Path: ACPro/ACEngine
% A/A* computation from mach number and ratio of specific heats.
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Form:
a = AOverAStar( gamma, machNo )
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Inputs
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gamma (1,1) Ratio of specific heats
machNo (1,:) Mach number
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Outputs
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a (1,:) A/A*
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Reference: Mattingly, "Elements of Gas Turbine Propulsion,"
McGraw-Hill, 1996, p. 878.
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Common: CommonData/SwooshWatermark Common: General/CellToMat Common: General/MatToCell Common: General/Watermark Common: Graphics/NewFig Common: Graphics/Plot2D Common: Graphics/PltStyle
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