************************************************************** * LABORATORI D'ENVOL PARAGLIDING DESIGN * * Input data file version 3.20V * ************************************************************** * Version 2022-09-26 * ************************************************************** * 1. GEOMETRY * ************************************************************** * Brand name "LABORATORI D'ENVOL" * Wing name "gnuComet-test" * Drawing scale 1. * Wing scale 1.025672373 * Number of cells 28 * Number of ribs 29 * Alpha max and parameter 4.5 1 * Paraglider type and parameter "ds" 1 * Rib geometric parameters * Rib x-rib y-LE y-TE xp z beta RP Washin pos_w desp Z Z_pos 1 0.00 -0.00 322.25 0.00 0.00 0.00 33.33 0.00 0.0 50.0 2 43.55 0.39 302.62 43.51 1.56 4.21 33.33 0.00 0.0 50.0 3 86.84 1.55 289.88 86.55 6.21 8.12 33.33 0.00 0.0 50.0 4 129.70 3.47 283.47 128.71 13.81 12.23 33.33 0.00 0.0 50.0 5 171.93 6.30 277.21 169.64 24.20 16.14 33.33 0.00 0.0 50.0 6 213.28 10.73 271.22 208.91 37.10 20.04 33.33 0.00 0.0 50.0 7 253.46 16.79 266.02 246.00 52.55 25.21 33.33 0.00 0.0 50.0 8 292.25 24.35 261.34 280.37 70.49 29.95 33.33 0.00 0.0 50.0 9 329.41 33.27 256.08 311.75 90.38 34.70 33.33 0.00 0.0 50.0 10 364.74 43.38 250.26 339.99 111.59 39.24 33.33 0.00 0.0 50.0 11 398.04 54.52 243.92 364.89 133.68 45.06 33.33 0.00 0.0 50.0 12 428.76 66.36 234.50 384.97 156.90 53.28 33.33 0.00 0.0 50.0 13 456.49 78.52 221.51 400.12 180.10 60.55 33.33 0.00 0.0 50.0 14 480.98 90.65 206.41 409.34 202.72 75.39 33.33 0.00 0.0 50.0 15 503.50 103.21 189.42 412.42 224.97 88.85 33.33 0.00 0.0 50.0 ************************************************************** * 2. AIRFOILS * ************************************************************** * Airfoil name, intake in, intake out, open , disp. rrw 1 gnua.txt 1.6 6.3 1 0 0.5 0 2 gnua.txt 1.6 6.3 1 0 1 15 3 gnua.txt 1.6 6.3 1 0 1 15 4 gnua.txt 1.6 6.3 1 0 1 15 5 gnua.txt 1.6 6.3 1 0 1 15 6 gnua.txt 1.6 6.3 1 0 1 15 7 gnua.txt 1.6 6.3 1 0 1 15 8 gnua.txt 1.6 6.3 1 0 1 15 9 gnua.txt 1.6 6.3 1 0 1 15 10 gnua.txt 1.6 6.3 1 0 1 15 11 gnua.txt 1.6 6.3 1 0 1 15 12 gnua.txt 1.6 6.3 1 0 1 15 13 gnua.txt 1.6 6.3 0 0 1 15 14 gnua.txt 1.6 6.3 0 0 1 15 15 gnua.txt 1.6 6.3 0 0 1 1 ************************************************************* * 3. ANCHOR POINTS * ************************************************************* * Airf Anch A B C D E F 1 4 8.5 30.0 53 77 0 0 2 4 8.5 30.0 53 77 0 100 3 4 8.5 30.0 53 77 0 100 4 4 8.5 30.0 53 77 0 100 5 4 8.5 30.0 53 77 0 100 6 4 8.5 30.0 53 77 0 100 7 4 8.5 30.0 53 77 0 100 8 4 8.5 30.0 53 77 0 100 9 4 8.5 30.0 53 77 0 100 10 4 8.5 30.0 53 77 0 100 11 4 8.6 30.0 53 77 0 100 12 4 8.6 30.0 53 77 0 100 13 3 9.9 40.0 70 0 0 100 14 0 9.9 40.0 70 0 0 100 15 4 0.0 30 60 90 0 0 ************************************************************* * 4. AIRFOIL HOLES * ************************************************************* 2 1 12 9 1 14.59 2.79 2.735 6.72 0. 0. 0. 0. 1 22.18 2.61 2.375 6.72 0. 0. 0. 0. 1 33.36 1.64 2.5 5.9 0. 0. 0. 0. 1 40.32 1.46 2.4 5.8 0. 0. 0. 0. 1 47.41 1.34 2.23 5.7 0. 0. 0. 0. 1 59.17 1.27 1.84 3.4 0. 0. 0. 0. 1 65.23 1.33 1.7 3.2 0. 0. 0. 0. 1 71.21 1.18 1.6 3.0 0. 0. 0. 0. 1 81.87 0.89 1.6 1.6 0. 0. 0. 0. 13 14 3 1 23.5 2.5 6.5 6.5 0. 0. 0. 0. 1 55.0 1.92 4.3 4.3 0. 0. 0. 0. 1 81. 1.1 1.7 1.7 0. 0. 0. 0. ************************************************************* * 5. SKIN TENSION * ************************************************************* Extrados 0. 0. 0. 0. 7.5 1.3 10. 1.33 15. 2.5 20. 2.5 80. 2.5 80. 2.5 90. 1.33 90. 1.33 100. 0.0 100. 0. 0.0114 1000 1.0 ************************************************************* * 6. SEWING ALLOWANCES * ************************************************************* 15 25 25 upper panels (mm) 15 25 25 lower panels (mm) 15 ribs (mm) 15 vribs (mm) ************************************************************* * 7. MARKS ************************************************************* 25. 0.5 0.15 ************************************************************ * 8. Global angle of attack estimation * ************************************************************* * Finesse GR 6.0 * Plumb point estimation % 36.6 * Calage % 34 * Risers lenght cm 45 * Line lenght cm 525 * Karabiners cm 40 *************************************************** * 9. SUSPENSION LINES DESCRIPTION (4 lines) *************************************************** 3 4 13 3 1 1 2 1 3 1 0 0 1 1 - 1 2 4 3 1 1 2 1 3 2 0 0 1 2 - 1 2 4 3 1 1 2 1 3 3 0 0 1 3 - 1 2 4 3 1 1 2 2 3 4 0 0 1 4 - 1 2 4 3 1 1 2 2 3 5 0 0 1 5 - 1 2 4 3 1 1 2 2 3 6 0 0 1 6 - 1 2 4 3 1 1 2 3 3 7 0 0 1 7 - 1 2 4 3 1 1 2 3 3 8 0 0 1 8 - 1 2 4 3 1 1 2 3 3 9 0 0 1 9 - 1 2 4 3 1 1 2 4 3 10 0 0 1 10 - 1 2 4 3 1 1 2 4 3 11 0 0 1 11 - 1 2 4 3 1 1 2 4 3 12 0 0 1 12 - 1 2 4 3 1 1 2 4 3 13 0 0 1 13 - 1 2 4 13 3 1 1 2 1 3 1 0 0 2 1 - 1 2 4 3 1 1 2 1 3 2 0 0 2 2 - 1 2 4 3 1 1 2 1 3 3 0 0 2 3 - 1 2 4 3 1 1 2 2 3 4 0 0 2 4 - 1 2 4 3 1 1 2 2 3 5 0 0 2 5 - 1 2 4 3 1 1 2 2 3 6 0 0 2 6 - 1 2 4 3 1 1 2 3 3 7 0 0 2 7 - 1 2 4 3 1 1 2 3 3 8 0 0 2 8 - 1 2 4 3 1 1 2 3 3 9 0 0 2 9 - 1 2 4 3 1 1 2 4 3 10 0 0 2 10 - 1 2 4 3 1 1 2 4 3 11 0 0 2 11 - 1 2 4 3 1 1 2 4 3 12 0 0 2 12 - 1 2 4 3 1 1 2 4 3 13 0 0 2 13 - 1 2 4 17 3 1 1 2 1 3 1 0 0 3 1 - 1 2 4 3 1 1 2 1 3 2 0 0 3 2 - 1 2 4 3 1 1 2 1 3 3 0 0 3 3 - 1 2 4 3 1 1 2 2 3 4 0 0 3 4 - 1 2 4 3 1 1 2 2 3 5 0 0 3 5 - 1 2 4 3 1 1 2 2 3 6 0 0 3 6 - 1 2 4 3 1 1 2 3 3 7 0 0 3 7 - 1 2 4 3 1 1 2 3 3 8 0 0 3 8 - 1 2 4 3 1 1 2 3 3 9 0 0 3 9 - 1 2 4 3 1 1 2 4 3 10 0 0 3 10 - 1 2 4 3 1 1 2 4 3 11 0 0 3 11 - 1 2 4 3 1 1 2 4 3 12 0 0 3 12 - 1 2 4 3 1 1 2 4 3 13 0 0 3 13 - 1 2 4 3 1 1 2 5 3 14 0 0 1 15 - 1 2 4 3 1 1 2 5 3 15 0 0 2 15 - 1 2 4 3 1 1 2 5 3 16 0 0 3 15 - 1 2 4 3 1 1 2 5 3 17 0 0 4 15 - 1 2 4 12 3 1 1 2 1 3 1 0 0 4 1 - 1 2 4 3 1 1 2 1 3 2 0 0 4 2 - 1 2 4 3 1 1 2 1 3 3 0 0 4 3 - 1 2 4 3 1 1 2 2 3 4 0 0 4 4 - 1 2 4 3 1 1 2 2 3 5 0 0 4 5 - 1 2 4 3 1 1 2 2 3 6 0 0 4 6 - 1 2 4 3 1 1 2 3 3 7 0 0 4 7 - 1 2 4 3 1 1 2 3 3 8 0 0 4 8 - 1 2 4 3 1 1 2 3 3 9 0 0 4 9 - 1 2 4 3 1 1 2 4 3 10 0 0 4 10 - 1 2 4 3 1 1 2 4 3 11 0 0 4 11 - 1 2 4 3 1 1 2 4 3 12 0 0 4 12 - 1 2 4 *************************************************** * 10. BRAKES *************************************************** 200 13 4 1 1 2 1 3 1 4 1 6 2 - 6 2 3 4 4 1 1 2 1 3 1 4 2 6 3 - 6 2 3 4 4 1 1 2 1 3 2 4 3 6 4 - 6 2 3 4 4 1 1 2 1 3 2 4 4 6 5 - 6 2 3 4 4 1 1 2 2 3 3 4 5 6 6 - 6 2 3 4 4 1 1 2 2 3 3 4 6 6 7 - 6 2 3 4 4 1 1 2 2 3 4 4 7 6 8 - 6 2 3 4 4 1 1 2 2 3 4 4 8 6 9 - 6 2 3 4 4 1 1 2 3 3 5 4 9 6 10 - 6 2 3 4 4 1 1 2 3 3 5 4 10 6 11 - 6 2 3 4 4 1 1 2 3 3 6 4 11 6 12 - 6 2 3 4 4 1 1 2 3 3 6 4 12 6 13 - 6 2 3 4 4 1 1 2 3 3 6 4 13 6 14 - 6 2 3 4 * Brake distribution 0 25 55 70 100 0 0 0 0 0 *************************************************** * 11. Ramification lengths *************************************************** 3 180 4 300 150 3 100 4 180 80 *************************************************** * 12. H V and VH ribs *************************************************** 12 80 150 1 16 3 8.5 0. 2.2 1.8 4 8.5 0. 2.2 1.8 2 16 6 8.5 0. 2.2 1.8 7 8.5 0. 2.2 1.8 3 16 9 8.5 0. 2.2 1.8 10 8.5 0. 2.2 1.8 4 16 3 30.0 0. 2.0 2.0 4 30.0 0. 2.0 2.0 5 16 6 30.0 0. 2.0 2.0 7 30.0 0. 2.0 2.0 6 16 9 30.0 0. 2.0 2.0 10 30.0 0. 2.0 2.0 7 16 3 53.0 0. 2.0 2.0 4 53.0 0. 2.0 2.0 8 16 6 53.0 0. 2.0 2.0 7 53.0 0. 2.0 2.0 9 16 9 53.0 0. 2.0 2.0 10 53.0 0. 2.0 2.0 10 16 3 77. 0. 2.0 2.0 4 77. 0. 2.0 2.0 11 16 6 77. 0. 2.0 2.0 7 77. 0. 2.0 2.0 12 16 9 77. 0. 2.0 2.0 10 77. 0. 2.0 2.0 ***************************************************** * 15. Extrados colors ***************************************************** 3 1 1 1 40.1 0. 2 1 1 20.15 0. 3 1 1 0.0 0. ***************************************************** * 16. Intrados colors ***************************************************** 1 1 1 1 0. 0. ***************************************************** * 17. Aditional rib points ***************************************************** 0 ***************************************************** * 18. Elastic lines corrections ***************************************************** 100 75 25 40 40 20 35 35 20 10 35 35 15 10 5 1 0.08 0.2 0.2 2 0.08 0.2 0.2 3 0.08 0.2 0.2 4 0.08 0.2 0.2 5 0.08 0.2 0.2 ****************************************************** * 19. DXF layer names ****************************************************** 10 general default line-external cutexternal line-sewing cutinternal points points circles circles triangles triangle square square text text reference refer notes notes ****************************************************** * 20. Marks types ****************************************************** 10 typepoint 1 0.25 1.2 2 0.3 1.2 typepoint2 1 0.25 1.2 2 0.2 1.2 typepoint3 1 0.25 1.2 2 0.2 1.2 typevent 1 10. 0.0 2 2.0 0.0 typetab 1 10. 0.0 3 2.0 0.0 typejonc 1 10. 0.0 2 2.0 0.0 typeref 1 5.0 1. 1 2.0 0.0 type8 1 0.2 5.0 1 0.0 5.0 type9 1 0.0 7.0 1 3.2 4.5 type10 1 0.0 6.0 1 0.0 3.33 ******************************************************* * 21. JONCS DEFINITION (NYLON RODS) ******************************************************* 1 2 1 1 10 4.2 10.8 1.36 2.0 3.67 10.8 0.79 2.0 0.0 9.35 6.3 9.35 2 11 14 4.2 10.8 1.36 2.0 3.67 10.8 0.79 2.0 0.0 9.35 6.3 9.35 ******************************************************* * 22. NOSE MYLARS DEFINITION ******************************************************* 0 ******************************************************* * 23. TAB REINFORCEMENTS ******************************************************* 0 ******************************************************* * 24. GENERAL 2D DXF OPTIONS ******************************************************* 1 A_lines_color 1 red B_lines_color 30 orange C_lines_color 3 green D_lines_color 4 cyan E_lines_color 6 magenta F_lines_color 2 yellow ******************************************************* * 25. GENERAL 3D DXF OPTIONS ******************************************************* 1 A_lines_color 1 red B_lines_color 30 orange C_lines_color 3 green D_lines_color 4 cyan E_lines_color 8 grey F_lines_color 6 magenta Extrados 1 5 blue Vents 0 1 red Intrados 1 3 green ******************************************************* * 26. GLUE VENTS ******************************************************* 1 1 0 2 0 3 0 4 0 5 0 6 0 7 0 8 0 9 0 10 0 11 0 12 0 13 -2 14 -1 15 -1 ******************************************************* * 27. SPECIAL WING TIP ******************************************************* 0 ******************************************************* * 28. PARAMETERS FOR CALAGE VARIATION ******************************************************* 1 4 8.5 30.0 53 77 0 0 -4 4 4 4 ******************************************************* * 29. 3D SHAPING ******************************************************* 1 1 groups 1 group 1 1 15 upper 0 1 lower 0 1 * Print parameters Inter3D 0 1 15 1 Ovali3D 0 1 15 0 tesse3D 0 1 15 1 exteDXF 0 1 15 1 exteSTL 1 1 15 1 ******************************************************* * 30. AIRFOIL THICKNESS MODIFICATION ******************************************************* 1 1 0.844 2 0.87 3 0.9 4 0.9 5 0.9 6 0.9 7 0.9 8 0.9 9 0.9 10 0.9 11 0.9 12 0.9 13 0.9 14 0.8 15 0.1 ******************************************************* * 31. NEW SKIN TENSION MODULE ******************************************************* 1 1 * Skin tension group number "1" from rib 1 to 15, 11 points, type "1" 1 1 15 11 1 1 0. 0.05 0. 0. 2 3.5 0.1 10. 0.525 3 7.0 0.5 20. 1.25 4 14. 1.3 30. 1.875 5 19 2.38 35 2.1875 6 21.5 2.6 40. 2.5 7 65. 2.6 65. 2.5 8 72.5 2.4 70. 2.4 9 80. 2.0 75. 2.3 10 90. 0.8 87.5 1.15 11 100. 0.0 100. 0.1 ******************************************************* * 32. PARAMETERS FOR PARTS SEPARATION ******************************************************* 1 panel_x 1.9 panel_x_min 1.0 panel_y 0.8 rib_x 1.0 rib_y 1.0 rib_1y 1.8 parameter7 1.0 parameter8 1.0 parameter9 1.0 parameter10 1.0 ******************************************************* * 33. DETAILED RISERS ******************************************************* 1 1 A 45.0 cm B 45.0 cm C 55.0 cm D 65.0 cm ******************************************************* * 34. LINES CHARACTERISTICS TABLE ******************************************************* 1 6 1 r 25. 2. Riser 1000 daN polyester 20.0 g s 12. cm 7 2 c 1.90 Line275 275 daN s_dyneem 2.26 g s 12. cm 1 3 c 1.40 Line160 160 daN s_dyneem 1.34 g s 10. cm 3 4 c 1.15 Line120 120 daN s_dyneem 1.00 g s 10. cm 5 5 c 0.80 Line100U 100 daN u_dyneem 0.43 g p 8. cm 2 6 c 2.00 Line200B 200 daN s_dynemm 3.10 g s 12. cm 6 ******************************************************* * 35. SOLVE EQUILIBRIUM EQUATIONS ******************************************************* 1 g 9.807 m/s2 gravity of Earth ro 1.225 kg/m3 air mass density mu 18.46 muPa·s air dynamic viscosity (microPascals) V 11.0 m/s estimated flow speed Alpha 9.0 deg estimated wing angle of attack at trim speed Cl 0.59885 wing lift coefficient cle 1.0 lift correction coefficient Cd 0.04285 wing drag coefficient cde 1.10 drag correction coefficient Cm 0.0 wing moment coefficient Spilot 0.50 m2 pilot+harness frontal surface Cdpilot 0.8 pilot+harness drag coefficient Mw 4.0 kg wing mass Mp 85.0 kg pilot mass included harness and instruments Pmc 0.0 m pilot mass center below main karabiners Mql 8.0 g one quick link mass (riser-lines) Ycp 0.850 m y-coordinate center of pressure Zcp 0.404 m z-coordinate center of pressure ******************************************************* * 36. CREATE FILES FOR XFLR5 ANALYSIS ******************************************************* 1 * Panel parameters 15 chord nr 5 per cell 1 cosine distribution along chord 0 uniform along span * Include billowed airfoils (more accuracy) 0 ******************************************************* * 37. SOME SPECIAL PARAMETERS ******************************************************* 1 6 1291 12 nsegments in transverse direction (stl surfaces) 1341 0 use CAD colors for each line type according table 34 1146 36. gravity center in % of a typical section (default is 36%) 1351 6 Solve method (1 or 6) 1352 2 Use flat area (1) or projected area (2) 1353 2 Print normal (0) or advanced detailed output (1),(2)