Test flow calibration study of the Langley Arc-Heated Scramjet Test FacilityThe test flow at the exits of two square cross-section contoured nozzles with nominal exit Mach numbers of 4.7 and 6 has been studied as calibration data for the NASA-Langley Arc-Heated Scramjet Test Facility over simulated flight conditions from Mach 5.5 (at altitudes from 98,600-128,000 ft) to Mach 7 (at altitudes from 108,000-149,000 ft). Nozzle exit contour maps of measured thermodynamic properties, calculated Mach number, and calculated mass flow are used to determine the mass flow approaching the inlets of various scramjet engines. Good agreement is found between experimentally measured facility total mass flow and facility total mass flow determined by integration of the nozzle exit mass flow contours.
Document ID
19870058171
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Thomas, Scott R. (NASA Langley Research Center Hampton, VA, United States)
Voland, Randall T. (NASA Langley Research Center Hampton, VA, United States)
Guy, Robert W. (NASA Langley Research Center Hampton, VA, United States)