Path: ACPro/ACPerformance
% Computes the velocity and Mach profile for constant dynamic pressure.
Computes the velocity and Mach number profile for constant dynamic
pressure as a function of altitude and desired dynamics pressure.
This function uses StdAtm. This profile is useful for ramjets
and scramjets.
For speed, if using in a loop, pass it atmData which can be loaded
with the operation:
atmData = load('AtmData.txt');
Type ConstantDynamicPressureVelocity for an example with a dynamic
pressure of 7000 N/m^2.
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Form:
[v, mach] = ConstantDynamicPressureVelocity( h, q, atmData )
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Inputs
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h (1,:) Altitude (km)
q (1,1) Dynamic pressure (N/m^2)
atmData (1,:) File name for standard atmosphere
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Outputs
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v (1,:) Velocity (m/s)
mach (1,:) Mach number
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AerospaceUtils: AeroData/AtmData Common: Atmosphere/StdAtm Common: CommonData/SwooshWatermark Common: General/CellToMat Common: General/DeBlankLT Common: General/MatToCell Common: General/Watermark Common: Graphics/NewFig Common: Graphics/Plot2D Common: Graphics/PlotDoubleYAxis Common: Graphics/PltStyle Common: Graphics/TitleS Common: Graphics/XLabelS Common: Graphics/YLabelS
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