**Program Airloads-V4 :**

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 :

- Steady and unsteady , translational / rotational / flapping
- 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

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