1) FREE AEROROCKET SOFTWARE: AeroRocket's extensive collection of aerodynamics, model rocketry and high power rocketry software will be provided FREE to deserving students, schools or very qualified independent researchers on the basis of a simple online application. Please limit the number of requested software titles to one or two programs per month per online application. Applicants are encouraged to apply the following month if their software request is not accepted. A detailed project description and a reference to a valid web site will greatly enhance the probability of acceptance into this unique program. In addition, free software will only be provided to students, schools or independent researchers that will not pirate AeroRocket software and are not on the Sales Banned List. This offer is only valid by clicking online application. Emailed requests for free software will be ignored. To download the software a username and password will be emailed after the application for free software is accepted by John Cipolla. See the updated list of qualified recipients of no-cost AeroRocket software.

2) FREE UPGRADES: A benefit of AeroRocket's policy is that all upgrades for purchases made after 5/01/2012 are FREE.

3) BACK UP SOFTWARE PROTECTION: Back up software protection is FREE of charge so no need to worry about system crashes or hard disk errors ever again. Simply provide name and date purchased so AeroRocket can email the installation file. This unlimited backup feature applies to the original version of your software for the original purchaser.

4) SOFTWARE LICENSE: By downloading software the user agrees to comply with the Software License agreement.
 

NOTE-1: Software Installation: Download the .zip file and copy to the desktop. Then, double-click 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 right-click 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 NOTE-3, below.

NOTE-2: 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.
 

AeroWindTunnel 6.0 (2.7MB) New TOP
Airplane Flight Dynamics & Stability Analysis for Gliding and Powered Flight
Detailed Information

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. 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.


AeroEuler 2.0 (3.4MB) TOP
Space-Marching CFD Training Code
Detailed Information

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 (3.0MB) TOP
Model Rocket CFD Analysis Program
Detailed Information

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 2.6 (4.8MB) TOP
Minimum Length Nozzle Design & AeroSpike Nozzle Design Program
Detailed Information

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. 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

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 (2.8MB) TOP
Aerodynamic Drag Prediction and Flight Performance Analysis
Detailed Information

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 (2.6MB) TOP
Center of Pressure (XCp) Analysis
Detailed Information

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 U-g Flutter Methods
Detailed Information

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 torsion-flexure wing oscillations for determining flutter and divergence velocity using either the Theodorsen method or the U-g method.


HyperCFD (2.5MB) TOP
Supersonic CFD Analysis Program
Detailed Information

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.


Nozzle 3.7 (4.9MB) TOP
Converging-Diverging Nozzle Analysis
Detailed Information

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.


StarTravel (3.7MB) New TOP
Astrodynamics & Relativistic Flight
Detailed Information

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. 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.


VisualCFD 4.1 (2.7MB) TOP
Finite Volume CFD Analysis Program
Detailed Information

VisualCFD is a "true" three-dimensional axisymmetric and two-dimensional CFD program that solves the inviscid Euler equations for subsonic, transonic and supersonic flow using automatic mesh generation and graphical results visualization. VisualCFD 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 thickness (2-D) direction. The latest version of VisualCFD 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, VisualCFD 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 VisualCFD 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. 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. 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.


Wind Tunnel Course (4MB) TOP
How to use the AeroRocket Subsonic Wind Tunnel
Detailed Information

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.


Wind Tunnel Testing $75.00/Hour TOP
AeroRocket Subsonic Wind Tunnel Testing
Detailed Information Contact by 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 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.

MORE NOTES:
NOTE-3: To install AeroRocket software the user requires WinZip, the original and most popular compression utility for Windows ... Please click for more information.

NOTE-4: All AeroRocket programs are fully compatible with Windows Vista, Windows 7 and Windows XP, etc.

NOTE-5: 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 (EFFECTIVE 5/01/2013): WHEN DOWNLOADING AEROROCKET SOFTWARE THE USER IS AGREEING THE SOFTWARE IS PRESENTED AS-IS 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 MULTI-LICENSE USE ON AS MANY COMPUTERS THAT ARE AVAILABLE TO THE USER. 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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