Software > AeroCFD 7.0

AeroCFD is a computer program written using Microsoft Visual Basic 6. AeroCFD is interactive allowing the rocketeer to quickly and easily perform CFD design studies using the power of the Windows Graphical User Interface. AeroCFD uses vortex and source panel methods to solve the frictionless potential flow equations and employs linearized theory to compute compressible flow up to Mach 0.80. Meshing the flow field is very simple with AeroCFD. The user simply inputs model rocket geometry such as nose cone type, nose cone length and body tube diameter. Then, AeroCFD automatically meshes the computational domain, as it is called, with thousands of panels that break the flow field into discrete elements for use by the 2nd order vortex and source panel methods. Then, once the results are computed AeroCFD provides the rocketeer with a complete set of visualization tools to make interpretation of the complex flow field results simple. For example, color velocity and pressure contour plots allow the rocketeer to quickly and easily visualize complex flow around the model rocket. In addition, a simple and efficient fin geometry utility allows the rocketeer to quickly specify fin and launch lug dimensions. Then, using source and vortex panel methods the rocketeer can determine contribution of the fins to overall center of pressure and the effects of fin geometry on overall rocket stability, drag and lift. The vortex panel analysis for fins and body is a real break through for model rocket design and the visualization of the rocket's flow field is a unique feature not available anywhere else but in AeroCFD. AeroCFD is able to more accurately determine FOREBODY and BASE drag coefficients than the DATCOM methods used by various Rocket Simulation programs which translates into more reliable and accurate flight predictions.

AeroCFD 7 includes a completely new routine called 2D-WING for the determination of wing section aerodynamics. 2D-WING determines drag coefficient (CD), lift coefficient (CL) and moment coefficient (Cm,c/4) of airfoil sections using the NACA four digit series, Streamlined, Flat Plate, D'Wedge and Imported shapes for a wide range of fin/wing shapes. Presently, several five-digit series airfoil shapes from Theory of Wing Sections, Appendix III have been provided in the file, NACA_AIRFOILS.zip to allow the user to specify more complex airfoil shapes. Over the next several months the entire contents Theory of Wing Sections, Appendix III will be included. For those who purchase AeroCFD 7 the final version of NACA_AIRFOILS.zip will be emailed upon completion.

Updated: October 4, 2007