AeroRocket Software Products
AeroCFD® 
AeroWindTunnel™ 
AeroSpike 
Nozzle 
AeroIsp™
AeroDRAG &
Flight Simulation™ 
AeroCP™ 
HyperCFD™ 
AeroFinSim™
AeroEuler™

StarTravel™

Wind Tunnel Course 
Buy
Latest Publications
“Potential Vortex
Transient Analysis and Experiment”, viXra
eprint archive, (2014)
"Hydrodynamic Analogue for Curved SpaceTime and General
Relativity", viXra eprint
archive, (2014)
Experimental Rocket Launches
Sprint Experimental Rocket
Sprint Model Rocket
AeroRocket
specializes in subsonic,
supersonic and hypersonic aerodynamics, Computational Fluid Dynamics
(CFD), warp drive physics and aerospace related
software development for rockets, airplanes and gliders. Other services include wind tunnel testing using
the AeroRocket designed and fabricated subsonic
wind tunnel and supersonic
blowdown wind tunnels.
AeroRocket software sales have ended. However, students and student
groups can receive a free donation of
AeroRocket software by
emailing a short description of use. Others may
request donated AeroRocket software on a case by case
basis. Please limit two per request.
John Cipolla
Chief Aerodynamicist,
AeroRocket and WarpMetrics 

Nozzle 3.7
Example: External shock pattern for an
overexpanded SSME rocket nozzle.
Nozzle 3.7
is a onedimensional isentropic with crosssectional area variation,
compressible flow computer program for the analysis of convergingdiverging
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.
The convergingdiverging nozzle
featured in the new AeroRocket supersonic blowdown wind tunnel
was designed
using
Nozzle 3.7 applying the concept of a normal shock
diffuser. Finally, use
AeroRocketCAD to generate Nozzle 3.7 and
AeroCFD shapes
from AutoCAD
DXF geometry.
More ...
AeroCFD 5.2 Example: The Masten Space
Systems XA1.0
vertical takeoff rocket has been modeled using AeroCFD 5.2.
AeroCFD
is a "true" threedimensional axisymmetric and twodimensional 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
(3D) or thickness (2D) direction. The latest version of AeroCFD has
increased the number of finitevolumes available for analysis from
18,000 cells to 50,000 cells without increasing run time. Due to its "true" 3dimensional
formulation, AeroCFD provides nonzero lift and nonzero pitching moment for axisymmetric shapes at angle of attack. 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.
See how to easily perform
high power rocket
CFD's and generate
multiple fin sets using
AeroCFD. See the new
AeroCFD demo which illustrates how simple it is to plot flow
fields, determine Cd and Xcp using AeroCFD.
SUPERSONIC BLOWDOWN WIND
TUNNEL
(1" DIAMETER)
A new
supersonic blowdown wind tunnel is available for testing
aerodynamic shapes. The new 1" insidediameter supersonic blowdown
wind tunnel, having a test section blockage factor
less than 3%, now joins the successful 1/2"
supersonic wind tunnel.
The AeroRocket 1" diameter supersonic
blowdown wind tunnel performs
drag measurements up to Mach 3.
In addition,
AeroRocket's expertise in the fabrication
of miniature wind tunnel models makes possible the measurement
of supersonic drag coefficient for designs ranging from
simple high power rockets to the very complex HTV3X and X30
NASP.
Mach number
verses time is measured during the blowdown process
using a pitotstatic pressure probe for measuring total
pressure (Po) and static pressure (Ps) of a compressible
fluid in this case air. Click here
to view a QuickTime movie of a 2.5 second segment
of a typical blowdown wind tunnel test using the 1"
diameter supersonic wind tunnel where nearly
constant Mach 1.6 flow is maintained for approximately
2.5 seconds, an eternity compared to typical shock tube
performance.
StarShip
VASIMR Analysis:
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.
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. Also,
perform a Variable Specific Impulse Magnetoplasma
Rocket (VASIMR) analysis or a standard constant specific impulse analysis (nuclear propulsion) by specifying starting exhaust velocity and ending
exhaust velocity or constant exhaust velocity for
heliocentric flight to planets and stars.
