Supersonic Vortex Lattice Method

Program Airloads-V5:

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

Geometry variation module for geometry optimization

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 :

Translational / rotational / flapping motion

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

Dynamic stability analysis using coupled inertial moments for state space free response with step and impulsive response along the three axes

Damping system to damp your free and forced pitch , roll and yaw

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

Solver variation module for different attitudes

Aeroelastic module using Matlab FEA toolbox

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

Inertia tensor and center of gravity calculator

External physical units converter

Scientific math 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