AEROROCKET SOFTWARE SALES HAVE
ENDED
Effective January 5, 2014 sales of my extensive library of rocket aerodynamics and scientific
software have ended. However, all software
descriptions and instructions will continue to be displayed for
the use of past software purchasers and as a resource for the
Internet. This action is being taken to allow more time for me
to conduct a wide variety of subsonic and supersonic wind tunnel
tests for inhouse and consulting efforts. In addition, the time
afforded by this action will allow me to conduct increasingly
complex warp physics research and to publish
technical
papers in the areas of free vortex flow and
warp drive physics. Finally, all users
of my software are reminded to continue to abide by the Software
License agreement. Where it should be obvious the
singleuser license is reserved for the individual on the
order form and method of payment/check.
Thank you.
John Cipolla
Chief Aerodynamicist
AeroRocket and WarpMetrics
NOTE1: Software Installation: Download the .zip file and copy to the desktop. Then,
doubleclick the .zip file to run WinZip
which extracts and installs the computer program. If this procedure does
not work then copy the .zip file to the
desktop then rightclick the .zip file and
click Open with WinZip or Extract to... to run the
installation program. Follow the setup instructions and use
provided defaults for proper installation. Please see NOTE3,
below.
NOTE2: Input data for all AeroRocket programs must use a period (.)
and not a comma (,) and the computer must be set to the English (United States)
language. For example, gas constant should be
written as Rgas = 355.4 (J / kg*K = m^2 / sec^2*K)
and not Rgas = 355,4. The English (United States)
language is set in the
Control Panel by clicking Date, Time, Language and
Regional Options then Regional and Language Options
and finally by selecting English (United States).
If periods are not used in all inputs and outputs the results
will not be correct. See more notes below.
AeroCFD 5.1 (2.7MB)
TOP
Finite Volume CFD Analysis Program with Fins
Detailed
Information Buy
AeroCFD
is an axisymmetric threedimensional and twodimensional
Computational Fluid Dynamics program
that solves the compressible 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
(3D) or thickness (2D) direction. The latest version of AeroCFD has
increased the number of discrete finitevolumes available for analysis from
18,000 cells to 50,000 cells. Due to its "true" 3dimensional formulation,
AeroCFD provides nonzero lift
and nonzero pitching moment for axisymmetric shapes with fins 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
SearsHaack 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 userdefined shapes. For
added flexibility AeroCFD can import up to 1,000 XR data points
for generating axisymmetric and twodimensional designs that
require grid clustering in regions where shock waves dominate the flow. Flow fields are displayed using fillcontour plots, linecontour
plots and surface distribution plots for pressure coefficient,
pressure ratio, temperature ratio, density ratio and Mach number.
The RESULTS section clearly displays FX, FY, MZ, CX, CY, CM, CD, CL,
base drag, surface friction drag and center of pressure location. All output
can be sent directly to a color printer.
AeroWindTunnel
6.0 (2.7MB)
New
TOP
Airplane Flight Dynamics & Stability Analysis
for Gliding and Powered Flight
Detailed
Information Buy
AeroWindTunnel
is AeroRocket's first wind tunnel simulation program for determining
airplane and glider stability and whether or not a glider or
model airplane is stable
enough to
fly. AeroWindTunnel is a true wind tunnel simulation program in that it
determines whether an airplane is stable based on the position
of the wingbody neutral point relative to the center of gravity
and whether the relative contribution of the wings, fuselage and
vertical fins to the forces and moments around the airplane
center of gravity are sufficient for longitudinal and lateral
stability. In addition, AeroWindTunnel
uses sliderbar control to define airplane geometry instead of
timeconsuming CAD geometry definitions. AeroWindTunnel has been
validated from 0.3 Mach to 3.5 Mach using the AeroRocket wind tunnel and other
online sources. In the latest version the
maximum Mach number has been
increased from Mach 4 to Mach 30 for all coefficient plots
verses Mach number and angle of attack. Finally,
AeroWindTunnel
includes a bonus program
called
2DWING™ for the aerodynamic analysis of
twodimensional and finite aspect ratio airfoil sections.
AeroEuler
2.0 (3.4MB)
TOP
SpaceMarching CFD Training Code
Detailed
Information Buy
AeroEuler
is a new CFD training
code designed for the analysis of twodimensional and axisymmetric
supersonic flow using the MacCormack spacemarching method and
the analysis of threedimensional subsonic flow using panel methods.
This new CFD program solves supersonic flow in seconds by marching
the solution downstream using the MacCormack forwardpredictor,
backwardcorrector method. A complete derivation of the equations,
discussion of the theory and program listing will be provided
in the report, EulerCode.pdf. The 16page Euler Code Theory report
will be provided FREE with every purchase of AeroEuler and will
be distributed as part of the AeroEuler.zip download file.
AeroSpike
2.6 (4.8MB)
TOP
Minimum Length Nozzle Design &
AeroSpike Nozzle Design Program
Detailed Information Buy
AeroSpike performs 2D and 3D Minimum Length Nozzle (MLN)
design using the method of characteristics. In addition, for annular and linear aerospike
nozzle designs AeroSpike performs an expansionwave analysis
from the throat of the thruster, where Mn=1, to each
point on the plug contour to determine CF, CFvac, ISP and ISPvac
and determines the shape of the optimized aerospike nozzle. In
addition, AeroSpike plots CF, Thrust, CFvac, ISP, and ISPvac
verses pressure ratio (Pc/Pa) on a semilog scale as well as
generating color contour plots of Mn, P/Pc, T/Tc and R/Rc. New
in this version is the ability to include
base thrust pressure to
determine truncated base contribution to total thrust and thrust coefficient
(CF).
AeroIsp
3.0 (2.5MB)
TOP
Solid Rocket Motor Design Program
Detailed Information
Buy
AeroIsp
is a solid rocket motor internal ballistics
computer program that assumes the rate of combustion of the burning
gases are in dynamic equilibrium with the rate at which the exhaust
gases are expelled out the nozzle. Plots thrust, Chamber Pressure, Burn Rate Burn Area, Burn
Area Ratio (Kn), and Thrust Coefficient (Cf) as a function of
time. For the same great price AeroIsp
now includes star grain geometry and experimental curvefit
determination of burn rate coefficient and burn rate exponent.
AeroDRAG
& Flight Simulation (2.8MB)
TOP
Aerodynamic Drag Prediction and Flight Performance Analysis
Detailed Information
Buy
AeroDRAG & Flight Simulation
is a computer program that allows the rocketeer to
quickly and easily perform rocket drag (Cd) and flight simulations
using the power of Microsoft Windows. AeroDRAG & Flight Simulation
interactively predicts subsonic, transonic and supersonic rocket
drag to Mach 20 using the Newtonian surface inclination method
for nosebody and fin combinations. AeroDRAG & Flight Simulation
also performs flight simulations of rockets in vertical flight.
For flight simulations the basic equations of rocket motion are repeatedly integrated
to determine rocket velocity, altitude and acceleration using
a finite difference procedure. In this latest version of AeroDRAG
& Flight Simulation, the Cd can vary with rocket velocity
and air density varies with altitude. The ability to model the
variation of Cd with velocity (Mn) is important for accurate
high speed and high altitude rocket predictions. Finally, AeroDRAG
& Flight Simulation is unmatched in its ability to determine
subsonic drag of ringfin and tubefin stabilized rockets along
with many other new features. Now,
AeroDRAG & Flight Simulation models the
twodimensional flight path of rockets that fly in the proximity
of the gravitational field of the Earth.
AeroCP 4.0
(2.6MB)
TOP
Center of Pressure (XCp) Analysis
Detailed Information
Buy
AeroCP Provides an efficient way to compute
center of pressure location (XCp) for model and high power rockets. AeroCP
4.0 determines XCp for rockets having conical expansions,
conical reductions, boat tails, arbitrary fin shapes and several
nose cone types. In addition, AeroCP computes XCp of multiple
stage rockets where all data is clearly visible. Also, performs airframe
loads analyses in the form of shear, moment and stress
distribution plots and fin aeroelastic analyses using the
Barrowman lift curve slope (CN_alpha). This new version displays
main fins lift slope, booster fins lift slope and center of
pressure from tip of nose cone using the Barrowman equations.
AeroFinSim
4.5 (3.4MB)
New Version
TOP
Fin Structural Analysis Program
Includes Spin Stabilization and
the Theodorsen and Ug Flutter Methods
Detailed Information
Buy
is three programs in one.
First, AeroFinSim is a structural analysis program. This portion of the
program determines how strong the fins are. Second, the
program
can determine the flutter velocity of the fins. You can't know
if your fins will rip off during launch unless you know the fin
flutter velocity and the divergence velocity. Third,
AeroFinSim determines stability of spin stabilized rockets. A pdf
file that fully explains spin stabilization is included.
As an advanced feature for modeling unusually shaped fins
and wings,
added the capability to model
unsteady torsionflexure wing
oscillations for determining flutter and divergence velocity using either the
Theodorsen method or the Ug method.
HyperCFD (2.5MB)
TOP
Supersonic CFD Analysis Program
Detailed Information
Buy
HyperCFD
Determines
drag coefficient (Cd), center of pressure (Xcp) and CNalpha
of supersonic and hypersonic rockets and reentry vehicles. HyperCFD
uses empirical corrections to the modified Newtonian surface
inclination method that allows excellent results above Mach 1.05.
Includes a wide variety of nose cone shapes and fin crosssections.
Nose cone shapes include, conical, elliptical, parabolic, power
series SearsHaack, tangent ogive and spherical segment. Fin
crosssections include, single wedge, symmetrical double wedge,
arbitrary double wedge, biconvex section, streamline section,
roundnose 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.
Nozzle
3.7 (4.9MB)
TOP
ConvergingDiverging Nozzle Analysis
Detailed Information
Buy
Nozzle
is a onedimensional compressible flow computer program
for the analysis of convergingdiverging rocket nozzles. Nozzle
internal flow may be entirely subsonic, entirely supersonic or
a combination of subsonic 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 crosssectional
shape in the axial direction of the nozzle is specified by selecting
from five standard nozzle types or by defining nozzle geometry
using the FreeForm nozzle geometry method. Nozzle plots color
contours of pressure ratio, temperature ratio, density ratio,
and Mach number and has a slider bar that displays realtime
values of all nozzle flow properties. New in this version is
the ability to determine shockangle, jetangle (plumeangle)
and Mach number for axisymmetric and twodimensional nozzles
in the region near the lip for underexpanded and overexpanded
flow.
StarTravel
(3.7MB)
New
TOP
Astrodynamics & Relativistic Flight
Detailed Information
Buy
StarTravel performs
twobody astrodynamics analyses of spacecraft and satellites
knowing burnout velocity and flightpath angle at burnout. For
this purpose StarTravel
uses twobody astrodynamics for determining suborbital, 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 of StarTravel is the ability
to
determine the ballistic trajectory of rockets
and missiles launched vertically, horizontally and everything in
between.
Developed Satellite Trajectory Kit to determine the ballistic trajectory of rockets
and missiles launched vertically, horizontally and everything in
between. Perform a Variable Specific Impulse Magnetoplasma
Rocket (VASIMR) analysis or a standard constant specific impulse rocket
analysis (nuclear propulsion) by specifying starting exhaust velocity and ending
exhaust velocity or constant exhaust velocity for
heliocentric flight to planets and stars.
Wind Tunnel Course
(4MB)
TOP
How to use the AeroRocket
Subsonic Wind Tunnel
Detailed Information
Buy WindTunnelCourse
shows stepbystep how to compute aerodynamic coefficients
like CD, CL, L/D, XCP, Cn, Ca,
Cm, Cna and CMa from voltages generated by the Force Measurement
System's DRAG and LIFT load cells. Also, detailed mechanical
drawings, wind tunnel test procedures and description of
various wind tunnel components not previously described by
the WindTunnelPlans.pdf file is provided. In
addition, a QuickTime video describing the AeroRocket wind
tunnel in more detail is provided as part of the package.
Wind Tunnel Testing
$75.00/Hour
TOP
AeroRocket Subsonic Wind Tunnel
Testing
Detailed Information
Email for
FREE quote
Have
your designs tested in the
AeroRocket
Wind Tunnel. Determine lift (CL) and drag (CD) coefficients for
any aerodynamic shape utilizing the wind tunnel's twocomponent
force measurement system. The wind tunnel at AeroRocket's disposal
was developed inhouse to provide a wide range of lift, drag,
velocity and pressure profile measurements.
AeroRocket will fabricate your wind tunnel model or
use the model you fabricate yourself. Please
contact AeroRocket to receive a free cost estimate for wind
tunnel testing.
MORE NOTES:
NOTE3: To install
AeroRocket software the user requires WinZip, the
original and most popular compression utility for Windows ...
Please click
for
more information.
NOTE4: All AeroRocket programs are fully compatible
with Windows Vista,
Windows 7 and Windows XP, etc.
NOTE5: To view the Spool Rocket Report, RMTS
Detailed Plans and selected software instructions please use
Adobe Acrobat Reader. Free download using the following link.
AEROROCKET
SOFTWARE LICENSE:
BY DOWNLOADING AEROROCKET SOFTWARE THE USER IS AGREEING THE SOFTWARE
IS PRESENTED ASIS AND NO WARRANTY IS EXPRESSED OR IMPLIED. THE
SOFTWARE USER
TAKES COMPLETE RESPONSIBILITY FOR OPERATING THE SOFTWARE AND PROPERLY
INTERPRETING THE RESULTS. IN ADDITION, ALL AEROROCKET PROGRAMS
ARE INTENDED FOR SINGLELICENSE OR SINGLE USER USE. WHILE MAKING BACKUP COPIES IS
ALLOWED, AEROROCKET PROGRAMS MAY NOT BE DISTRIBUTED OR
DONATED TO ANYONE OUTSIDE THE ORGANIZATION OR HOUSEHOLD. ALSO, AEROROCKET SOFTWARE MUST NOT BE
PLACED ON THE INTERNET OR UPLOADED TO ANY THIRD PARTY WEB SITE
BECAUSE THIS ACTION VIOLATES TRADEMARK, COPYRIGHT AND
IS IN VIOLATION OF THIS AGREEMENT.
INDIVIDUALS AND COMPANIES WHO DO NOT COMPLY WITH THIS SOFTWARE
AGREEMENT WILL BE PLACED ON THE
SALES BANNED LIST
WHICH MAKES THEM INELIGIBLE FOR UPGRADES.
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