AeroCFD 7.0 New
Copyright 1999-2022 John Cipolla/AeroRocket


Typical AeroCFD contour plot

AeroCFD is a "true" three-dimensional axisymmetric and two-dimensional implicit finite volume 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 (3-D) or thickness (2-D) direction. The latest version of AeroCFD 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, AeroCFD 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 AeroCFD 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. The RESULTS section clearly displays FX, FY, MZ, CX, CY, CM, CD, CL, base drag, surface friction drag and center of pressure location. 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. All output can be sent directly to a color printer. See how to easily generate single and multiple fin sets using AeroCFD.

AeroCFD allows the user to control the mesh distribution around a body using simple point-and-click operations and are explained in simple step-by-step Operating Instructions. Model geometry is easily defined by selecting from a number of standard shapes that are automatically combined into one final shape with fins. In addition, transition shapes have a power series shape control for defining very unusual three-dimensional axisymmetric and two-dimensional shapes. In addition, a free-form fin utility allows the user to attach complex fins having several definition points to the final CFD airframe. Fin effects are superimposed on the final CFD solution using classical mechanics and are not part of the mesh definition. Using this methodology relatively thick fins having complex geometry are modeled efficiently for subsonic, supersonic and hypersonic flow.

AeroCFD uses a very efficient 3-D numerical analysis technique to solve the Euler equations for 1st, 2nd or 3rd order accuracy. An implicit finite volume numerical scheme uses upwind differencing methods that are biased in the direction determined by the signs of the characteristic speeds. Specifically, Steger-Warming flux-vector-splitting and Roe flux-difference-splitting methods are used for accurate solutions in shock-wave dominated flows. Shock waves are captured in as few as zero to one cell using the Roe flux-difference splitting methods. Subsonic flows use standard finite volume differencing methods. Engineering solutions are achieved in approximately 5 to 10 minutes using the default numerical settings for most models after a "good" mesh is developed. AeroCFD development started around 2002 using numerical algorithms described by the following AIAA research paper, "Three-Dimensional Unsteady Euler Equations Solution Using Flux Vector Splitting", AIAA-84-1552.