3-D finite wing in incompressible
and steady potential air flow
By
Edition 1.1 August 1999
This is edition 1.1 of the AeroWing documentation, and it concerns the AeroWing program version 1.10. Both the program and the documentation were written by Christophe Paget. Acknowledgement is given to Jérôme Matrat who provided the finite element code in this program.
The original was distributed by Christophe Paget < ptc@ffa.se > June 15th 1999.
Edition 1.1 was made by Christophe Paget < aerowing@engineer.com
> on August 27th 1999 by restricting capabilities of the program
due to finite element code limitations.
This documentation can be found at the following World Wide Web addresses:
http://go.to/aerowing or http://fly.to/aerowing or http://get.to/aerowing
http://www.oocities.org/Tokyo/Club/7077/ or even
http://tv.acmecity.com/parody/99/
This file may be copied and distributed in accordance with the usual
copying permissions of the Free
Software Foundation. These permissions are given in the General Public
License section of the "GNU Manuel".
This software comes with NO WARRANTY.
Permission is granted to make and distribute verbatim copies of this manual provided the copyright notice and this permission notice are preserved on all copies.
Permission is granted to copy and distribute modified versions of this
manual under the conditions for verbatim copying, provided that the entire
resulting derived work is distributed under the terms of a permission notice
identical to this one.
Table of Contents
Introduction *
Chapter 1 Getting started *
1.2. Set-up the program *
2.2. "Wing Property" window *
2.3. "Composite Stacking" window *
2.4. "Free Hand Stacking Sequence" window *
2.5. "Database Stacking Sequence" window *
Chapter 4 examples *
Appendix A: what is WHAT in the program? *
Appendix B: references *
AeroWing© is a program concerning 3-D finite wing in an incompressible, non-rotational and steady potential flow. This program contains the basis of aeroelasticity, meaning that it calculates the aerodynamic pressure distribution on the wing and computes the displacement field of the 3-D wing due to loading. The program was written from an educational point of view using fully graphic user interfaces. The authors of the program welcome any new routines that could improve the use of this free-based licensed program. The novelty of this program is that it handles finite wing made of two composite skins. The users can also set-up the composite lay-up sequences.
The AeroWing© program is in fact a library of Matlab, therefore it needs the MATLAB program for running. In any case AeroWing belongs to MATLAB© from MathWorks.
AeroWing© was written at the very beginning in PC platform and was extended to Unix and Unix-like platforms. Besides, the program is compliant with Matlab versions 4.xx and 5.xx. However, the program takes care of the platform type (PC, Unix or Unix-like platform) and Matlab version by itself.
The MAC version of the program will be available in the next version
of AeroWing.
1.1. How to download the program
The free program AeroWing© can be downloaded from the following web sites:
http://go.to/aerowing or http://fly.to/aerowing
or http://www.oocities.org/Tokyo/Club/7077/
or even http://tv.acmecity.com/parody/99/
A copy can be sent for free on request at one of the following Emails:
aerowing@engineer.com
or ptc@ffa.se
Matlab 4 users
For users running the program on matlab version 4, the administrator needs to store the whole folder content "aerowf" at the location "~\matlab\toolbox\matlab\". It remains to the administrator to set the matlab path. For this, at the location "~\matlab\", the administrator has to write the path for the folder "aerowf" in the file named " matlabrc.m.
If the program is used by several users, make sure that all files can be accessed by all users by setting the full rights on all files (in writing, reading and executing modes), otherwise the program will not work.
To run the program, start the program Matlab first, then write the program
name aerowing. Then, follow the help menus provided in each
window.
Matlab 5 users
For users running the program on matlab version 5, the administrator needs to store the whole folder content "aerowf" at the location of the administrator?s choice (typically at "~\matlab\toolbox\matlab\". It remains to the administrator to set the matlab path. For this, the file named "aerowing.m" (located originally at "~\aerowf\aerowing.m") has to be moved to any location the administrator?s wish.
If the program is used by several users, make sure that all files can be accessed by all users by setting the full rights on all files (in writing, reading and executing modes), otherwise the program will not work.
To run the program, start the program Matlab first, then go the directory
where the file "aerowing.m" is and write the program name aerowing.
Then follow the help menus provided in each window.
The program will start with the main window as shown in Figure 1.
Figure 1: Main window of AeroWing©
On the right hand side of this main window, one can see the main menu. It includes the "Wing design" popup menu, the "Angle of attack" slider, the "Mach number" slider, the "Run" button, the "Summary file" button, the "Help" button and the "Close" button.
The "Wing design" popup menu gives the user two choices:
The "Angle of attack" slider allows the user to select
an angle of attack using the mouse, dragging the slider. The user might
also write the angle of attack by hand, using the edit window to
the right of "Attack Angle", with a red number. Note that
the angle of attack is here expected in degree. It is also important to
write a numerical value and not any other letters (such as 0 instead of
O).
The "Mach number" slider allows the user to select the
velocity of the simulated aircraft wing by using the mouse, dragging the
slider. The user might also write the Mach number by hand, using the edit
window to the right of "Mach number", with a red number.
Note that the Mach number is obviously expected in Mach, depending on the
altitude. It is also important to write a numerical value and not any other
letters (such as 0 instead of O).
The "Altitude" slider allows the user to select the altitude
of the simulated aircraft wing by using the mouse, dragging the slider.
The user might also write the altitude by hand, using the edit window
to the right of "Altitude", with a red number. Note that
the altitude is expected in kilometre. It is also important to write a
numerical value and not any other letters (such as 0 instead of O).
Once the angle of attack, the velocity and the altitude are set, the
user might start running the program by clicking on the "Run AeroWing"
button with the mouse. A window will then appear (Figure 2) to ask the
user to give the wished name for the result file. At the same time the
user will give the path where the file will be stored.
Figure 2: Save window for the calculation results
Once the file name and location has been defined, the program will start to calculate the aerodynamic pressure difference distribution using the "Lifting-surface solution by vortex ring element" method [1]. The pressure difference will then be applied on the wing top-element surfaces of the wing mesh, and the displacement and "loads" will be calculated using the finite element method [2].
During the calculation the entire menu panel will freeze until the calculations
are completed.
The "Summary file" button will be valid when the calculation
will be completed. Clicking it will display the file containing a summary
of all needed information.
The "Help" button will open a window to give the user
some help to use this main window.
The "Close" button will close the window and bring the user back to the user?s original-directory.
The user must NOT close any window using the "close button" situated
on the top right, but only using the "close button" situated on the bottom
right.
"Magnification" button opens a window to give the user
the choice of the magnification for the calculated displacement, because
the displacement might often be a very small amplification.
"AeroWing©" button situated on the bottom
left of the main window will give the user more information about the free
license agreement that AeroWing© is subjected to.
When the "Change wing" command is selected, a new window "Wing Property" window will open, as shown in Figure 3. This window allows the user to entirely define the wing to be studied.
The user has to go through all buttons and popup menus to fully define
the wing to be studied: i.e. popup menus "Wing Type", "Material
Type", "Y-Splitting", "X-Splitting",
"NACA Airfoil" and the button "Save Settings",
"Refresh Window" as often as possible, and finally change
the coordinates of the main nodes of the wing if necessary.
Figure 3: "Wing Property" window
The popup menu "Wing Type" gives the user the choice of the wing shape, as shown in Figure 4.
Figure 4: Wing type popup menu
"1-part Wing" will give the user the hand on the four main node coordinates, situated to the top left, defining a wing in only one part. Only the data in red can be changed by the user.
"2-part Wing" will give the user the hand on the six main node coordinates, situated to the top left, defining a wing in two parts (named Part 1 at the wing root and Part 2 at the wing tip). Only the data in red can be changed by the user.
The remaining alternatives are given libraries, meaning the user cannot change the node coordinates, but only the airfoil profile.
Note that all data are in meters unless clearly specified in any window.
If the user desires to add more libraries, changes need to be done on
the Matlab files named "uif.m" and "visu3d.m"
only.
The popup menu "Material Type" gives the user the choice of the material type, as shown in Figure 5.
Figure 5: Material type popup menu
"Titanium", "Advanced Aluminium", "Carbon Steel" and "Monel" are homogeneous material. These material data could be found in the file with the extension ".sum", by clicking on the "Summary file" button in the main window. Besides, the wing will be entirely made of the selected material, which is not the case of the "Composite" case.
"Composite" is a material made of several layers that
can be orientated in several different directions. This material is considered
as orthotropic. Besides, the composite will be considered as two skins,
in the upper and lower side of the wing, while the inside of the wing will
be filled of advanced aluminium material. The composite characteristics
will be defined in other windows by selecting in "Material Type"
the option "Composite".
The popup menu "Y-Splitting" gives the user the choice of the number of elements in the chordwise direction between 1 and 10, as shown in Figure 6.
Figure 6: Y-Splitting popup menu
The popup menu "X-Splitting" gives the user the choice of the number of elements in the spanwise direction between 2 and 20. When the wing is defined in two parts, two popup menus will define the splitting such as "Part 1 X-Splitting" and "Part 2 X-Splitting".
Note that the more splitting the wing has, the longer the calculations will take.
As an example, the computing time* was evaluated for the
following extreme cases:
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(in s) |
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* Defined with a Unix station HP-Apollo-series 700
for one aeroelasticity iteration.
"NACA Airfoil" popup menu will allow the user to define the airfoil section between 3 different families:
As an example, the NACA modified 5-digits is shown in Figure 7.
Figure 7: NACA modified 5-digits window
In the wing definition, only the camber line was modelled. The wing
section was then modelled flat, with the airfoil maximum thickness for
the wing thickness. Besides, the chord line was assumed to be the same
as the zero-lift chord. AeroWing version 1.2
is then expected to take into account the thickness distribution and to
take into account the real chord line.
"Refresh Window" button will refresh the window, in case
some changes were not displayed in the present window. It is advised to
the user to refresh the window as often as possible.
"Save Settings" button will save all the settings of the
wing that the user has just defined under the user?s desired location,
under the user?s desired name, with the extension ".mat",
as shown in Figure 8.
Figure 8: "Save settings" window
The "Help" button will open a window to give the user some help to use this "Wing Property" window.
The "Back to AeroWing" button will close the window and bring the user back to the main window.
The user must NOT close any window using the "close button" situated
on the top right, but only using the "Back to AeroWing" button
situated on the bottom right.
2.3.
"Composite Stacking" window
When the "Composite" command is selected in the popup menu "Material Type", a new window "Composite Stacking" window will open, as show in Figure 9. This window allows the user to entirely define the composite skin of the wing.
Figure 9: Composite stacking window
This window allows the user to select the matrix and reinforcement types,
as well as the lay-up sequence. The reinforcement form includes only the
"unidirectional" option. Later versions of AeroWing will include new reinforcement
forms such as chopped fibre, weaving, non-crimp fabrics, knitting or mats.
For aerodynamicians, who do not know anything about composites, a brief summary follows.
Composite materials are one of the best innovations of recent decades. This material has a lot of advantages over other materials, such as 20% lower ratio weight/area than aluminium, stronger on privileged direction than advanced material used in aeronautics. The main disadvantages of the composites are time consumption, that is higher than for conventional alloy, the complexity of manufacturing, necessitating autoclave and skilled labour, and their weakness to low energy impacts.
However, the composites are made of several layers called ply stacked
one on top of the others. Each ply is made of a matrix, often epoxy in
aeronautics, which is reinforced by fibres, usually carbon or glass in
aeronautics. The fibres can have several forms such as unidirectional,
chopped fibres or fabrics. In aeronautics, the best quality and strength
are expected, therefore only unidirectional fibre will be used, so far.
Besides, each ply can be orientated differently to each other creating
a lay-up (or stacking) sequence. The lay-up is the key of the whole composite
structure, and will be the most difficult part of the composite wing to
choose. Aircraft manufacturers usually hide the lay-up sequence they use
in the composite structure, for reasons of competition.
After this small introduction on composites, only four parameters need to be defined by the user, the "Matrix", "Reinforcement type", "Reinforcement form" and "Lay-up sequence".
"Matrix" popup menu gives the user the libraries of available matrix type, as shown in Figure 10.
Figure 10: Matrix popup menu
"Reinforcement" popup menu gives the user the libraries of available reinforcement type, as shown in Figure 11.
Figure 11: Reinforcement popup menu
"Reinforcement form" popup menu gives the user only the
option of unidirectional reinforcement form. Other reinforcement forms
are expected in the next version of AeroWing.
"Own Lay-up" button opens a new window called "Free
Hand Stacking Sequence" which gives the user the opportunity to
define freely the composite lay-up sequence of the wing to be studied.
"Lay-up Library" button opens a new window called "Database
Stacking Sequence" which gives the user the opportunity to pick
a composite lay-up sequence from a library.
The "Help" button will open a window to give the user
some help to use this "Composite Stacking" window.
The "Back to Wing" button will close the window and bring the user back to the "Wing Property" window.
The user must NOT close any window using the "close button" situated on the top right, but only using the "Back to Wing" button situated on the bottom right.
Note: The composite plies are not individually modelled in the
laminate, in order to save computing time, but are homogenised to a single
layer, that is the skin.
2.4.
"Free Hand Stacking Sequence" window
When the "Own Lay-up" button is pushed in the "Composite Stacking" window, a new window "Free Hand Stacking Sequence" window will open, as shown in Figure 12. This window allows the user to freely define the lay-up sequence of the composite skin.
Figure 12: Free Hand Stacking Sequence window
The popup menus on the top left side of the present window define the lay-up sequence, as shown in the example of Figure 12. The selected lay-up sequence will be displayed in blue colour right below the popup menus.
For those again which are not familiar with the composites, brief summary is given on the lay-up code.
Let us study the following example:
{04/± 454/±
30S/902}={0/0/0/0/45/-45/45/-45/45/-45/45/-45/30/-30/-30/30/90/90}
Each script corresponds to an angle in degree only where 0° coincides with the spanwise direction (X-direction in the model), then 90° the chordwise direction (Y-direction in the model). Basically the subscript n defines the number of times of ply with the same orientation will be repeated (04 = 0° +0° +0° +0° ). The subscript s stands for symmetric, meaning that for example ± 45S = (+45° )+(-45° )+(-45° )+(+45° ).
Note that ± is different from 
in
the plies order.
Besides, the subscript at the end of the lay-up (such as { }4S) determines the number of times the part of the lay-up is repeated. This is for simplicity of the lay-up writing. When the subscript is just a number n, the part of the lay-up is repeated n-times. When the subscript is a number followed by s for symmetric, the symmetry is first applied and further the repeated number of times containing the symmetric part, such as:
{03/90}3S = {0/0/0/90/90/0/0/0}{0/0/0/90/90/0/0/0}{0/0/0/90/90/0/0/0}
"Lay-up library" button will close the present window
to open the "Database Stacking Sequence" window to allow
the user to select a lay-up from lay-up libraries.
The "Help" button will open a window to give the user some help to use this "Free Hand Stacking Sequence" window.
The "Back to Wing" button will close the window and bring the user back to the "Wing Property" window.
The user must NOT close any window using the "close button" situated
on the top right, but only using the "Back to Wing" button
situated on the bottom right.
2.5.
"Database Stacking Sequence" window
When the "Lay-up Library" button is pushed in the "Composite
Stacking" window, a new window "Database Stacking Sequence"
window will open, as shown in Figure 13. This window allows the user to
select a lay-up sequence of the composite skin from a lay-up library.
For more information on composite lay-up sequence, do refer to the previous section 2.4.
The libraries of lay-up are absolutely arbitrary. It is made to be customised by the user for simplicity reasons.
Figure 13: Database Stacking Sequence window
If the case where the user decides to go for the "Free Hand Stacking
Sequence", just push the button "Lay-up Manually"
on the top right of the window.
The "Help" button will open a window to give the user some help to use this "Database Stacking Sequence" window.
The "Back to Wing" button will close the window and bring the user back to the "Wing Property" window.
The user must NOT close any window using the "close button" situated
on the top right, but only using the "Back to Wing" button
situated on the bottom right.
Chapter 3 error and warning messages
Because nobody is perfect, the user might initiate some anomalies in the program, such as in the wing definition. Indeed, in the "Wing Property" window, the user is asked to define the wing geometry (in the free hand case only). In the case where the user defines somehow a zero chord, which does not exist in reality, the program will warn the user to resolve the mistake, as shown in Figure 14. Nevertheless, in the hypothesis the user would like to define a delta wing, where in the theory the tip chord is zero, the program will set by itself a chord of 1 millimetre (0.0394 inch). If this condition were not respected, the element defined at the tip would have an inhomogeneous shape, which will initiate error in the calculation by the finite element method.
Figure 14: Warning message for zero chord at the wing tip
For the case where the user selects a composite wing (a wing made of two panels of composites), some constrains may appear, being warned by messages such as the one shown in Figure 15. Because the airfoil thickness is proportional to the airfoil chord, the airfoil thickness might be smaller than the two composite skin thicknesses, which is not physically possible. The program will thus make sure the distance between the two composite skins will remain positive.
Figure 15: "Error in the wing definition" window
Besides, if changes in the Matlab license or in the computer platform
occurred, the program AeroWing will warn the user to make sure the free
license agreement has been read.
The theory used in this program is reported in a report [3], and contains examples and checking of the results with experimental tests. The report can be sent on demand by Email at aerowing@engineer.com.
For the first example, the wing properties were:
| Wing Type | Airbus 300-200 |
| Material Type | Advanced Aluminium |
| Y-Splitting | 2 |
| X-Splitting | 5 |
| NACA Airfoil | 5333 |
| Angle of Attack (degree) | 8 |
| Velocity (Mach Number) | 0.8 |
| Altitude (km) | 10 |
| Magnification factor | 5000 |
Table 1: Case of wing in AeroWing software
Figure 16: Example of 3D-displacement of a wing with data from Table 1.
For the second example, the wing properties were:
| Wing Type | Dassault Rafale |
| Material Type | Composite |
|
Epoxy |
|
HTA |
|
Continuous |
|
(04/454/904/-454/02)S |
|
4.56 mm |
|
Advanced Aluminium |
| Y-Splitting | 5 |
| X-Splitting | 6 |
| NACA Airfoil | 4508 |
| Angle of Attack | 4 |
| Velocity (Mach Number) | 2.2 |
| Altitude (km) | 12 |
| Magnification factor | 10000 |
Table 2: Case of wing in AeroWing software
Figure 17: Example of 3D-displacement of a wing with data from Table 2.
Figure 16 shows the vortex ring elements, as well as the wake in solid lines, on the top of the finite wing. All panels are placed a quarter backward (towards the trailing edge) in order to fulfil the Kutta condition. The collocation points in dots, are placed in the centre of each vortex panel.
Figure 18: Vortex ring elements and wakes (in solid lines) and
collocation points (in dots)
In order to make sure somebody succeeds in improving this program, this section is devoted to explaining what each file does and where to change different parameters. However, if the reader discovers bugs or has questions, do not hesitate to contact the authors at the following Email addresses:
aerowing@engineer.com or
ptc@ffa.se
The main files:
Addaw.m: This M-file set the path of AeroWing folder in Matlab v5.
Aerow4.m: This M-file checks if the Matlab version 4 or platform changed, in order to display the license agreement.
Aerow5.m: This M-file checks if the Matlab version 5 or platform changed, in order to display the license agreement.
Aerowing.m: This M-file is the command to start Matlab from the directory it is placed and directs the user folder to the AeroWing folder "aerowf".
Aerowg.m: This M-file sets the Matlab path.
Airstd.m: This M-file defines the air properties at the selected altitude.
Awlicen.m: This M-file contains the free license agreement.
Awlicen.txt: This Text-file contains the free license agreement.
Awlicense.html : This HTML-file contains the free license agreement.
C.m: This M-file calculates the Theodorsen coefficient F and G of the Theodorsen function.
Css.m: This function is the User Interface for the Stacking Sequence of Composite materials. It works only with the file visu4d.m and with the program AeroWing.
Css2.m: This function is the User Interface for the Stacking Sequence of Composite materials. It works only with the file visu5d.m and with the program AeroWing.
Iae.m: This M-file is the file that concerns the main window so called "AeroWing".
Mae.m: This M-file defines the model nodes and elements.
Mae2.m: This M-file is the manager file of the program. It launches the program Vis2.m, Vis3.m and Sif.m.
Mag.m: This M-file launches the magnification window and displays the new wing without displacement and with magnified displacement.
Mal.m : This M-file checks if there are any elements with corners having angles greater than 135°, which cannot be handled by the finite element program.
Matdata.m: This M-file contains the material data of the matrix and the reinforcement. It also defines the 3-D material data for the composite skins.
Matlab.mat: This Mat-file is opened automatically by the Matlab program when the user starts to save data, and cancel the on-going process. Therefore, the data contained in this file are the saved data of the wing properties.
Nac16.m: This M-file is the graphic user interface for airfoil profile NACA series n.
Nac4.m: This M-file is the graphic user interface for airfoil profile NACA 4 digits.
Nac4m.m: This M-file is the graphic user interface for airfoil profile NACA modified 4-digits.
Nac5.m: This M-file is the graphic user interface for airfoil profile NACA 5 digits.
Nac5m.m: This M-file is the graphic user interface for airfoil profile NACA modified 5-digits.
Naca.m: This M-file contains the thickness distribution and camber equations.
Pdis.m: This M-file calculates the pressure distribution of an arbitrary airfoil. This is the main file for defining the pressure distribution of an arbitrary airfoil section (Not completed).
Psifct.m: This M-file defines the function 
used
in Pdis.m (Not completed).
Rma.m: This M-file removes the angle of attack on the deformed wing for recalculation of the aerodynamic forces.
Rmaw.m: This M-file removes the AeroWing path from the Matlab v5 path.
Rmo: This Unix or Unix-like file removes the file "*_output.dat" created by the finite element code which computed the displacement and the stresses.
Sif.m: This M-file defines the finite element input file (.dat) as well as the summary file (.sum).
Theo.m: This M-file calculates the moment and lift of an airfoil section for 2-D incompressible and steady flow, from the Theodorsen theory. This file is the main file for defining the lift and moment of thin plate by Theodorsen.
Uif.m: This M-file works together with iae.m.
Vis2.m: This M-file displays the reference model in 3D.
Vis3.m: This M-file displays the loaded model in 3D.
Vis4.m: This M-file displays the magnified loaded model in 3D.
Visu3d.m: This M-file defines the graphic user interface of "Wing Property" window.
Visu4d.m: This M-file defines the graphic user interface of "Composite Stacking" window.
Visu5d.m: This M-file defines the graphic user interface of the "Free Hand Stacking Sequence".
Visu6d.m: This M-file defines the graphic user interface of the "Database Stacking Sequence".
Vorwing.m: This M-file is the main file that deals with the lift-surface solution by vortex ring element developed in reference 1.
Voring.m: This M-file calculates the induced velocity created by the four-segment strength that constitutes the vortex ring.
Voring2.m: This M-file calculates the induced velocity created by the two-segment strength that constitutes the trailing vortex segment.
Vortex.m: This M-file calculates the global velocity induced by the vortex ring and wake, taking into account the other half wing.
Vortxl.m: This M-file calculates the velocity induced by any segment.
Yoc16.m: This M-file is the function thickness distribution (in percent of chord), depending on the chord ordinate: y/c=f(x/c), for profile NACA series n.
Yoc4.m: This M-file is the function thickness distribution (in percent of chord), depending on the chord ordinate: y/c=f(x/c), for profile NACA 4 digits.
Yoc4m.m: This M-file is the function thickness distribution (in percent of chord), depending on the chord ordinate: y/c=f(x/c), for profile NACA modified 4-digits.
Yoc5.m: This M-file is the function thickness distribution (in percent of chord), depending on the chord ordinate: y/c=f(x/c), for profile NACA 5 digits.
Yoc5m.m: This M-file is the function thickness distribution (in percent of chord), depending on the chord ordinate: y/c=f(x/c), for profile NACA modified 5-digits.
README.txt: This Text-file is the set-up explanation file. Do refer to this file for installation. Do not forget to change this file if any changes where performed by the reader.
20nodes.f: This source file is the finite element code file in FORTRAN 77.
20nodes.exe: This executable file is the finite element code file in FORTRAN 77.
Inputname.inp: This file is the finite element result file containing the node displacement field.
20node: This Unix file only executes the program 20nodes.exe and transfers output file to the main directory for FEM calculations.
Manual.html: This file in the manual of the present program in HTML format.
s2sa.mat: s1=Part 1 x-splitting, s2=Part 2 x-splitting.
labsa.mat.: labs, labl, labs5, labl5, nafore, naback, napm, btnPospop are information for defining the colour and position and changes in popup menus.
choicesa.mat: choice, choice5, col, col5, col5_text, col_text, switch1, switch2, colorStr2 are variables to define the colour and position and changes in popup menus.
visu3dsa.mat: evalStr is the string used in the visu3d.m file.
thicksa.mat: thickness is the thickness of the NACA profile.
nacasa.mat: yocpup and yocpun are the thickness distributions of the NACA profile and yocpc is the camber distribution. Supemax is the maximum thickness value.
nodesa.mat: x1 y1 z1, x2 y2 z2, x3 y3 z3, x4 y4 z4, x5 y5 z5, x6 y6 z6 are the node coordinates of the six main nodes defining the complete wing. 1 corresponds to the top root and 6 to the bottom root. Note that 2 here is the top middle node, 3 is the top tip node, 4 is the bottom tip node and 5 is the bottom middle node.
nonewsa.mat: nodevis3a is the new node and displacement at the last iteration of the aeroelasticity feedback for the specific accuracy.
comppsa.mat: matrixStr2 reinfStr2 reinffStr2 thickStr2 are some data displayed in visu4d.m.
angixsa.mat: angle_ind contains all angles of all plies defined in the composite stacking sequence.
visu4dsa.mat: wevalStr is the command string data for the file visu4d.m.
angdisa.mat: angle_disp2 is the set of ply angles, angle_disp3 is the set of corresponding subscripts of the ply angles and angle_disp4 is the last subscript concerning the whole lay-up block.
lmplysa.mat: nbrlaminae is the number of composite layers and lsss2 is a string describing the lay-up.
visu5dsa.mat: levalStr is the command string data for the file visu5d.m and visu6d.m.
lyupsa.mat: layup is the string defining the lay-up.
dat2sa.mat: angle_ind2 bomb16 are parameters used in the file visu6d.m.
visu6dsa.mat: levalStr is the command string data for the file visu5d.m and visu6d.m.
nacnasa.mat: nacav1 nacav2 nacav3 nacav4 nacav5 nacava nacavb nacav16a nacav16b nacav16c nacav16d nacav16e mltam cliu mltan clil are the parameters used to identify a NACA airfoil.
matersa.mat: thickStr volumf e11l e22l e33l g12l g13l g23l nu12l nu13l nu23l are the material data of composite laminate defined by the "Simplified Composite Micromechanics Equations for Hygral, Thermal and Mechanical Properties", Nasa Technical Memorandum 83320.
mahosa.mat: rhoho eho nuho wingdefws wingdefwm are the material data for homogeneous materials.
perset.mat: newmatfile newpath are the file name and file location given by the user for the results.
ataksa.mat: attack is the angle of attack in degree and speed is the velocity in Mach number.
commsa.mat: wlibrary_comment is the string comment in file visu3d.m.
elemsa.mat: element is the element code, node is the node coordinates of the referenced mesh, elem is a part of element, nxestr is the number of element in the x-direction, nyestr is the number of element in the y-direction, nzestr is the number of element in the z-direction.
invisa.mat: initvis is the index to check if this program was started for the first time of not.
layupsa.mat: Parameters for setting the lay-up display in visu4d.m.
nbl5.mat: indexation and licensmatlab are parameters to check to state of change in terms of matlab version or computer platform.
awpfp.mat: This file contains the image of the first window for MATLAB v5.
pcs2sa.mat: s1=Part 1 x-splitting, s2=Part 2 x-splitting.
pcbsa.mat.: labs, labl, labs5, labl5, nafore, naback, napm, btnPospop are information for defining the colour and position and changes in popup menus.
pcoicesa.mat: choice, choice5, col, col5, col5_text, col_text, switch1, switch2, colorStr2 are variables to define the colour and position and changes in popup menus.
pcsu3dsa.mat: evalStr is the string used in the visu3d.m file.
pcicksa.mat: thickness is the thickness of the NACA profile.
pccasa.mat: yocpup and yocpun are the thickness distributions of the NACA profile and yocpc is the camber distribution. Supemax is the maximum thickness value.
pcdesa.mat: x1 y1 z1, x2 y2 z2, x3 y3 z3, x4 y4 z4, x5 y5 z5, x6 y6 z6 are the node coordinates of the six main nodes defining the complete wing. 1 corresponds to the top root and 6 to the bottom root. Note that 2 here is the top middle node, 3 is the top tip node, 4 is the bottom tip node and 5 is the bottom middle node.
pcnewsa.mat: nodevis3a is the new node and displacement at the last iteration of the aeroelasticity feedback for the specific accuracy.
pcmppsa.mat: matrixStr2 reinfStr2 reinffStr2 thickStr2 are some data displayed in visu4d.m.
pcgixsa.mat: angle_ind contains all angles of all plies defined in the composite stacking sequence.
pcsu4dsa.mat: wevalStr is the command string data for the file visu4d.m.
pcgdisa.mat: angle_disp2 is the set of ply angles, angle_disp3 is the set of corresponding subscripts of the ply angles and angle_disp4 is the last subscript concerning the whole lay-up block.
pcplysa.mat: nbrlaminae is the number of composite layers and lsss2 is a string describing the lay-up.
pcsu5dsa.mat: levalStr is the command string data for the file visu5d.m and visu6d.m.
pcupsa.mat: layup is the string defining the lay-up.
pct2sa.mat: angle_ind2 bomb16 are parameters used in the file visu6d.m.
pcsu6dsa.mat: levalStr is the command string data for the file visu5d.m and visu6d.m.
pccnasa.mat: nacav1 nacav2 nacav3 nacav4 nacav5 nacava nacavb nacav16a nacav16b nacav16c nacav16d nacav16e mltam cliu mltan clil are the parameters used to identify a NACA airfoil.
pctersa.mat: thickStr volumf e11l e22l e33l g12l g13l g23l nu12l nu13l nu23l are the material data of composite laminate defined by the "Simplified Composite Micromechanics Equations for Hygral, Thermal and Mechanical Properties", Nasa Technical Memorandum 83320.
pchosa.mat: rhoho eho nuho wingdefws wingdefwm are the material data for homogeneous materials.
pcrset.mat: newmatfile newpath are the file name and file location given by the user for the results.
pcaksa.mat: attack is the angle of attack in degree and speed is the velocity in Mach number.
pcmmsa.mat: wlibrary_comment is the string comment in file visu3d.m.
pcemsa.mat: element is the element code, node is the node coordinates of the referenced mesh, elem is a part of element, nxestr is the number of element in the x-direction, nyestr is the number of element in the y-direction, nzestr is the number of element in the z-direction.
pcvisa.mat: initvis is the index to check if this program was started for the first time of not.
pcyupsa.mat: Parameters for setting the lay-up display in visu4d.m.
nbl4.mat: indexation and licensmatlab are parameters to check to state of change in terms of Matlab version or computer platform.
Unknown.mat: This file is an example file for the first user. Warning!!, this file should remain if the administrator or the user decides to delete useless files of this folder "Settings".
Note: It might be some more files, but it would have been files defined by the previous users or works.
All files with the extension .mat correspond to the files that contain wing property data.
All files with the extension .dat are the input files of the finite element code.
All files with the extension _output.dat are the output files of the finite element code.
All files with the extension .sum are the corresponding
summary
files to help the user.
[2] I. M. Smith and D. V. Griffiths, Programming the finite element method, Second edition, ed. John Wiley & Sons Ltd., 1988
[3] C. A. Paget and J. Matrat, Advanced topic in Aeronautics: A 3-D
Aeroelastic Program, internal report, FFA-KTH, 1999