From 1.7 to 2.0

Description: A study of a 20 degree and a 25 degree half-angle high mass-flow ratio conical supersonic inlet was made on a 16-inch ram jet in the 8- by 6-foot supersonic tunnel. A greater range of stable subcritical operation was obtained with the low mass-flow ratio inlets; a greater range was obtained with the 25 degree than with the 20 degree half-angle low mass-flow ratio inlet. The high mass-flow ratio inlet had the least drag.
Date: February 27, 1952
Creator: Nussdorfer, Theodore J.; Obery, Leonard J. & Englert, Gerald W.
open access

Stall Characteristics Obtained from Flight 10 of Northrop X-4 No. 2 Airplane (USAF No. 46-677)

Description: NACA instrumentation has been installed in the X-4 airplanes to obtain stability and control data during the acceptance tests conducted by the Northrop Aircraft Corporation. This report presents data obtained on the stalling characteristics of the airplane in the clean and gear- down configurations. The center of gravity was located at approximately 18 percent of the mean aerodynamic chord during the tests. The results indicated that the airplane was not completely stalled when stall was gradua… more
Date: February 27, 1950
Creator: Sadoff, Melvin & Sisk, Thomas R.
open access

A summary of the longitudinal and lateral stability and control characteristics obtained from rocket-model tests of a swept-wing fighter-type airplane at Mach numbers from 0.5 to 1.9

Description: Report presenting a flight investigation of a swept-wing fighter-type airplane to determine drag coefficients, longitudinal and lateral stability derivatives, effects of aeroelasticity on rolling effectiveness, and the effect of the engine jet exhaust on the trim characteristics over the range of Mach numbers.
Date: February 27, 1957
Creator: Mitcham, Grady L.
open access

Tabulated pressure data for several flap-type trailing edge controls on a trapezoidal wing at Mach numbers of 1.61 and 2.01

Description: Report presenting an investigation at two Mach numbers for a range of Reynolds numbers to determine the pressure distributions at several spanwise stations for a series of 25.4-percent-chord trailing-edge controls on a trapezoidal wing with a 23 degree sweptback leading edge, aspect ratio of 3.1, and taper ratio of 0.4. The report contains the tabulated pressure data for the complete range of test variables.
Date: February 27, 1956
Creator: Lord, Douglas R. & Czarnecki, K. R.
open access

Transonic Characteristics of a 45 Degree Sweptback Wing-Fuselage Combination: Effect of Longitudinal Wing Position and Division of Wing and Fuselage Forces and Moments

Description: Report presenting an investigation on a body of revolution with a sweptback wing with a 0.25-mean-aerodynamic-chord point at the maximum body diameter and 1.2 mean aerodynamic chords behind the maximum diameter. The fuselage had a fineness ratio of 10, a 45 degree swept wing with an aspect ratio of 4.0, a taper ratio of 0.6, and NACA 65A006 airfoil sections parallel to the plane of symmetry. Lift, drag, pitching moments, and angles of attack were measured at a range of Mach numbers.
Date: February 27, 1953
Creator: Hallissy, Joseph M. & Bowman, Donald R.
open access

Turbojet-engine evaluation of AISI 321 and AISI 347 stainless steels as nozzle-blade materials

Description: Report presenting an investigation to evaluate the engine service performance of nozzle-diaphragm blades of AISI 321 and AISI 347 stainless steels. Data were obtained from three nozzle diaphragms alternately bladed with each of the two materials. Results regarding a visual inspection, a metallurgical examination, the mechanism of cracking, and the classification of failures are provided.
Date: February 27, 1950
Creator: Garrett, Floyd B. & Yaker, Charles
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