Standard method of graphical presentation of centrifugal compressor performance /

The NACA Subcommittee on Supercharger Compressors has recommended the use of the method described in this report, for comparing the performance of centrifugal compressors, and it has been adopted by the NACA as a standard.Prepared at the Aircraft Engine Research Laboratory, Cleveland, Ohio.Originally issued as NACA as Advance Restricted Report E5F13a (August 1945).NACA Wartime Report E-4.Includes bibliographical references.The NACA Subcommittee on Supercharger Compressors has recommended the use of the method described in this report, for comparing the performance of centrifugal compressors, and it has been adopted by the NACA as a standard.Mode of access: Internet

Recommended test procedure for aircraft engine turbosupercharger power plants /

This procedure is designed to provide for the aircraft, engine, turbosupercharger manufacturers, and other interested groups a guide for instrumenting, testing, and presenting the over-all characteristics of any engine-turbosupercharger installation.Prepared at the Aircraft Engine Research Laboratory, Cleveland, Ohio.Advance Restricted Report E3F22?Originally issued as NACA as Advance Restricted Report 3G14 (June 1943).NACA Wartime Report E-135.Includes bibliographical references.This procedure is designed to provide for the aircraft, engine, turbosupercharger manufacturers, and other interested groups a guide for instrumenting, testing, and presenting the over-all characteristics of any engine-turbosupercharger installation.Mode of access: Internet

Standard procedures for rating and testing centrifugal compressors /

The test-rig installation, measurements, instrumentation, test procedure, methods of calculation, and presentation of data, adopted by the National Advisory Committee for Aeronautics as standard for rating and testing centrifugal superchargers, are given in this paper.Prepared at the Aircraft Engine Research Laboratory, Cleveland, Ohio.Originally issued as NACA as Advance Restricted Report E5F13 (August 1945).NACA Wartime Report E-6.Includes bibliographical references.The test-rig installation, measurements, instrumentation, test procedure, methods of calculation, and presentation of data, adopted by the National Advisory Committee for Aeronautics as standard for rating and testing centrifugal superchargers, are given in this paper.Mode of access: Internet

A preliminary investigation of the icing characteristics of a large rectangular-throat pressure-type carburetor /

A rectangular-throat pressure-type carburetor was investigated to determine the icing characteristics of this part of a large four-engine bomber induction system. Runs of 15-minute duration were made at a simulated low-cruising power condition over a range of carburetor-air temperatures from 12 to 100 degrees F with varied moisture contents to establish the limiting conditions for the formation of visible and serious icing. The investigation included icing tests made with a standard nozzle bar and an impinging-jets nozzle bar.Prepared at the Aircraft Engine Research Laboratory, Cleveland, Ohio.Originally issued as NACA as Memorandum Report E6G11 (July 1946).NACA Wartime Report E-284.Includes bibliographical references.A rectangular-throat pressure-type carburetor was investigated to determine the icing characteristics of this part of a large four-engine bomber induction system. Runs of 15-minute duration were made at a simulated low-cruising power condition over a range of carburetor-air temperatures from 12 to 100 degrees F with varied moisture contents to establish the limiting conditions for the formation of visible and serious icing. The investigation included icing tests made with a standard nozzle bar and an impinging-jets nozzle bar.Mode of access: Internet

A general representation for axial-flow fans and turbines /

A general representation of fan and turbine arrangements on a single classification chart is presented which is made possible by a particular definition of the stage of an axial-flow fan or turbine. Several unconventional fan and turbine arrangements are indicated and the applications of these arrangements are discussed.Prepared at the Aircraft Engine Research Laboratory, Cleveland, Ohio.Originally issued as NACA as Advance Restricted Report E5E04 (June 1945).NACA Wartime Report E-10.Includes bibliographical references.A general representation of fan and turbine arrangements on a single classification chart is presented which is made possible by a particular definition of the stage of an axial-flow fan or turbine. Several unconventional fan and turbine arrangements are indicated and the applications of these arrangements are discussed.Mode of access: Internet

Heat-transfer tests of aqueous ethylene glycol solutions in an electrically heated tube /

As part of an investigation of the cooling characteristics of liquid-cooled engines, tests were conducted with an electrically heated single-tube heat exchanger to determine the heat-transfer characteristics of AN-E-2 ethylene glycol and other ethylene glycol-water mixtures for a range of conditions.Prepared at the Aircraft Engine Research Laboratory, Cleveland, Ohio.Originally issued as NACA as Advance Restricted Report E5F07 (August 1945).NACA Wartime Report E-136.Includes bibliographical references.As part of an investigation of the cooling characteristics of liquid-cooled engines, tests were conducted with an electrically heated single-tube heat exchanger to determine the heat-transfer characteristics of AN-E-2 ethylene glycol and other ethylene glycol-water mixtures for a range of conditions.Mode of access: Internet

Analysis of spark-ignition engine knock as seen in photographs taken at 200,000 frames a second /

A motion-picture of the development of knock in a spark-ignition engine is presented, which consists of 20 photographs taken at intervals of 5 microseconds, or at a rate of 200,000 photographs a second, with an equivalent wide-open exposure time of 6.4 microseconds for each photograph. A motion picture of a complete combustion process, including the development of knock, taken at the rate of 40,000 photographs a second is also presented to assist the reader in orienting the photographs of the knock development taken at 200,000 frames per second are analyzed and the conclusion is made that the type of knock in the spark-ignition engine involving violent gas vibration originates as a self-propagating disturbance starting at a point in the burning or autoigniting gases and spreading out from that point through the incompletely burned gases at a rate as high as 6800 feet per second, or about twice the speed of sound in the burned gases. Apparent formation of free carbon particles in both the burning and the burned gas is observed within 10 microseconds after passage of the knock disturbance through the gases.Other authors include: H. Lowell and Olsen, Walter O. Logan, Jr., and Gordon E. Osterstrom.Prepared at the Aircraft Engine Research Laboratory, Cleveland, Ohio.Originally issued as NACA as Advance Restricted Report E6D23 (May 1946).NACA Wartime Report E-239.Includes bibliographical references.A motion-picture of the development of knock in a spark-ignition engine is presented, which consists of 20 photographs taken at intervals of 5 microseconds, or at a rate of 200,000 photographs a second, with an equivalent wide-open exposure time of 6.4 microseconds for each photograph. A motion picture of a complete combustion process, including the development of knock, taken at the rate of 40,000 photographs a second is also presented to assist the reader in orienting the photographs of the knock development taken at 200,000 frames per second are analyzed and the conclusion is made that the type of knock in the spark-ignition engine involving violent gas vibration originates as a self-propagating disturbance starting at a point in the burning or autoigniting gases and spreading out from that point through the incompletely burned gases at a rate as high as 6800 feet per second, or about twice the speed of sound in the burned gases. Apparent formation of free carbon particles in both the burning and the burned gas is observed within 10 microseconds after passage of the knock disturbance through the gases.Mode of access: Internet

Performance characteristics of a Junkers Jumo 211F engine supercharger with a DVL fully shrouded impeller and scroll diffuser /

A German supercharger from a Junkers Jumo 211F engine was tested by the NACA. The supercharger differed from conventional American superchargers in that it had a fully shrouded impeller, which discharged through a very short vaneless diffuser into a scroll-collector case.Prepared at the Aircraft Engine Research Laboratory, Cleveland, Ohio.Originally issued as NACA as Advance Restricted Report E5B03 (February 1945).NACA Wartime Report E-3.Includes bibliographical references.A German supercharger from a Junkers Jumo 211F engine was tested by the NACA. The supercharger differed from conventional American superchargers in that it had a fully shrouded impeller, which discharged through a very short vaneless diffuser into a scroll-collector case.Mode of access: Internet

Knocking tendency of an air-cooled aircraft-engine cylinder with one and with two spark plugs /

Tests have been conducted with an air-cooled aircraft-engine cylinder to determine the effect on the knocking tendency of cutting out one spark plug when the engine is operating at or near the knock point with two spark plugs firing.Prepared at the Aircraft Engine Research Laboratory, Cleveland, Ohio.Advance Restricted Report E3G23?Originally issued as NACA as Advance Restricted Report 3G23 (July 1943).NACA Wartime Report E-133.Includes bibliographical references.Tests have been conducted with an air-cooled aircraft-engine cylinder to determine the effect on the knocking tendency of cutting out one spark plug when the engine is operating at or near the knock point with two spark plugs firing.Mode of access: Internet

Relation between spark-ignition engine knock, detonation waves, and autoignition as shown by high-speed photography /

A critical review of literature bearing on the autoignition and detonation-wave theories of spark-ignition engine knock and on the nature of gas vibrations associated with combustion and knock results in the conclusion that neither the autoignition theory nor the detonation-wave theory is an adequate explanation of spark-ignition engine knock. A knock theory is proposed, combining the autoignition and detonation-wave theories, introducing the idea that the detonation wave develops in autoignited or afterburning gases, and ascribing comparatively low-pitched heavy knocks to autoignition but high-pitched pinging knocks to detonation waves with the possibility of combinations of the two types of knock.Prepared at the Aircraft Engine Research Laboratory, Cleveland, Ohio.Originally issued as NACA as Advance Restricted Report E6C22 (April 1946).NACA Wartime Report E-238.Includes bibliographical references.A critical review of literature bearing on the autoignition and detonation-wave theories of spark-ignition engine knock and on the nature of gas vibrations associated with combustion and knock results in the conclusion that neither the autoignition theory nor the detonation-wave theory is an adequate explanation of spark-ignition engine knock. A knock theory is proposed, combining the autoignition and detonation-wave theories, introducing the idea that the detonation wave develops in autoignited or afterburning gases, and ascribing comparatively low-pitched heavy knocks to autoignition but high-pitched pinging knocks to detonation waves with the possibility of combinations of the two types of knock.Mode of access: Internet