NDLI: Real-air data reduction procedures based on flow parameters measured in the test section of supersonic and hypersonic facilities

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Real-air data reduction procedures based on flow parameters measured in the test section of supersonic and hypersonic facilities

Content Provider	NASA Technical Reports Server (NTRS)
Author	Wilder, S. E. Miller II, C. G.
Copyright Year	1972
Description	Data-reduction procedures for determining free stream and post-normal shock kinetic and thermodynamic quantities are derived. These procedures are applicable to imperfect real air flows in thermochemical equilibrium for temperatures to 15 000 K and a range of pressures from 0.25 N/sq m to 1 GN/sq m. Although derived primarily to meet the immediate needs of the 6-inch expansion tube, these procedures are applicable to any supersonic or hypersonic test facility where combinations of three of the following flow parameters are measured in the test section: (1) Stagnation pressure behind normal shock; (2) freestream static pressure; (3) stagnation point heat transfer rate; (4) free stream velocity; (5) stagnation density behind normal shock; and (6) free stream density. Limitations of the nine procedures and uncertainties in calculated flow quantities corresponding to uncertainties in measured input data are discussed. A listing of the computer program is presented, along with a description of the inputs required and a sample of the data printout.
File Size	3516745
Page Count	93
File Format	PDF
Alternate Webpage(s)	http://archive.org/details/NASA_NTRS_Archive_19720011674
Archival Resource Key	ark:/13960/t8md3pr5d
Language	English
Publisher Date	1972-03-01
Access Restriction	Open
Subject Keyword	Fluid Mechanics Supersonic Flow Thermodynamics Reaction Kinetics Flow Measurement Real Gases Hypersonic Flow Free Flow Data Reduction Shock Tunnels Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science
Content Type	Text
Resource Type	Technical Report

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