LEparagliding 3.10

Note: Remember usual color index numbers for CAD systems:
1= red, 2=yellow, 3=green, 4=cyan, 5=blue, 6=magenta 7=white 8=dark grey 9= grey,... up to 255 depending on your color palette. It is preferable not to use colors with more than two digits.

SECTION 25: GENERAL 3D DXF OPTIONS

This section allows the user to define some colors in the 3D DXF plans. Allows to draw unifilar not ovalized versions of the surfaces.

Line 1: integer
if integer = 0 DXF options set by default
if integer = 1 add some others parameters for the 3D DXF

Only if first integer is 1 then add:

Line 2: text1 integer text2
tex1: A_lines_color (do not change this text)
integer: color number index for "A" lines
text2: color name (optional text not used)

Line 3: text1 integer text2
tex1: B_lines_color (do not change this text)
integer: color number index for "B" lines
text2: color name (optional text not used)

Line 4: text1 integer text2
tex1: C_lines_color (do not change this text)
integer: color number index for "C" lines
text2: color name (optional text not used)

Line 5: text1 integer text2
tex1: D_lines_color (do not change this text)
integer: color number index for "D" lines
text2: color name (optional text not used)

Line 6: text1 integer text2
tex1: E_lines_color (do not change this text)
integer: color number index for "E" lines
text2: color name (optional text not used)

Line 7: text1 integer text2
tex1: F_lines_color (do not change this text)
integer: color number index for "F" brake lines
text2: color name (optional text not used)

Line 8: text1 integer integer text2
tex1: Extrados (do not change this text)
integer: if set to "0" unifiilar extrados is not drawn, if set to "1" is drawn
integer: color index for the extrados
text 2: optional text with the color name

Line 9: text1 integer integer text2
tex1: Vents (do not change this text)
integer: if set to "0" unifiilar vents is not drawn, if set to "1" is drawn
integer: color index for the vents
text 2: optional text with the color name

Line 10: text1 integer integer text2
tex1: Intrados (do not change this text)
integer: if set to "0" unifiilar intrados is not drawn, if set to "1" is drawn
integer: color index for the intrados
text 2: optional text with the color name

Example:
*******************************************************
*       25. GENERAL 3D DXF OPTIONS
*******************************************************
1
A_lines_color    1     red
B_lines_color    8     grey
C_lines_color    8     grey
D_lines_color    8     grey
E_lines_color    8     grey
F_lines_color    30    orange
Extrados    1    5     blue
Vents       0    1     red
Intrados    1    3     green

SECTION 26. GLUE VENTS

This section allows to automatically "glue" the air inlets (vents) into the panel of extrados, intrados, or to separate them. The vents include sewing edges. The skin tension i the vent is linear and automatically corresponds to that defined at the points correspondingin extrados and intrados.
The vent definition is very easy and intuitive. You have to make a list of two columns. In the first column, the profile number is indicated, and in the second column the corresponding parameter:
1 means glue the vent to the extrados (normally used in paragliders single skin type)
0 means do not glue anywhere (open air inlet). It is drawn apart to define with CAD special air intakes (circles, ellipses, ...)
-1 means glue the vent to the intrados (usually means, closed cell)
-2 means diagonal vent 100% open ant left, glued to intrados
-3 means diagonal vent 100% open alt right, glued to intrados

Line 1: integer
if integer = 0 then end the section and use old vents style (not recommended)
if integer = 1 add some others parameters for precise vents control

Only if first integer is 1 then add N lines, one for each airfoil number i:

Line i: integer1 integer2
integer1: airfoil number (cell between airfoil i and airfoil i-1)
integer2: vent parameter (available parameters 1, 0, -1,-2,-3 as explained above)

Examples 1 (use old style):

*******************************************************
*       26. GLUE VENTS
*******************************************************
0

Examples 2 (full vent control):

*******************************************************
*       26. GLUE VENTS
*******************************************************
1
1    0
2    0
3    1
4 -2
5   -3
...
20 -2
21 -1
22 -1
23 -1

S26

Figure 5. Glue vents

Functional vents in version 3.02:
0 (=open, but print apart for design special vents)
1 (=closed and "glued" to upper surface)
-1 (=closed and "glued" to lower surface)
-2 (=diagonal vent open at left and "glued" to lower surface)
-3 (=diagonal vent open at right and "glued" to lower surface)

Figure 5+: Vents types (version >= 3.02)

SECTION 27 SPECIAL WINGTIPS

It is used for defining wingtips with special shapes:

Figure 6. Special wingtip

Line 1: integer
if integer = 0 do not add wingtip modifications(set by default)
if integer = 1 add some wingtip modifications

Only if first integer is 1 then add:

Line 2: text real
text: AngleLE (do not change this text)
real: angle in degrees between the horizontal and the leading edge in the last cell

Line 3: text real
text: AngleTE (do not change this text)
real: angle in degrees between the horizontal and the trailing edge in the last cell

Example 1:
*******************************************************
* 27. SPECIAL WING TIP
*******************************************************
1
AngleLE 45
AngleTE -7.78

"1" refers to define "type 1" wing tip modifications. It is planned to define several modifications. Type 1 is the simplest.
"AngleLE" is a name not computed. It serves to remember that next we have to write the new angle in degrees between the horizontal and the leading edge in the last cell. It is usual to force the angle of the last cell, and this section allows it to be done without modifying the geometry matrix. Set 45º for example. "AngleTE" is a name not computed for the trailing edge. Set the angle as desired, -7.78º for example.

Example 2:
*******************************************************
* 27. SPECIAL WING TIP
*******************************************************
0

SECTION 28 PARAMETERS FOR CALAGE VARIATION

Study the variations in the riser lengths and calage when applying speed system or trim system. It is interesting to experiment with new calages in prototypes or to define the speed or trim systems.
s28a

Figure 7a. Principles of the study of the calage variations.

We study the variations in the riser lengths when applying accelerator (speed system) pivoting in the last riser (most common case), which remains with constant length. For practical purposes we define a negative alpha angle of pitch increased in N1 spaces gradually, and then we compute the variations in the line lengths and calage. We do the same study, assuming a trim system that increases the picth angle in N2 spaces gradually. In this case, the most usual is to consider the constant length A riser and the other variables in length.

The program analyzes a total of 4 cases, depending on the pivot point and if it is reduction or increase in angle:
s28b

Figure 7b. Cases a,b,c,d reported in file lep-out.txt

In output file SECTION 7: lep-out.txt we see the tables that relate in detail the variations of angle, with the calage variations, and increments or decrements of length in each riser. It is interesting to experiment with new calages in prototypes or to define the speed or trim systems. Four cases:
a) Speed system pivot in last riser
b) Speed system pivot in first riser
c) Trimer system pivot in first riser
d) Trimer system pivot in last riser

Example lep-out.txt:
a) Speed system pivot in last riser:
-------------------------------------------
i   alpha       A       B       C Calage
1     .00     .00     .00     .00   25.00
2   -1.00   -2.18   -1.29     .00   21.19
3   -2.00   -4.35   -2.59     .00   17.40
4   -3.00   -6.52   -3.88     .00   13.66
Column 2 > angle alpha in degrees
Column 3 > Decrease of length A riser (amount of accelerator) in cm
Column 4 > Decrease of length B riser in cm
Column 5 > Decrease of length C riser in cm = 0 (pivot in C riser)
Column 6 > New calage %

Write data in in SECTION 28 with one or four lines:

Line 1: integer
if integer = 0 do nothing
if integer = 1 do calage study "type 1"

Only if first integer is 1 then add:

Line 2: integer
integer: number of risers to be considered (2,3,4,5 or 6)

Line 3: real1 real2 real3 real4 real5 real6
real1: % of central chord for riser A (is not necessary to match anchor position)
...
real6: % of central chord for riser E (is not necessary to match anchor position)

Line 4: real1 integer1 real2 integer2
real1: max angle (negative) in degrees set by the speed system
integer1: number of steps in angle for study purpose
real2: max angle (positive) in degrees set by the trim system
integer2: number of steps in angle for study purpose

Example:
*******************************************************
*       28. PARAMETERS FOR CALAGE VARIATION
*******************************************************
1
3
10. 30.35 60 0 0 0
-4 4 5 10
*******************************************************

Explanation:
Set to calage type "1" (first line), only type "1" available
"3" risers to be considered
A=10.% B=30.35% C=60% D= E= F=   (set % to be considered)
Speed angle set to -4º and compute in 4 steps
Trim angle set to 5º and compute in 10 steps

s28c

Figure 7c. New graphic in plan 2-1 (.dxf output)

SECTION 29 3D SHAPING

The model of 3-Shaping proposed by the Laboratori, consists in making one or two transverse cuts in the upper surface, near the leading edge, and another optional cut on the bottom surface. We will call this model as "type 1". The edges of the transverse cuts will be modified from the straight line into an arc of a circle. In this way, we can "add fabric" lengthwise and we can control the ovalization and the tension in this direction. Ovalization in transverse direction is achieved via the module of skin tension (SECTIONS 5 or 31). In summary, we can control the amount of tissue and tension in transverse and in longitudinal direction near the nose, where the curvatures are greatest.

To set the parameters of the 3D-shaping in the model "type 1" is necessary to study the profile in detail, viewing and counting the individual points that form it, Laboratori style! :-) You need to view your profile in CAD (or in the .txt file), identify and count points. Remember that the points in a profile is counted starting in the trailing edge (point 1), continuing by the upper surface, nose, vents, lower surface, and ending again in the trailing edge. Exactly as described previously. We could define another model "type 2" where the position of the cut points are defined in % of the length of the panel, but in this model 1, is considered to specify exactly the points considered.

For each cut, it is necessary to define a "zone of influence". In the zones of influence is measured the length of a section of the profile and is compared with the corresponding length in the ovalized profile. This question is fundamental to understand the 3D-shaping type 1. It is necessary to view the figure below:

Figure 8. Cuts and zones of influence. J1,j2,j3,j4,j5,j6,j7 indicate numeric values of the selected points in the profile, starting to count from the trailing edge. J4 and j5 are the vent points.

For the purposes of notation, we will call the different parts in which we divide the profile as:
zone 1 (between j1 and j2), extrados part 1
zone 2 (between j2 and j3), extrados part 2
zone 3 (between j3 and j4), extrados part 3 or nose
zone 4 (between j4 and j5), or vents
zone 5 (between j5 and j6), intrados part 1
zone 6 (between j6 and j7), intrados part 2

In each zone 1,2,3,4,5,6 the program computes the length ot the arch of airfoil (d1) and the arch of the ovalized airfoil (d2). The differences of longitude (d2-d1) are calculated automatically in each zone, and then applied consistently to each cut with a value (f) obtained using the values (d2-d1) of the adjacent zones. Is provided a setting parameter around 1.0, which serves the designer to regulate the depth of the 3D-shaping in each cut, in relation to the automatic calculation. Thus, using the coefficient of 1.0, the depth of 3D is according to the theory exposed. Using a coefficient of 0.0 does not apply the 3D effect, and using values higher or lower than 1.0 increases or decreases the effect. The control of the depth of 3D-shaping is continuous and individual for each cut. A more detailed description, and the formulas used in the calculation are described in this technical note about 3D-shaping. For each rib, a full report of the values d1, d2, d2-d1, computed in each zone, and the final values f aplied in each cut are printed in tabular form in section 9 of the file lep-out.txt. Also, for verification purposes, a new section 10 is written to the lep-out.txt file with the counting of the points of each profile, to verify that they are all the same for all profiles, and that they are compatible with the defined cuts.

It should be noted, that the parameters applied in this section, will be usually "invariant values" applied to the majority of the designs. We just have to think about all this, a single time for each type of profile. And the Laboratory will provide soon the recommended values in next designs. Of course, finding the good parameters is a real art. The program LEparagliding now provides the tools to make numerical and graphical experiments (lep-out.txt section 9 and leparagliding.txt plan in box 1-8).

Explanation of the parameters in SECTION 29:

Line 1: integer
if integer = 0 then no not use 3D-shaping, and finish writing the section.
if integer = 1 then use 3D-shaping, and continue writing:

Line 2: integer
integer = type of 3D-shaping theory used, now we use only model "type 1" using transverse cuts, set parameter to 1.

Line 3: character integer
character = groups
integer1 = number of groups used

Line 4: character integer1 integer2 integer3
character = group
integer1 = number of the group
integer2 = initial rib in group
integer3 = final rib in group

Line 5: character integer1 integer2
character = upper , word meaning upper surface (extrados)
integer1 = number of cuts in upper surface (possible values 1 or 2).
integer2 = subtype of cuts, set to 1, only value accepted

Line 6: integer1 integer2 real
integer1 = initial point in the first zone of influence (j1)
integer2 = point where the first cut is set (j2)
real = "depth" of 3D-shaping in the cut, possible values 0.0, 0.1,....,1.0,1.2,... (multiplier coefficient arount 1.0)

Line 7: integer1 integer2 real   (only if we use two extrados cuts)
integer1 = initial point in the second zone of influence (j2)
integer2 = point where the second cut is set (j3)
real = "depth" of 3D-shaping in the cut, possible values 0.0, 0.1,....,1.0,1.2,... (multiplier coefficient arount 1.0)

Line 8: character integer1 integer2
character = lower , word meaning lower surface (intrados)
integer1 = number of cuts in lower surface (possible values 0 or 1).
integer2 = subtype of cuts, set to 1, only value accepted

If the number of cuts in intrados is 0, stop writing, else

Line 9: integer1 integer2 real   (only if we use two extrados cuts)
integer1 = point where the intrados cut is set (j6)
integer2 = final point in the intrados zone of influence (j7)
real = "depth" of 3D-shaping in the cut, possible values 0.0, 0.1,....,1.0,1.2,... (multiplier coefficient arount 1.0)

(...Repeat lines 5,6,7,8,9 for next groups...)

Line 10: character
character = "* print parameters:" (comment line, it is mandatory to write something)

Line 11: character integer1 integer2 integer3 integer4
character = Inter3D, word to indicate representation of the intermediate airfoils in 3D lep-3d.dxf
integer1 = 0 indicates do not draw, and 1 draw
integer2 = index of first airfoil to draw
integer3 = index of last airfoil to draw
integer4 = 0 it indicates to draw with symmetry, 1 only one side

Line 12: character integer1 integer2 integer3 integer4
character = Ovali3D, word to indicate representation of the intermediate ovalized airfoils in 3D lep-3d.dxf
integer1 = 0 indicates do not draw, and 1 draw
integer2 = index of first airfoil to draw
integer3 = index of last airfoil to draw
integer4 = 0 it indicates to draw with symmetry, 1 only one side

Line 13: character integer1 integer2 integer3 integer4
character = tesse3D, word to indicate representation of panel tessellation in 3D lep-3d.dxf
integer1 = 0 indicates do not draw, and 1 draw
integer2 = index of first panel to draw
integer3 = index of last panel to draw
integer4 = 0 it indicates to draw with symmetry, 1 only one side

Line 14: character integer1 integer2 integer3 integer4
character = exteDXF, word to indicate representation of panels tessellation in 3D in a new external DXF file (possible use in CFD analysis)
integer1 = 0 indicates do not draw, and 1 draw
integer2 = index of first panel to draw
integer3 = index of last panel to draw
integer4 = 0 it indicates to draw with symmetry, 1 only one side

Line 15: character integer1 integer2 integer3 integer4
character = exteSTL, word to indicate representation of panels tessellation in 3D in a new external STL file (used with programs of 3D modelling as OpenSCAD gold FreeCAD)
integer1 = 0 indicates do not draw, and 1 draw
integer2 = index of first panel to draw
integer3 = index of last panel to draw
integer4 = 0 it indicates to draw with symmetry, 1 only one side

Lines 12, 13, 14, 15 are mandatory to write, but the actions are not yet functional. We are working on the programming. These parameters will generate independent dxf files with the ovalized surfaces, and even a .stl model to view with FreeCAD or OpenSCAD, or even analyze with CFD programs.

All this may seem complicated, but it is much easier to understand section structure watching a few examples:

Example 1: Do not use 3D-shaping. Set one line with "0" parameter. It is the simplest solution to avoid the complicated 3D-shaping module! :)

*******************************************************
*       29. 3D SHAPING
*******************************************************
0

Example 2: Active 3D-shaping module but without any cut. The utility of defining this, is that the representation of plan 1-8 is activated automatically, with the drawing of the intermediate and ovalized airfoils in 2D. You can also activate the 3D representations in 3D, changing the settings "0" to "1" in the "Print parameters" subsection. In general, preferable to use example 2, that use the example 1 (the two are invariant sections).

************************************************************
*       29. 3D SHAPING
*******************************************************
1
1
groups 1
group   1    1    1
upper   0    1
lower   0    1
* Print parameters
Inter3D 0    1    1    0
Ovali3D 0    1    1    0
tesse3D 0    1    1    0
exteDXF 0    1    1    0
exteSTL 0    1    1    0

Example 3. Easy case, only one group and one cut in extrados.
First group from rib 1 to 14 using one cuts type 1 in upper surface and zero in lower surface.
Zone of influence of first cut started in point 30 and cut located in point 40, depth of the effect 0.8.
Zero cuts in lower surface, type 1.
Prints 3D intermediate (Inter3D) and ovalized (Ovali3D) airfoils at the left of rins 1 to 14

*******************************************************
*       29. 3D SHAPING
*******************************************************
1
1
groups 1
group    1    1   14
upper    1    1
1       30 40 0.8
lower    0    1
* Print parameters
Inter3D 1    1    14    0
Ovali3D 1    1    14    0
tesse3D 0    1    1     0
exteDXF 0    1    1     0
exteSTL 0    1    1     0

Example 4: General case, using two groups.

First group from rib 1 to 10 using two cuts in upper surface and one in lower surface.
Zone of influence of first cut started in point 25 and cut located in point 33, depth of the effect 0.8.
Zone of influence of the second cut in point 33 and cut located in point 44, depth of the effect 0.9.
Cut in lower surface in point 79 and zone of influence up to point 84, depth of effect 1.0.

Second group from rib 11 to 14 using two cuts in upper surface and one in lower surface.
Zone of influence of first cut started in point 25 and cut located in point 33, depth of the effect 0.9.
Zone of influence of the second cut in point 33 and cut located in point 44, depth of the effect 0.9.
Cut in lower surface in point 79 and zone of influence up to point 83, depth of effect 1.0.

*******************************************************
*       29. 3D SHAPING
*******************************************************
1
1
groups 2
group    1    1   10
upper    2    1
1       25 33 0.8
2       33 44 0.9
lower    1    1
1       79   84   1.0
group    2   11   14
upper    2    1
1       25 33 0.9
2       33 44 0.9
lower    1    1
1       79   83   1.0
* Print parameters
Inter3D 1    1    14    0
Ovali3D 1    1    14    0
tesse3D 0    1    1     0
exteDXF 0    1    1     0
exteSTL 0    1    1     0

The location of the cut points depends mainly on the study of the shape of the profile. It is interesting to concentrate the cuts where the difference in lengths between segments located in the intermediate profile and the ovalized (balloned) profile are larger. As a first approximation, can be studied to place the cuts in the 5.5% and 13.5% of the profile chord, counting from the leading edge. It is also important to choose correctly the coefficient of depth. Theoretically 1.0 is the best, but to smooth out the surfaces, you can choose a smaller coefficient.

As Piet suggests from the Netherlands, the 3D module can also be used as a simple alternative to separate colored panels in the noses area, or panels with more durable fabric. Remember that the 3D effect is adjustable in depth, and you can even use the parameter amplification 0.0 so that the cut between the parts of the panels is completely straight line. The subroutines developed in this section will be adapted to complete the separation in parts of colors.

The programming of this 3D-shaping module has been made possible thanks to the support of Scott Roberts from USA (Fluid Wings https://www.fluidwings.com/ ).

SECTION 30: AIRFOIL THICKNESS MODIFICATION

Coefficients of amplification or reduction of the thickness of the cells. Normally define as "1.0", or "0.0" in the wingtip.

Line 1: integer
if integer = 0 then no airfoil amplification set
if integer = 1 then add:

Lines 1,2,3,...,maxrib: integer   real
Integer: set rib number (1,2,3...) in all ribs
real: set amplification coefficient, for example 1.0 as default

Example:
*******************************************************
*       30. AIRFOIL THICKNESS MODIFICATION
*******************************************************
1
1    1.2
2    1.1
3    1.0
4    1.0
5    1.0
6    1.0
7    1.0
8    1.0
9    1.0
(...)
23 0.0

SECTION 31: NEW SKIN TENSION

The correct definition of the skin tension is essential for the internal solidity and the flight quality of the apparatus. For this reason, it is recommended that the designer have total control over the skin tension, with a very precise form (law of increments of width), and allowing changes in different panels along the span. This is what allows the new module.

The module new skin tension, functional from version 3.00, defines the additional widths of panels, to achieve the desired ovalitzation. The values applied to the extrados and intrados, for compatibility are the same as those explained in SECTION 5 (read again and notice the scheme 20181230), but there is a greater control. The number of points to define the widths is not limited to 6, now can be up to 100 points (!) (to choose freely). And it is possible to choose different widths for each one of the ribs, if it is considered necessary, (defining different "groups" of widths). Of course, the number of groups can be equal to the number of ribs, and thereby define the widths of each panel individually (for example, different tension in the panels of the center panels and in the wingtip.

The basic idea is to calculate increments of width to the left and to the right of each rib. Thus, a panel can have a 2% increase maximum in the left border and a 3% maximum to the right border. Negative values of increase are also acceptable, although I recommend not to use to simplify.

It is very recommended to use always the same number of points among different groups, because the current programming can generate undesiderd distortions (to be corrected soon).

The system allows to define in detail the tension in the extrados and intrados surfaces, but in the air inlets (vents)? The program automatically adds a linear transition in the vents area between extrados and intrados.

The "mysterious" two correction parameters of the last two lines of section 5 continue to have application. Normally no need to modify ever. I recommend use always:
1000   1.0

There are different ways of defining the skin tension. In the current version it is only active the version of "type 1", which consists of a linear interpolation and a width of reference for applying the law of increments of width, equal to the average width of each panel. Given the large amount of points available to interpolate (100) is not strictly necessary, a version with splines "type 2", to propose later. Usually with 10 or 15 points, linear interpolation is sufficient (old version uses only 6). Another proposal to consider is a version of linear interpolation "type 3" where the law of increments of width is not in reference to the mean width of the panel, but the width existing at each point between two adjacent profiles adjacent (possibly this is the solution that is most perfect).

To clarify and better explain all these fundamental issues, soon I'll be posting an article with diagrams.

Explanation of the parameters in section 31:

Line 1: integer
if integer = 0 then no not use new skin tension module, and finish writting the section.
if integer = 1 then use new skin tension module, and continue writting:

Line 2: integer
integer = number of skin tension grups (max= number of ribs)

Line 3: character
character = comment line explaining the group "i" from rib n1 to rib n2, using X points, and type "1".
(for now, only type "1" is possible, and means it uses linear interpolation between points. Add more points to smooth out, if necessary.)

Line 4: integer1 integer2 integer3 integer4 integer5
integer1 = group number
integer2 = initial rib
integer3 = final rib
integer4 = points for interpolation
integer5 = 1 , type linear of interpolation

Lines 5 to 5-1+ npoints of interpolation: integer real1 real2 real3 real4
integer = point of interpolation in consucutive order
real1 = Distance in % of length of the extrados panel starting in the leading edge
real2 = Additional width in % of the extrados panel
real3 = Distance in % of length of the intrados panel starting in the trailing edge
real4 = Additional width in % of the intrados panel

(Same geometric definition as in SECTION 5.)

In the following lines. Continue describing groups starting with the line of comments.

Examples:

Example 1 (do not use new skin tension module):

*******************************************************
*       31. NEW SKIN TENSION MODULE
*******************************************************
0

Example 2:
*******************************************************
*       31. NEW SKIN TENSION MODULE
*******************************************************
1
3
* Skin tension group number "1" from rib 1 to 10, 7 points, type "1"
1    1    10    7    1
1    0.         0.5     0.         0.
2    7.5        1.3     10.        1.33
3    15.        2.5     20.        2.5
4    80.        2.5     80.        2.5
5    90.        1.33    90.        1.33
6    95.        0.65    95.        0.9
7    100.       0.0    100.        0.5
* Skin tension group number "2" from rib 11 to 19, 7 points, type "1"
1    11    19    7    1
1    0.        0.5       0.        0.
2    7.5        1.3     10.        1.33
3    15.        2.5     20.        2.5
4    80.        2.5     80.        2.5
5    90.        1.33    90.        1.33
6    95.        0.65    95.        0.9
7    100.       0.0    100.        0.5
* Skin tension group number "3" from rib 20 to 23, 7 points, type "1"
1    20    23    7    1
1    0.         0.5      0.         0.
2    7.5        1.3   10.         1.33
3    15.        2.5     20.         2.5
4    80.        2.5   80.         2.5
5    90.        1.33    90.         1.33
6    95.        0.65    95.         0.9
7    100.    -0.5    100.         0.5
********************************************************

Notes	Source code	Linux version	Windows version	MAC version
3D-shaping active	leparagliding.f	lep-3.10-lin-32bit lep-3.10-lin-64bit (includes gnuA+ example)	lep-3.10-win32-xp lep-3.10-win-32bit lep-3.10-win-64bit (includes gnuA+ example)	Compile