Open AccessCALIBRATION OF MACH 2 NOZZLE BLOCKS WITH 6% PERFORATED-WALL TEST SECTION
Author(s) -
W. T. Botner,
H.R. Spahr,
R.C. Maydew
Publication year - 1959
Language(s) - English
Resource type - Reports
DOI - 10.2172/4187277
Subject(s) - mach number , transonic , nozzle , wind tunnel , calibration , mach wave , subsonic and transonic wind tunnel , section (typography) , drag divergence mach number , rocket engine nozzle , range (aeronautics) , supersonic wind tunnel , hypersonic wind tunnel , mechanics , aerospace engineering , aerodynamics , engineering , physics , computer science , quantum mechanics , operating system
The speed range of the Sandia 12-by-12-inch transonic wind tunnel was recently increased from Mach 1.35 to Mach 2.0 by the installation of interchangeable fixed Mach 2 nozzle blocks. The installed blocks are shown. (auth
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