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Path: Thermal/ThermalAnalysis
% Aerodynamic heat flux.
The input may be a data structure or a file name of a .mat file
containing the data structure. Since this uses the standard atmosphere
model it only works up to 80 km. See StdAtm.m.
This model uses the assumption that the tip is blunt and that the
Prandtl number is 1. The heat flux is therefore (1/4)cF rho V^3.
The characteristic length is the radius of a nose cone or length
of the flat surface.
Type AeroHeatFlux for a demo.
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Form:
AeroHeatFlux
qDot = AeroHeatFlux( f, sigma )
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Inputs
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f (1,:) Filename
or
(1,1) Data structure
.time (1,:) Time (sec) (Plotting only)
.velocity (1,:) Velocity (m/s)
.altitude (1,:) Altitude (m)
.range (1,:) Range (m) (Plotting only)
sigma (1,1) Characteristic length (m)
type (1,:) 'laminar plate' 'turbulent plate' 'blunt nose'
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Outputs
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qDot (1,:) Heat flux (W/m^2)
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References: H. Julian Allen and A. J. Eggers, Jr., "A Study of the
Motion and Aerodynamic Heating of Ballistic Missiles
Entering the Earth's Atmosphere at High Supersonic
Speeds," NACA Report 1381.
Hankey, W., 'Re-entry Aerodynamics", AIAA Press.
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AeroUtils: AtmosphericCalculations/ReynoldsNumber AeroUtils: AtmosphericCalculations/SutherlandsLaw AeroUtils: AtmosphericCalculations/TemperatureStagnation Common: Atmosphere/StdAtm Common: Graphics/Plot2D Common: Graphics/TimeLabl
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