WINGS 2.11 is composed by 18 softwares organised around 4 groups PROFIL, AILE,FUSELAGE, ACCESSOIRESto which is added a library of data deals with 1220 profiles of wing and 107 polar of wing sections .
The various files calculated with this software
and corresponding to the profiles, ribs, frameworks, fuselage sections, can
be recorded in DXF format then to be imported in a vectorial software
like AutoSketch, AutoCad, VeCAD... The printing of the various drawings
can be carried out on a printer (A4 sheetbysheet or listing) and on plotter
until the A0 format.
Donwload the drawings of ribs
and sections of a fuselage in DXF format computed
by Wings
WINGS 2.1 is delivered to its purchasers ( 115 Euros including post fees) in the form of a CD Rom and a user guide of 80 pages in the A4 format (in french) . The software (stored in compressed form) and the data files of the library of profiles are recorded on the same CD Rom. The use of the software is described in different papers published in french magazines for modelers
A documentation on the specifications of WINGS 2.11 (in french) can be downloaded in pdf format and read with the free software Acrobat Reader
The PROFIL group is
devoted to calculate, draw, print out, import and modify the wing sections.
6 calculators make it possible to obtain the coordinates and to trace the
wing sections from the series 16, 16 modified, 4, 4 modified, 5 and 6. A
software is available to carry out the importation of the profiles stored
in the library of data, to draw them on the screen and to print them with
required dimensions. A specific editor permits to introduce the coordinates
of a profile which would not exist in the library
For example, with the calculator NACA series 4 (represented on the example above), it is enough to calculate and visualize wing section 4412 . The characteristic 4412 is introduced into the corresponding boxes : 4% for the value of the maximum camber, 40%/10=4 for the position along the chord of maximum camber and 12% for the relative thickness. 
The wing section calculated previously is thinned here from 12% to 8% whole while preserving the curve of the mean line. Its relative thickness can be also modified overall or one can calculate the profile of a rib inclined compared to the plan of the wing (break of dihedral or rib at root). 
The WING group is devoted
Example of calculation of a trapezoidal wing whose profile evolves along the wingspan and who undergoes a negative twist angle. This configuration makes it possible to obtain, with a simple geometry, a wing with good aerodynamic properties presenting an quasielliptic distribution of pressure what limits the appearance of vortices generating induced drag, improves stability , increases the aileron efficiency at low speed and decreases the secondary effects. 


The goupe FUSELAGE makes it possible to calculate:
From the measures taken on the side view and the top view, one can generate the various sections of a fuselage composed of archs of ellipses 
Another method of creating a fuselage is to draw, using a specific graphic editor, the nose section, the master section and the rear section. The software calculates the intermediate sections then 
Once the sections created, one can visualize in 3D the feature of the fuselage with adjustable angles of sight from 0° to 360° 
Each section can be transformed in former by adding to its drawing the thickness of the coversheet, stringers, a central scrap and a separation in halfformers. It is also possible to compute the negative trace of the section to carry out a framework 
Calculation of polar diagrams according to the profile polar and the characteristics of the plane 
Calculation of the diagram of stability of the plane 
Calculation of the wing area, the wing loading, the average chord and its position along the wingspan. Calculation according to the characteristics of the profile of wing of the position of the center of gravity 
Calculation, according to the mass and to the position of the devices, of the variation between the effective and optimum positions of the center of gravity 
Calculation of the performances of the plane (take off , cruising speed) 
Calculation of the power and the cylinder capacity of the engine for the propulsion of the plane according to the categories of flight and the nature of the engine 
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