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AeroRocket Engineering The sole source for AeroCFD, FinSim, AeroSpike and HyperCFD  | MAIN PAGE | SUMMARY OF EXPERIENCE | Providing Affordable Aerodynamics Software Since November 1, 1999
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Latest Publications
"Rocket Spin Stabilization Using Canted Fins",
SpinSim (2002)
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Nozzle 10:
Nozzle
is a one-dimensional and two-dimensional,
compressible flow computer program for the analysis of
converging-diverging nozzles, including ramjet and scramjet engines. Nozzle models inviscid, adiabatic and hence isentropic flow of a
calorically perfect gas through variable-area ducts. Nozzle internal flow may be entirely subsonic, entirely
supersonic or a combination of subsonic
FinSIM
10
and the new Flutter Velocity Tool: Quickly and easily
predict fin flutter velocity, UF and fin divergence velocity, UD for any rocket while
specifying fins in the Fin Geometry screen by simply using a slider bar. Predict flutter velocity from
sea level all the way to maximum altitude that was defined on the main
AeroFinSim
analysis screen. Get instant flutter velocity feedback while specifying fin
AeroCFD®
is a "true" three-dimensional axisymmetric and two-dimensional
implicit finite volume CFD program that solves the inviscid Euler equations
for subsonic, transonic and supersonic flow using automatic mesh generation and
graphical results visualization. AeroCFD
provides a maximum of
100 cells in the axial direction, 50 cells in the transverse direction and
10 cells in the circumferential
(3-D) or
AeroSpike performs an expansion-wave
analysis from the throat of the thruster nozzle, where Mn = 1.0,
to the thruster nozzle internal-exit as a series of simple wave
expansions. Then, for the external ramp AeroSpike performs a
series of Prandtl-Meyer expansions from the
StarTravel performs two-body astrodynamics analyses of spacecraft and satellites knowing burnout velocity and flight-path angle at burnout. For this purpose StarTravel uses two-body astrodynamics theory for determining sub-orbital, orbital and interplanetary motion around the Earth and Sun. In addition, StarTravel performs general heliocentric and Hohmann Transfer orbital analyses for determining minimum velocity and flight time required for travel from Earth to other planets in the solar system. StarTravel also has a Solar System Calculator for animating orbital motion of the planets around the Sun. Finally, StarTravel uses the Special Theory of Relativity to determine elapsed time on Earth and aboard our starship when speeds approach the speed of light and determines the relativistic Doppler frequency shift of star light observed by our starship in the form of a color contour plot of the firmament. New in the latest version is the ability to determine the ballistic trajectory of rockets and missiles launched vertically, horizontally and everything in between. |
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Additional Links |
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Author's viXra e-print archive |
Warp Drive Research | Contact AeroRocket | |
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and supersonic including
shock waves in the diverging part of the nozzle. Shock waves are
clearly identified as vertical red lines on all plots. The cross-sectional
shape in the axial direction of the nozzle is specified by selecting
from five standard nozzle types or by defining nozzle geometry
using the Free-Form nozzle geometry method. Nozzle plots color
contours of pressure ratio, temperature ratio, density ratio,
and Mach number and has a slider bar that displays real-time values
of all nozzle flow properties. New in this version is the ability
to determine shock-angle, jet-angle (plume-angle) and Mach number
for axisymmetric and two-dimensional nozzles in the region near
the lip for underexpanded and overexpanded flow. The converging-diverging nozzle
featured in the new AeroRocket supersonic blow-down wind tunnel
was designed
using
Nozzle
applying the concept of a normal shock diffuser.
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 aerodynamic 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 and hypersonic rocket drag and center of
pressure location for medium and large scale professional sounding
rockets. Finally
geometry and get an idea of fin shock angle and fin Surface Mach number that a fin will
experience during supersonic flight. Flutter velocity accuracy is enhanced by using the
NASA web site 
thickness (2-D) direction. The latest version of AeroCFD has
increased the number of discrete finite-volumes available for analysis from
18,000 cells to 50,000 cells. Due to its "true" 3-dimensional formulation,
AeroCFD provides non-zero lift
and non-zero pitching moment for axisymmetric shapes at angle of attack without requiring computational
times exceeding one hour. Model geometry is specified by selecting from a library of standard shapes. Nose sections are defined using one of five basic shapes
that include Conical, Ogive, Elliptical, Parabolic and
Sears-Haack with power series coefficient. The user has the
option for adding up to two constant diameter sections,
one variable diameter transition section and one variable diameter
boat tail section to complete the library of user-defined shapes.
For added flexibility AeroCFD can import up to 1,000 X-R data points
for generating axisymmetric and two-dimensional designs that
require grid clustering in regions where shock waves dominate the flow.
The RESULTS section clearly displays FX, FY, MZ, CX, CY, CM, CD, CL,
base drag, surface friction drag and center of pressure location. Flow fields are
displayed using fill-contour plots, line-contour plots and surface
distribution plots for pressure coefficient, pressure ratio,
temperature ratio, density ratio and Mach number.
lip of the cowl,
where R=Re, to the entire length of the external ramp of the aerospike nozzle. The ideal contour or shape of the external
ramp of the aerospike nozzle is determined using isentropic supersonic
flow theory. Then, depending on whether the flow is underexpanded
or if the flow is overexpanded AeroSpike performs either a Prandtl-Meyer
expansion analysis or an oblique shock wave analysis to determine
the angle of the outer flow boundary from the lip of the cowl.
As a by product of the oblique shock wave analysis AeroSpike
determines the shock wave angle for overexpanded flow and plots both the
outer boundary contour and the initial shock wave from the lip of
the cowl.
