7 Matching Results

Search Results

Advanced search parameters have been applied.
in subjects: "pressure characteristics"  
Results: 1 - 7
open access

Measurement of Static Pressure on Aircraft

Description: "Existing data on the errors involved in the measurement of static pressure by means of static-pressure tubes and fuselage vents are presented. The errors associated with the various design features of static-pressure tubes are discussed for the condition of zero angle of attack and for the case where the tube is inclined to flow. Errors which result from variations in the configuration of static-pressure vents are also presented" (p. 645).
Date: December 17, 1956
Creator: Gracey, William
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Investigation of the flow through a single-stage two-dimensional nozzle in the Langley 11-inch hypersonic tunnel

Description: Report presenting flow surveys in the second of several nozzles to be investigated in the 11-inch hypersonic tunnel. The single-stage, two-dimensional nozzle was designed by the method of characteristics for a Mach number of 7.08 without boundary-layer corrections. Results regarding the variation of flow properties with time, variation of flow parameters with settling-chamber pressure, calibration surveys, and general discussion of the nozzle characteristics are provided.
Date: December 1950
Creator: McLellan, Charles H.; Williams, Thomas W. & Beckwith, Ivan E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

A balanced diaphragm type of maximum cylinder pressure indicator

Description: A balanced diaphragm type of maximum cylinder pressure indicator was designed to give results consistent with engine operating conditions. The apparatus consists of a pressure element, a source of controlled high pressure and a neon lamp circuit. The pressure element, which is very compact, permits location of the diaphragm within 1/8 inch of the combustion chamber walls without water cooling. The neon lamp circuit used for indicating contact between the diaphragm and support facilitates the us… more
Date: December 1930
Creator: Spanogle, J. A. & Collins, John H., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Pressure Measurements on an Afterbody Behind Various Blunt Nose Shapes at a Mach Number of 2

Description: Memorandum presenting an investigation of flow surrounding afterbodies behind blunt nose shapes at a Mach number of 2 in the 27- by 27-inch preflight jet. Pressure measurements were made on and around the afterbodies for each configuration.
Date: December 27, 1957
Creator: Speegle, Katherine C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Calculation of the Pressures on Aircraft Engine Bearings

Description: For aircraft engines the three principal operating conditions are idling speed, cruising speed, and diving with the engine stopped. In what follows, we will discuss a method which affords a good idea of the course of pressure for the above mentioned operating conditions. The pressures produced in the driving gear are of three kinds; namely, the pressure due to gases, the pressure due to the inertia of the rotating masses, and the pressure due to the inertia of the reciprocating masses.
Date: December 1929
Creator: Steigenberger, O.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Theoretical and Experimental Investigation of Aerodynamic-Heating and Isothermal Heat-Transfer Parameters on a Hemispherical Nose With Laminar Boundary Layer at Supersonic Mach Numbers

Description: Note presenting a determination of the effect of a strong, negative pressure gradient on the local rate of heat transfer through a laminar boundary layer on the isothermal surface of an electrically heated, cylindrical body of revolution with a hemispherical nose from wind-tunnel tests at a Mach number of 1.97. Results regarding pressure distributions, temperature distributions and recovery factor, and heat transfer are provided.
Date: December 1954
Creator: Stine, Howard A. & Wanlass, Kent
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Investigation of a High-Pressure-Ratio Eight-Stage Axial-Flow Research Compressor With Two Transonic Inlet Stages 1: Aerodynamic Design

Description: Memorandum presenting an eight-stage high-pressure-ratio axial-flow compressor designed for use as a research unit in which the problems associated with design and off-design performance of transonic stages combined with highly loaded subsonic stages could be studied. The report discusses the design procedure and presents the experimentally determined overall performance of the compressor.
Date: December 4, 1953
Creator: Voit, Charles H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
Back to Top of Screen