**
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**. |