.: code Airfoil Smooth -- Smoothing of airfoil geometry, version 3.0 (07.02.2020)

Applies smoothing to airfoil coordinates within given band.

.: code Airfoil Editor -- The editor of airfoil geometry

Allows modification of the reference profile geometry while controlling change in pressure distribution for given flow parameters (Mach, Re, Alpha).

.: code Cp Editor 3D -- The editor of pressure distribution on the wing for inverse problem

This program is an example of building a graphical user interface using FOX toolkit library and OpenGL.

.: code Cp Editor 2D -- The editor of pressure distribution on airfoil for inverse problem

This program is an example of building a graphical user interface using FOX toolkit library and OpenGL. This code is usefull if you have code of solving of airfoil inverse problem

.: code RefValues -- Flight parameters and boundary layer parameters (standard atmosphere)

Calculates main flight parameters based on given values of Mach and Reynolds numbers, using International Standard Atmosphere (ISA) model. Estimates parameters of the grid points distribution (geometric progression coefficient and number of nodes) in turbulent boundary layer for given X/Lref and Yplus values. Evaluates parameters of turbulent boundary layer on a plate: displacement thickness Dstar, thickness D and friction coefficient Cf turb (X / Lref).

.: code Clift(N) -- Flight parameters (standard atmosphere)

Calculates basic flight parameters on the basis of a standard atmosphere (ISA).

.: code Panel_2D -- Multi-element airfoil

Calculates by panel method the integral aerodynamic parameters and the pressure distribution on multi-element airfoil.
In version 2.0 the boundary layer calculation included
Updating 27.02.2019 - version 2.1.

.: code InfSWing -- Infinite swept wing

Calculates the distributed and integral characteristics of subsonic or transonic flow around an infinite swept wing at given Mach number, angle of attack, and sweep angle, including the solving of an inverse problem.. The flow is calculated by numerical integration of the conservative form of the full potential equation with correction for non-isentropic conditions in the vicinity of shocks. The solving of an inverse problem defines geometry of the airfoil of an infinite swept wing by corrected the pressure distribution.
Beta - версия 2.0.

.: code JoukowskiAF_BL -- Joukowski Airfoil

Calculates geometry and pressure distribution on Joukowski airfoil with specified thikness and camber.
Calculates boundary layer parameters on the upper and lower surfaces of the airfoil.
The code can be useful for the education purposes.
Updating 22.02.2019 - version 2.1.

.: FOX toolkit -- Library for building Graphical User Interfaces

Project file for compilation of FOX toolkit library using CodeBlocks and MinGW and the example of building GUI for RefValues code using FOX toolkit library.