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HyperCFD™
2.5.1 ($150.00)
Supersonic
and Hypersonic Rocket Analysis
Determine drag coefficient
(Cd), center of pressure (Xcp), CN-alpha and Cm-alpha of supersonic
and hypersonic rockets and re-entry vehicles. In addition, on
a separate screen HyperCFD displays and plots CN-Body, CN-Fins,
CN-Total and Cm-Total as a function of angle of attack (AOA)
using up/down controls. HyperCFD uses empirical corrections to
the modified Newtonian surface inclination method that allows
excellent results from Mach 1.05 to Mach 20. Includes a wide
variety of nose cone shapes and fin cross-sections. Nose cone
shapes include, conical, elliptical, parabolic, power series
Sears-Haack, tangent ogive and spherical segment. Fin cross-sections
include single wedge, symmetrical double wedge, arbitrary double
wedge, biconvex section, streamline section, round-nose section,
and elliptical section fin shapes. HyperCFD is useful to determine
supersonic rocket drag and Cp location for level 3 flights. Useful
companion program to AeroCFD &
2D-WING™.
New Features
1) Temperature on the surface of the rocket relative to free-stream
conditions.
2) Pressure and temperature can be output to a PLT file and read
as a text file.
3) Cd estimation as a function of AOA based on Newtonian surface
inclination theory.
4) Cd estimation and XCp estimation as a function of small angle
of attack (1 to 2 degrees).
5) Cd estimation for decreasing cross-sectional components.
HyperCFD Results
Case #1: Re-Entry Vehicle
HyperCFD main screen displaying
re-entry vehicle
HyperCFD re-entry vehicle pressure
distribution
Case #2: Conical Nose Cone
Case #3: Missile With Fins
Hypersonic missile In free flight
HyperCFD main screen displaying
hypervelocity missile
HyperCFD fin geometry screen for
hypervelocity missile
HyperCFD Motor On/Off screen
HyperCFD Biconic Re-Entry Vehicle
HyperCFD analysis of a Biconic re-entry
vehicle operating at Mach 5 to determine Cd (drag coefficient),
Xcp (center of pressure) and CNa (lift slope)
The following links illustrate
how HyperCFD has been used to analyze re-entry vehicles.
Revisiting China’s Early Warhead Designs
Iranian Warhead Evolution
Mars Phoenix Entry Capsule Aerodynamics
Orientation
of the Mars Phoenix entry capsule
HyperCFD analysis of the Mars
Phoenix entry capsule operating at Mach 18.5 to determine Cd,
Xcp and CNa. |
