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The NASA Langley 8-foot Transonic Pressure Tunnel calibrationThe NASA Langley 8-Foot Transonic Pressure Tunnel is a continuous-flow, variable-pressure wind tunnel with control capability to independently vary Mach number, stagnation pressure, stagnation temperature, and humidity. The top and bottom walls of the test section are axially slotted to permit continuous variation of the test section Mach number from 0.2 to 1.2, the slot-width contour provides a gradient-free test section 50 in. long for Mach numbers equal to or greater than 1.0 and 100 in. long for Mach numbers less than 1.0. The stagnation pressure may be varied from 0.25 to 2.0 atm. The tunnel test section has been recalibrated to determine the relationship between the free-stream Mach number and the test chamber reference Mach number. The hardware was the same as that of an earlier calibration in 1972 but the pressure measurement instrumentation available for the recalibration was about an order of magnitude more precise. The principal result of the recalibration was a slightly different schedule of reentry flap settings for Mach numbers from 0.80 to 1.05 than that determined during the 1972 calibration. Detailed tunnel contraction geometry, test section geometry, and limited test section wall boundary layer data are presented.
Document ID
19950004327
Acquisition Source
Legacy CDMS
Document Type
Technical Publication (TP)
Authors
Brooks, Cuyler W., Jr.
(NASA Langley Research Center Hampton, VA, United States)
Harris, Charles D.
(NASA Langley Research Center Hampton, VA, United States)
Reagon, Patricia G.
(NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 6, 2013
Publication Date
August 1, 1994
Subject Category
Aerodynamics
Report/Patent Number
NAS 1.60:3437
L-17322
NASA-TP-3437
Accession Number
95N10739
Funding Number(s)
PROJECT: RTOP 505-59-10-30
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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