 An Object Oriented Symbolic Algorithm For Aero/Hydrodynamic Design And Simulation

Program Abilities :

1- Two Dimensional Geometry Package :

• Calculates ordinates for the following :
• NACA symm/cambered one series
• NACA symm/cambered four series with standard/modified thickness
• NACA five series with standard/modified thickness
• NACA reflexed five series with standard/modified thickness
• NACA symm/cambered six series with standard/modified mean line
• Joukowski airfoils
• Von-Karman Trefftz airfoils
• Variable axis elliptical sections
• Built-in library of 1490 different airfoil
• Automatic paneling with four different schemes
• Uniform spacing
• Full cosine
• Half cosine
• Half sine
• Ability to invert any airfoil up-side-down
• Option to write a geometry file

2- Two Dimensional Solvers :

• Using Four Different Analytical/numerical aerodynamic methods to solve the inviscid compressible/incompressible potential flow about two dimensional lifting and non-lifting surfaces , for pure non-lifting panel method please refer to Constant Source Panel Method
• Thin Airfoil Theory , concentrated trigonometric distribution of vortices along the camber line
• Lumped Vortex panel method , concentrated lumped distribution of vortices at the quarter chord of each panel assembling the camber line
• Constant Source + Constant Vortex Panel Method , surface distribution of constant sources and constant vortices at each panel assembling the surface , the sources are different for each panel but the vortex is the same
• Linear Vortex Panel Method , surface distribution of linearly varying vortices distributed over each panel assembling the surface
• The package calculates dimensionless lift , momet about leading edge , moment about quarter chord , Also the center of pressure location and the zero lift angle of attack
• Plots the variation of the dimensionless lift and moments with the angle of attack
• Option to write a geometry/results file

3- Three Dimensional Geometry Package :

• The 3D Geometry Package calculates ordinates for any number of non lifting bodies using the following methods :
• Frame by frame method
• Rotate two different parametric numeric or symbolic curves in space to generate a body of revolution . Two curves to generate the upper and lower parts separately
• Option to change any point on any frame at any body
• The 3D Geometry Package reads symbolic equations and numeric numbers
• No restriction for the number of panels nor the spacing scheme as the package curve fits and surface fits all the surfaces
• The 3D Geometry Package uses the lofting method to construct lifting surfaces with any cross-section you want , with Any number of wings , any number of partitions for each wing
• Each wing may have different twist pivot
• Each partition on each wing may have different sweep pivot , sweep angle , twist and dihedral angles
• Each partition may have any airfoil family on the same wing
• Leading and trailing edge control surface for any partition at any wing
• Ability to change any local axes in the main global axes
• Different options for paneling location for lifting surfaces :
• Around the actual surface
• On the mean cambered surface
• At the chord plane
• Trailing vortices extend from each bound vortex :
• To a distance downstream
• To the panel trailing edge , then to a distance downstream
• To the panel trailing edge then to the partition trailing edge , and finally to a distance downstream
• Trailing vortices extension :
• Parallel to the x-axis
• Parallel to the free-stream
• The package automatically calculates the Mean aerodynamic chord length and position with the center of gravity and inertia tensor for the complete model
• Center of gravity location depends on area/ mass distribution
• Option to export your model to :
• Ansys 3d curves files .dat
• Datcom+ input files .dcm
• Matlab .m files
• Matlab binary files .mat
• Unigraphics spline files .dat
• Virtual reality model file .wrl
• VLAERO input file .vlp

4- Three Dimensional Solver :

• Using an advanced Vortex Lattice Method to solve the potential flow about lifting and non lifting surfaces , with the following options :
• Compressible and incompressible flow fields
• Subsonic and supersonic flight speeds
• Using the default trailing wakes , the Solver Package can calculate the roll-up trailing wakes using the wake relaxation techniques
• The 3D Solver Package calculates aerodynamic forces , moments , distributed loads , static and dynamic stability and control derivatives in eight different fluids
• Detailed solution for each panel with sectional airloads calculations
• Easy to find the aerodynamic center and to estimate the static margin with the zero lift angle of attack
• Solving the leading edge suction/thrust forces for sharp-edge delta wings at high angles of attack , using the leading edge suction analogy
• Horizontal and vertical tail sizing , for longitudinal and directional stability in subsonic and supersonic speeds
• Geometry variation module for geometry optimization

5- Dynamics Simulation Package :

• The Solver Package runs only one time to estimate the aerodynamic coefficients and the stability and control derivatives , while the aerodynamic model calculates new resultant forces and moments at each time step during the simulation
• Atmospheric model
• International standard atmosphere , up to 25 km altitude
• Mathematical implementation of the 1976 committee on extension to the standard atmosphere COESA , up to 32 kilometer altitude
• Military handbook MIL-HDBK-310 , non standard day climatic data up to 80 km altitude
• Military standards MIL-STD-210C , non standard day climatic data up to 80 km altitude
• Wind model
• Military specifications MIL-F-8785c for Discrete wind gust model
• Military specifications MIL-F-8785c for Discrete wind shear model
• NASA dryden discrete/continuous wind turbulence model with dryden velocity spectra
• Continuous wind turbulence with Von-Karman velocity spectra
• Gravity model implementation of the geocentric equipotential ellipsoid of the world geodetic system WGS84
• Exact
• Taylor series
• Close approximation
• Engine model , in progress
• Higher order Integrators to solve the six degrees ordinary differential equations of motion for a variable mass rigid body
• Motion animation using simple graphs/virtual reality world
• Easy to display any output data for your complete motion envelop
• Ability to use a Joystick to control your motion
• Flight control system , in progress

6- Tricks and Tweaks :

• Options for instant geometry building and/or instant airloads calculations
• Save / load / modify / add / subtract / rescale /reposition any geometry
• Default values with full description for any input data
• Ability to change the reference geometry / mass distribution / inertia
• Write results file to any file extension you want
• Ability to calculate atmospheric pressure / temperature / density / speed of sound at altitudes up to 80 kilometers
• External physical units converter added with a scientific math calculator and an inertia calculator
• Fixed/autohide input panels
• Easy to change any :
• Input panel color
• Font color
• Figure color
• Pressure color map
• Wireframe color
• Body color
• High light color
• Line color
• Line width
• Line marker
• Keyboard short-cuts for the most of the program functions
• Resize the program window and check buttons by hovering your mouse or just scroll its wheel
• The program can say out loud specific results
• Some voice command features , to talk to the program , in progress

The program is a one man project started at 2008

• First version 2008
• Second version 2009
• Third version 2010
• Fourth version 2012
• Fifth version 2014                      More Wallpapers Here

Copy Rights 1094 And 1094-01 2009©
All Equations / Matlab / C / C++ / Fortran Codes And Web Design Made By [email protected]