NOTE-1: Emetrix is a 100% secure web site for purchasing AeroRocket softeware using all major credit cards. Only Emetrix, the payment provider, handles your credit card information. Once a credit card order is accepted by Emetrix it normally takes only a few minutes for the purchaser to receive an email from sales@emetrix.com containing the software download link and instructions. In addition to the download, delivery on CD ROM may be selected for an additional $9.95. Also, a significant cost reduction (50%) is available for purchases of four or more items.

NOTE-2: For people who do not wish to use their credit cards to make online purchases Emetrix will accept credit card orders by telephone. To order AeroRocket software by telephone or to report problems regarding online purchases, Emetrix customer support may be reached Toll Free at: 888-447-1175 or for international orders at: 952-646-5558. Please contact AeroRocket if ordering problems persist.

NOTE-3: 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 user may need to specify period (.) usage by clicking Date, Time, Language and Regional Options then Regional and Language Options and finally selecting English (United States) in the Control Panel. If periods are not used in all inputs the results will not be correct.

NOTE-4: To install AeroRocket software the user needs WinZip, the original and most popular compression utility for Windows ... Please click for more information. More notes below.

AeroWindTunnel 6.0 ($100.00 US) New!
Airplane Flight Dynamics & Stability Analysis
for Gliding and Powered Flight
Detailed Information
Buy On-Line
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 wing-body 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 slider-bar control to define airplane geometry instead of time-consuming CAD geometry definitions. AeroWindTunnel has been validated from 0.3 Mach to 3.5 Mach using the AeroRocket wind tunnel and other online sources.


VisualCFD 3.5 ($200.00 US) New Version!
Finite Volume CFD Analysis Program
Detailed Information & Instructions
Buy On-Line

VisualCFD is a powerful new CFD computer program. VisualCFD is a 3-D axisymmetric and 2-D plane finite-volume numerical analysis program that rapidly solves the steady and unsteady inviscid Euler equations for subsonic, transonic, and supersonic flow. Easily generate flow fields using automatic grid generation and mesh distribution. The program provides a maximum of 60 cells in the axial direction (X), 30 cells in the transverse direction (Y) and 10 cells in the circumferential (3-D) or thickness (2-D) direction (Z). Flow is easily visualized using filled-contour plots, line-contour plots and surface distribution plots for Cp, pressure, temperature, Mach number and density. New features include surface contour plots and the ability to edit contour plot color level distribution. All output may be sent directly to a color printer. Now, import airframe shapes having up to 1,000 X-Y points for generation of more complex axisymmetric designs.


AeroEuler 2.0 ($115.00 US)
Space-Marching CFD Training Code
Detailed Information
Buy On-Line

AeroEuler is a new CFD training code designed for the analysis of two-dimensional and axisymmetric supersonic flow using the MacCormack space-marching method and the analysis of three-dimensional subsonic flow using panel methods. This new CFD program solves supersonic flow in seconds by marching the solution downstream using the MacCormack forward-predictor, backward-corrector method. A complete derivation of the equations, discussion of the theory and program listing will be provided in the report, EulerCode.pdf. The 16-page 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.


AeroCFD 7.0 ($90.00 US) New Version!
Model Rocket CFD Analysis Program
Detailed Information
Buy On-Line

AeroCFD is a model rocket Computational Fluid Dynamics (CFD) computer program. AeroCFD uses vortex panel and source panel methods to solve the frictionless potential flow equations and employs linearized theory to approximate compressible flow up to Mach 0.80. A complete set of graphical tools such as velocity and pressure color contour plots are provided to allow the user to visualize 3D flow around the rocket. This new version includes AeroCFD 2D-WING for the aerodynamic analysis of wing sections using 2D vortex (lift) panels.


AeroSpike 2.5 ($50.00 US) New Version!
Minimum Length Nozzle Design &
AeroSpike Nozzle Design Program
Detailed Information
Buy On-Line

AeroSpike performs 2-D and 3-D Minimum Length Nozzle (MLN) design using the method of characteristics. In addition, for annular and linear aerospike nozzle designs AeroSpike performs an expansion-wave 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 semi-log scale as well as generating color contour plots of Mn, P/Pc, T/Tc and R/Rc.


Nozzle 3.6 ($40.00 US) New Version!
Converging-Diverging Nozzle Analysis
Detailed Information
Nozzle Validation Analysis
Buy On-Line

Nozzle is a one-dimensional compressible flow computer program for the analysis of converging-diverging 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 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.

AeroIsp 3.0 ($40.00 US) New Version!
Solid Rocket Motor Design Program
Detailed Information
Buy On-Line

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 curve-fit determination of burn rate coefficient and burn rate exponent.


AeroDRAG & Flight Simulation ($35.00 US) New Version!
Aerodynamic Drag Prediction and Flight Performance Analysis
Detailed Information
Buy On-Line

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 nose-body 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 ring-fin and tube-fin stabilized rockets along with many other new features. Now, AeroDRAG & Flight Simulation models the two-dimensional flight path of rockets that fly in the proximity of the gravitational field of the Earth.


AeroCP 4.0 ($15.00 US) New Version!
Center of Pressure (XCp) Analysis
Detailed Information
Buy On-Line

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.


HyperCFD ($150.00 US)
Supersonic CFD Analysis Program
Detailed Information
Buy On-Line

HyperCFD Determines drag coefficient (Cd), center of pressure (Xcp) and CN-alpha of supersonic and hypersonic rockets and re-entry 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 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.


AeroFinSim 4.0 ($35.00 US) New Version!
Fin Structural Analysis Program
Now, Includes Spin Stabilization and
the Theodorsen and U-g Flutter Methods
Detailed Information
Buy On-Line

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. NEW! added the ability to model unsteady torsion-flexure wing oscillations for determining flutter and divergence velocity using either the Theodorsen method or the U-g method.


Wind Tunnel Testing ($25.00/Hour US)
AeroRocket Subsonic Wind Tunnel
Detailed Information
AeroRocket Mail Order

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 two-component force measurement system. The wind tunnel at AeroRocket's disposal was developed in-house 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.


Wind Tunnel Course ($50.00 US)
How to use the AeroRocket Subsonic Wind Tunnel
Detailed Information
Buy On-Line

WindTunnelCourse shows step-by-step 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.


StarTravel ($45.00 US) New!
Astrodynamics & Relativistic Flight
Detailed Information
Buy On-Line

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 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.


RMTS ($25.00 US)
Rocket Motor Test Stand
Detailed Information
Buy On-Line

The RMTS is capable of recording the thrust-time characteristics of rocket motors generating up to 220 pounds of maximum thrust. Overall test-bed dimensions for the RMTS are 19 5/8" long x 12" wide x 16 1/2" high. The RMTS design package is distributed in pfd format on CD ROM or by download. Requires Adobe Acrobat Reader.



Spool Rocket Report ($25.00 US)
Detailed Information
Buy On-Line

The AeroRocket wind tunnel has been used to determine center of pressure location (XCp) and zero-degree drag coefficient (Cd) of spool rocket models having various plate-separation to plate-diameter ratios (L/D). Five spool rocket wind tunnel models were tested having L/D ratios of 1, 1.33, 1.67, 2 and 3. The Spool Rocket Report is distributed in pfd format on CD ROM or by download. Requires Adobe Acrobat Reader.

NOTE-5: Recent tests show all AeroRocket programs are fully compatible with Microsoft's new Windows Vista operating system in addition to Windows XP, etc.

NOTE-6: To view the Spool Rocket Report, RMTS Detailed Plans and selected software instructions please use Adobe Acrobat Reader. Free download using the following link.


IMPORTANT NOTE: WHEN PURCHASING AEROROCKET SOFTWARE THE USER IS AGREEING THE SOFTWARE IS SOLD AS IS AND NO WARRANTY IS EXPRESSED OR IMPLIED. THE USER TAKES COMPLETE RESPONSIBILITY FOR USING THE SOFTWARE AND PROPERLY INTERPRETING THE RESULTS. IN ADDITION, ALL AEROROCKET PROGRAMS ARE FOR INDIVIDUAL USE ONLY AND WHILE MAKING BACKUP COPIES IS ALLOWED, AEROROCKET PROGRAMS MAY NOT BE COPIED OR DISTRIBUTED OR DONATED TO ANYONE ELSE. FOR MULTI-LICENSE (MULTI-USER) PURCHASES PLEASE CONTACT AEROROCKET FOR SPECIAL REDUCED PRICING