************************************************************** * LABORATORI D'ENVOL PARAGLIDING DESIGN * * Input data file 3.27 version * ************************************************************** * 20251205 ************************************************************** * 1. GEOMETRY * ************************************************************** * Brand name "Laboratori d'envol" * Wing name "Swoop" * Drawing scale 1.5 * Wing scale 0.847342687 * Number of cells 50 * Number of ribs 51 * Alpha wingtip, parameter, (alpha center) 6.0 1 0.0 * Paraglider type and parameter "ds" 0 * Rib geometric parameters * Rib x-rib y-LE y-TE xp z beta RP Washin z_rot z_pos 1 0.00 -0.00 246.74 0.00 0.00 0.00 33.33 0.00 0.00 50.0 2 29.39 0.19 246.69 29.38 0.66 2.54 33.33 0.00 0.19 50.0 3 58.73 0.77 246.55 58.65 2.64 5.17 33.33 0.00 0.38 50.0 4 87.96 1.72 246.32 87.69 5.92 7.81 33.33 0.00 0.57 50.0 5 117.06 3.06 245.99 116.43 10.48 10.25 33.33 0.00 0.75 50.0 6 145.97 4.78 245.58 144.76 16.27 12.88 33.33 0.00 0.94 50.0 7 174.67 6.89 245.07 172.59 23.26 15.33 33.33 0.00 1.12 50.0 8 203.11 9.38 244.47 199.84 31.38 17.77 33.33 0.00 1.29 50.0 9 231.26 12.25 243.79 226.42 40.64 20.58 33.33 0.00 1.49 50.0 10 259.07 15.52 243.02 252.18 51.09 23.46 33.33 0.00 1.68 50.0 11 286.50 19.18 242.17 277.05 62.68 26.34 33.33 0.00 1.88 50.0 12 313.51 23.24 241.24 300.94 75.28 29.22 33.33 0.00 2.06 50.0 13 340.07 27.71 240.23 323.79 88.81 32.11 33.33 0.00 2.25 50.0 14 366.13 32.59 239.15 345.55 103.14 34.78 33.33 0.00 2.41 50.0 15 391.65 37.90 237.99 366.18 118.15 37.45 33.33 0.00 2.57 50.0 16 416.59 43.65 236.77 385.63 133.76 40.24 33.33 0.00 2.73 50.0 17 440.90 49.88 235.49 403.69 150.03 43.71 33.33 0.00 2.92 50.0 18 464.51 56.99 234.15 420.28 166.82 47.01 33.33 0.00 3.09 50.0 19 487.32 65.13 232.77 435.37 183.93 50.16 33.33 0.00 3.25 50.0 20 509.26 74.26 231.40 448.97 201.14 53.29 33.33 0.00 3.39 50.0 21 530.25 84.35 230.20 461.09 218.28 56.47 33.33 0.00 3.52 50.0 22 550.24 95.40 229.17 471.52 235.32 60.51 33.33 0.00 3.68 50.0 23 569.15 107.44 228.30 480.27 252.08 64.36 33.33 0.00 3.81 50.0 24 586.90 120.57 227.56 487.45 268.31 67.99 33.33 0.00 3.92 50.0 25 603.40 134.98 226.95 493.20 283.77 71.23 33.33 0.00 4.00 50.0 26 618.50 151.20 226.43 499.06 303.31 74.26 33.33 0.00 4.07 50.0 ************************************************************** * 2. AIRFOILS * ************************************************************** * Airfoil name. intake in. intake out. open. disp rweight 1 gnuReflex.txt 3.0 6.0 1 0 1 17 2 gnuReflex.txt 3.0 6.0 1 0 1 17 3 gnuReflex.txt 3.0 6.0 1 0 1 17 4 gnuReflex.txt 3.0 6.0 1 0 1 17 5 gnuReflex.txt 3.0 6.0 1 0 1 17 6 gnuReflex.txt 3.0 6.0 1 0 1 15 7 gnuReflex.txt 3.0 6.0 1 0 1 15 8 gnuReflex.txt 3.0 6.0 1 0 1 15 9 gnuReflex.txt 3.0 6.0 1 0 1 15 10 gnuReflex.txt 3.0 6.0 1 0 1 15 11 gnuReflex.txt 3.0 6.0 1 0 1 15 12 gnuReflex.txt 3.0 6.0 1 0 1 15 13 gnuReflex.txt 3.0 6.0 1 0 1 15 14 gnuReflex.txt 3.0 6.0 1 0 1 15 15 gnuReflex.txt 3.0 6.0 1 0 1 15 16 gnuReflex.txt 3.0 6.0 1 0 1 15 17 gnuReflex.txt 3.0 6.0 1 0 1 15 18 gnuReflex.txt 3.0 6.0 1 0 1 15 19 gnuReflex.txt 3.0 6.0 1 0 1 15 20 gnuReflex.txt 3.0 6.0 1 0 1 15 21 gnuReflex.txt 3.0 6.0 1 0 1 15 22 gnuReflex.txt 3.0 6.0 1 0 1 15 23 gnuReflex.txt 3.0 6.0 0 0 1 15 24 gnuReflex.txt 3.0 6.0 0 0 1 15 25 gnuReflex.txt 3.0 6.0 0 0 1 15 26 gnuReflex.txt 3.0 6.0 0 0 1 1 ************************************************************* * 3. ANCHOR POINTS * ************************************************************* * Airf Anch A B C D E F 1 3 10 37 72 0 0 0 2 3 10 37 72 0 0 100 3 3 10 37 72 0 0 100 4 3 10 37 72 0 0 100 5 3 10 37 72 0 0 100 6 3 10 37 72 0 0 100 7 3 10 37 72 0 0 100 8 3 10 37 72 0 0 100 9 3 10 37 72 0 0 100 10 3 10 37 72 0 0 100 11 3 10 37 72 0 0 100 12 3 10 37 72 0 0 100 13 3 10 37 72 0 0 100 14 3 10 37 72 0 0 100 15 3 10 37 72 0 0 100 16 3 10 37 72 0 0 100 17 3 10 37 72 0 0 100 18 3 10 37 72 0 0 100 19 3 10 37 72 0 0 100 20 3 10 37 72 0 0 100 21 3 10 37 72 0 0 100 22 3 10 37 72 0 0 100 23 3 10 37 72 0 0 100 24 3 10 37 72 0 0 100 25 3 10 37 72 0 0 100 26 3 5. 40 77 0 0 0 ************************************************************* * 4. AIRFOIL HOLES * ************************************************************* 1 1 25 9 1 14.69 2.90 2.05 5.0 0. 0. 0. 0. 1 22.0 2.07 3.07 7.15 0. 0. 0. 0. 1 29.3 2.07 2.05 5.3 0. 0. 0. 0. 1 42.5 0.52 2.05 3.82 0. 0. 0. 0. 1 50.0 0.52 2.84 4.89 0. 0. 0. 0. 1 57.48 0.52 2.05 3.82 0. 0. 0. 0. 1 65.45 0.00 2.05 2.8 0. 0. 0. 0. 1 79.00 -0.53 1.62 1.62 0. 0. 0. 0. 1 84.53 -0.55 1.3 1.3 0. 0. 0. 0. ************************************************************* * 5. SKIN TENSION * ************************************************************* Extrados 0. 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 * ************************************************************* 10 10 20 upper panels (mm) 10 10 20 lower panels (mm) 10 ribs (mm) 10 vribs (mm) ************************************************************* * 7. MARKS ************************************************************* 25. 0.5 0.15 ************************************************************ * 8. Global angle of attack estimation * ************************************************************* * Finesse GR 10.0 * Plumb point % of chord 38 * Calage % 30 * Risers lenght cm 47 * Line lenght cm (without risers) 708 * Karabiners cm 42 *************************************************** * 9. SUSPENSION LINES DESCRIPTION *************************************************** 3 3 12 4 1 1 2 1 3 1 4 1 1 2 4 1 1 2 1 3 1 4 2 1 3 4 1 1 2 1 3 2 4 3 1 6 4 1 1 2 1 3 2 4 4 1 7 4 1 1 2 2 3 3 4 5 1 10 4 1 1 2 2 3 3 4 6 1 11 4 1 1 2 2 3 4 4 7 1 14 4 1 1 2 2 3 4 4 8 1 15 4 1 1 2 3 3 5 4 9 1 18 4 1 1 2 3 3 5 4 10 1 19 4 1 1 2 3 3 6 4 11 1 22 4 1 1 2 3 3 6 4 12 1 23 12 4 1 1 2 1 3 1 4 1 2 2 4 1 1 2 1 3 1 4 2 2 3 4 1 1 2 1 3 2 4 3 2 6 4 1 1 2 1 3 2 4 4 2 7 4 1 1 2 2 3 3 4 5 2 10 4 1 1 2 2 3 3 4 6 2 11 4 1 1 2 2 3 4 4 7 2 14 4 1 1 2 2 3 4 4 8 2 15 4 1 1 2 3 3 5 4 9 2 18 4 1 1 2 3 3 5 4 10 2 19 4 1 1 2 3 3 6 4 11 2 22 4 1 1 2 3 3 6 4 12 2 23 16 4 1 1 2 1 3 1 4 1 3 2 4 1 1 2 1 3 1 4 2 3 3 4 1 1 2 1 3 2 4 3 3 6 4 1 1 2 1 3 2 4 4 3 7 4 1 1 2 2 3 3 4 5 3 10 4 1 1 2 2 3 3 4 6 3 11 4 1 1 2 2 3 4 4 7 3 14 4 1 1 2 2 3 4 4 8 3 15 4 1 1 2 3 3 5 4 9 3 18 4 1 1 2 3 3 5 4 10 3 19 4 1 1 2 3 3 6 4 11 3 22 4 1 1 2 3 3 6 4 12 3 23 3 1 1 2 4 3 7 0 0 1 25 3 1 1 2 4 3 8 0 0 1 26 3 1 1 2 4 3 9 0 0 2 26 3 1 1 2 4 3 10 0 0 3 26 *************************************************** * 10. BRAKES *************************************************** 300 12 4 1 1 2 1 3 1 4 1 6 2 4 1 1 2 1 3 1 4 2 6 4 4 1 1 2 1 3 2 4 3 6 6 4 1 1 2 1 3 2 4 4 6 8 4 1 1 2 2 3 3 4 5 6 10 4 1 1 2 2 3 3 4 6 6 12 4 1 1 2 2 3 4 4 7 6 14 4 1 1 2 2 3 4 4 8 6 16 4 1 1 2 3 3 5 4 9 6 18 4 1 1 2 3 3 5 4 10 6 20 4 1 1 2 3 3 6 4 11 6 22 4 1 1 2 3 3 6 4 12 6 24 * Brake distribution 0 25 50 80 100 0 0 0 0 0 *************************************************** * 11. Ramification lengths *************************************************** 3 180 4 275 100 3 135 4 200 80 *************************************************** * 12. H V and VH ribs *************************************************** 123 80 150 1 11 1 1 2 1 2.0 0 0 0 2 11 2 1 3 1 2.0 0 0 0 3 11 3 1 4 1 2.0 0 0 0 4 11 4 1 5 1 2.0 0 0 0 5 11 5 1 6 1 2.0 0 0 0 6 11 6 1 7 1 2.0 0 0 0 7 11 7 1 8 1 2.0 0 0 0 8 11 8 1 9 1 2.0 0 0 0 9 11 9 1 10 1 2.0 0 0 0 10 11 10 1 11 1 2.0 0 0 0 11 11 11 1 12 1 2.0 0 0 0 12 11 12 1 13 1 2.0 0 0 0 13 11 13 1 14 1 2.0 0 0 0 14 11 14 1 15 1 2.0 0 0 0 15 11 15 1 16 1 2.0 0 0 0 16 11 16 1 17 1 2.0 0 0 0 17 11 17 1 18 1 2.0 0 0 0 18 11 18 1 19 1 2.0 0 0 0 19 11 19 1 20 1 2.0 0 0 0 20 11 20 1 21 1 2.0 0 0 0 21 11 21 1 22 1 2.0 0 0 0 22 11 22 1 23 1 2.0 0 0 0 23 11 23 1 24 1 2.0 0 0 0 24 11 1 2 2 2 2.0 0 0 0 25 11 2 2 3 2 2.0 0 0 0 26 11 3 2 4 2 2.0 0 0 0 27 11 4 2 5 2 2.0 0 0 0 28 11 5 2 6 2 2.0 0 0 0 29 11 6 2 7 2 2.0 0 0 0 30 11 7 2 8 2 2.0 0 0 0 31 11 8 2 9 2 2.0 0 0 0 32 11 9 2 10 2 2.0 0 0 0 33 11 10 2 11 2 2.0 0 0 0 34 11 11 2 12 2 2.0 0 0 0 35 11 12 2 13 2 2.0 0 0 0 36 11 13 2 14 2 2.0 0 0 0 37 11 14 2 15 2 2.0 0 0 0 38 11 15 2 16 2 2.0 0 0 0 39 11 16 2 17 2 2.0 0 0 0 40 11 17 2 18 2 2.0 0 0 0 41 11 18 2 19 2 2.0 0 0 0 42 11 19 2 20 2 2.0 0 0 0 43 11 20 2 21 2 2.0 0 0 0 44 11 21 2 22 2 2.0 0 0 0 45 11 22 2 23 2 2.0 0 0 0 46 11 23 2 24 2 2.0 0 0 0 47 11 1 3 2 3 2.0 0 0 0 48 11 2 3 3 3 2.0 0 0 0 49 11 3 3 4 3 2.0 0 0 0 50 11 4 3 5 3 2.0 0 0 0 51 11 5 3 6 3 2.0 0 0 0 52 11 6 3 7 3 2.0 0 0 0 53 11 7 3 8 3 2.0 0 0 0 54 11 8 3 9 3 2.0 0 0 0 55 11 9 3 10 3 2.0 0 0 0 56 11 10 3 11 3 2.0 0 0 0 57 11 11 3 12 3 2.0 0 0 0 58 11 12 3 13 3 2.0 0 0 0 58 11 13 3 14 3 2.0 0 0 0 60 11 14 3 15 3 2.0 0 0 0 61 11 15 3 16 3 2.0 0 0 0 62 11 16 3 17 3 2.0 0 0 0 63 11 17 3 18 3 2.0 0 0 0 64 11 18 3 19 3 2.0 0 0 0 65 11 19 3 20 3 2.0 0 0 0 66 11 20 3 21 3 2.0 0 0 0 67 11 21 3 22 3 2.0 0 0 0 68 11 22 3 23 3 2.0 0 0 0 69 11 23 3 24 3 2.0 0 0 0 70 16 1 10. 100. 6.0 10.0 2 10. 0. 2.0 2.0 71 16 3 10. 0. 2.0 2.0 4 10. 100. 6.0 10.0 72 16 4 10. 100. 6.0 10.0 5 10. 100. 6.0 10.0 73 16 5 10. 100. 6.0 10.0 6 10. 0. 2.0 2.0 74 16 7 10. 0. 2.0 2.0 8 10. 100. 6.0 10.0 75 16 8 10. 100. 6.0 10.0 9 10. 100. 6.0 10.0 76 16 9 10. 100. 6.0 10.0 10 10. 0. 2.0 2.0 77 16 11 10. 0. 2.0 2.0 12 10. 100. 6.0 10.0 78 16 12 10. 100. 6.0 10.0 13 10. 100. 6.0 10.0 79 16 13 10. 100. 6.0 10.0 14 10. 0. 2.0 2.0 80 16 15 10. 0. 2.0 2.0 16 10. 100. 6.0 10.0 81 16 16 10. 100. 6.0 10.0 17 10. 100. 6.0 10.0 82 16 17 10. 100. 6.0 10.0 18 10. 0. 2.0 2.0 83 16 19 10. 0. 2.0 2.0 20 10. 100. 6.0 10.0 84 16 20 10. 100. 6.0 10.0 21 10. 100. 6.0 10.0 85 16 21 10. 100. 6.0 10.0 22 10. 0. 2.0 2.0 86 16 23 10. 0. 2.0 2.0 24 10. 100. 6.0 10.0 87 16 24 10. 100. 6.0 10.0 25 10. 0. 2.0 2.0 88 16 1 37. 100. 10.0 10.0 2 37. 0. 2.0 2.0 89 16 3 37. 0. 2.0 2.0 4 37. 100. 10.0 10.0 90 16 4 37. 100. 10.0 10.0 5 37. 100. 10.0 10.0 91 16 5 37. 100. 10.0 10.0 6 37. 0. 2.0 2.0 92 16 7 37. 0. 2.0 2.0 8 37. 100. 10.0 10.0 93 16 8 37. 100. 10.0 10.0 9 37. 100. 10.0 10.0 94 16 9 37. 100. 10.0 10.0 10 37. 0. 2.0 2.0 95 16 11 37. 0. 2.0 2.0 12 37. 100. 10.0 10.0 96 16 12 37. 100. 10.0 10.0 13 37. 100. 10.0 10.0 97 16 13 37. 100. 10.0 10.0 14 37. 0. 2.0 2.0 98 16 15 37. 0. 2.0 2.0 16 37. 100. 10.0 10.0 99 16 16 37. 100. 10.0 10.0 17 37. 100. 10.0 10.0 100 16 17 37. 100. 10.0 10.0 18 37. 0. 2.0 2.0 101 16 19 37. 0. 2.0 2.0 20 37. 100. 10.0 10.0 102 16 20 37. 100. 10.0 10.0 21 37. 100. 10.0 10.0 103 16 21 37. 100. 10.0 10.0 22 37. 0. 2.0 2.0 104 16 23 37. 0. 2.0 2.0 24 37. 100. 10.0 10.0 105 16 24 37. 100. 10.0 10.0 25 37. 0. 2.0 2.0 106 16 1 72. 100. 10.0 10.0 2 72. 0. 2.0 2.0 107 16 3 72. 0. 2.0 2.0 4 72. 100. 10.0 10.0 108 16 4 72. 100. 10.0 10.0 5 72. 100. 10.0 10.0 109 16 5 72. 100. 10.0 10.0 6 72. 0. 2.0 2.0 110 16 7 72. 0. 2.0 2.0 8 72. 100. 10.0 10.0 111 16 8 72. 100. 10.0 10.0 9 72. 100. 10.0 10.0 112 16 9 72. 100. 10.0 10.0 10 72. 0. 2.0 2.0 113 16 11 72. 0. 2.0 2.0 12 72. 100. 10.0 10.0 114 16 12 72. 100. 10.0 10.0 13 72. 100. 10.0 10.0 115 16 13 72. 100. 10.0 10.0 14 72. 0. 2.0 2.0 116 16 15 72. 0. 2.0 2.0 16 72. 100. 10.0 10.0 117 16 16 72. 100. 10.0 10.0 17 72. 100. 10.0 10.0 118 16 17 72. 100. 10.0 10.0 18 72. 0. 2.0 2.0 119 16 19 72. 0. 2.0 2.0 20 72. 100. 10.0 10.0 120 16 20 72. 100. 10.0 10.0 21 72. 100. 10.0 10.0 121 16 21 72. 100. 10.0 10.0 22 72. 0. 2.0 2.0 122 16 23 72. 0. 2.0 2.0 24 72. 100. 10.0 10.0 123 16 24 72. 100. 10.0 10.0 25 72. 0. 2.0 2.0 ***************************************************** * 15. Extrados colors ***************************************************** 26 1 1 1 63. 0. 2 1 1 63. 0. 3 1 1 63. 0. 4 1 1 63. 0. 5 1 1 63. 0. 6 1 1 63. 0. 7 1 1 63. 0. 8 1 1 63. 0. 9 1 1 63. 0. 10 1 1 63. 0. 11 1 1 63. 0. 12 1 1 63. 0. 13 1 1 63. 0. 14 1 1 63. 0. 15 1 1 63. 0. 16 1 1 63. 0. 17 1 1 63. 0. 18 1 1 63. 0. 19 1 1 63. 0. 20 1 1 63. 0. 21 1 1 63. 0. 22 1 1 63. 0. 23 1 1 63. 0. 24 1 1 63. 0. 25 1 1 63. 0. 26 1 1 63. 0. *****************************************************S * 16. Intrados colors ***************************************************** 26 1 1 1 48. 0. 2 1 1 55.5 0. 3 1 1 63. 0. 4 1 1 63. 0. 5 1 1 63. 0. 6 1 1 63. 0. 7 1 1 63. 0. 8 1 1 63. 0. 9 1 1 63. 0. 10 1 1 63. 0. 11 1 1 63. 0. 12 1 1 63. 0. 13 1 1 63. 0. 14 1 1 63. 0. 15 1 1 63. 0. 16 1 1 63. 0. 17 1 1 63. 0. 18 1 1 63. 0. 19 1 1 63. 0. 20 1 1 63. 0. 21 1 1 63. 0. 22 1 1 63. 0. 23 1 1 63. 0. 24 1 1 63. 0. 25 1 1 63. 0. 26 1 1 63. 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 5.5 1 0.0 3.9 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 1 1 1 25 5.5 10. 1.5 2.0 5. 14. 2.2 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 5 blue ******************************************************* * 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 0 3 green ******************************************************* * 26. GLUE VENTS ******************************************************* 1 1 -4 0.0 0.0 2 -4 67.0 0.0 3 -4 0.0 67.0 4 -4 67.0 0.0 5 -4 0.0 67.0 6 -4 67.0 0.0 7 -4 0.0 67.0 8 -4 67.0 0.0 9 -4 0.0 67.0 10 -4 67.0 0.0 11 -4 0.0 67.0 12 -4 67.0 0.0 13 -4 0.0 67.0 14 -4 67.0 0.0 15 -4 0.0 67.0 16 -4 67.0 0.0 17 -4 0.0 67.0 18 -4 67.0 0.0 19 -4 0.0 67.0 20 -4 67.0 0.0 21 -4 0.0 67.0 22 -4 67.0 0.0 23 -4 0.0 100.0 24 -1 25 -1 26 -1 ******************************************************* * 27. SPECIAL WING TIP ******************************************************* 1 AngleLE 55. AngleTE 5. ******************************************************* * 28. PARAMETERS FOR CALAGE VARIATION ******************************************************* 1 4 10. 30.35 49.29 76.27 0 0 -3.0 10 5.0 20 ******************************************************* * 29. 3D SHAPING ******************************************************* 1 1 groups 1 group 1 1 26 upper 0 1 lower 0 1 * Print parameters Inter3D 0 1 26 1 Ovali3D 1 1 26 0 tesse3D 0 1 26 1 exteDXF 0 1 26 1 exteSTL 1 1 26 1 ******************************************************* * 30. AIRFOIL THICKNESS MODIFICATION ******************************************************* 1 1 1.0 2 1.0 3 1.0 4 1.0 5 1.0 6 1.0 7 1.0 8 1.0 9 1.0 10 1.0 11 1.0 12 1.0 13 1.0 14 1.0 15 1.0 16 1.0 17 1.0 18 1.0 19 1.0 20 1.0 21 1.0 22 1.0 23 1.0 24 1.0 25 1.0 26 0.01 ******************************************************* * 31. NEW SKIN TENSION MODULE ******************************************************* 1 1 * Skin tension group number "1" from rib 1 to 26, 14 points, type "1" 1 1 27 14 1 1 0. 0.03 0. 0. 2 5. 0.4 10. 0.625 3 10.0 1.0 20. 1.25 4 15. 1.94 30. 1.875 5 17.5 2.93 35 2.1875 6 20. 3.32 40. 2.5 7 25. 3.5 65. 2.5 8 50. 3.5 70. 2.4 9 55. 3.33 75. 2.3 10 65. 2.77 80. 2.0 11 70. 2.35 85. 1.5 12 90. 0.67 90. 0.9 13 95. 0.19 95. 0.3 14 100. 0.0 100. 0.03 ******************************************************* * 32. PARAMETERS FOR PARTS SEPARATION ******************************************************* 1 panel_x 1.2 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 ******************************************************* 0 ******************************************************* * 34. LINES CHARACTERISTICS TABLE ******************************************************* 1 6 1 c 5.0 Riser 1000 daN u_dyneem 10.0 g p 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 ******************************************************* 0 ******************************************************* * 36. CREATE FILES FOR XFLR5 ANALYSIS ******************************************************* 0 ******************************************************* * 37. SOME SPECIAL PARAMETERS ******************************************************* 1 1 1341 1 use CAD colors for each line type according table 34 ******************************************************* * 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 12.4 m/s estimated flow speed Alpha 7.00 deg estimated wing angle of attact at trim speed Cl 0.67913 wing lift coefficient cle 1.0 lift correction coefficient Cd 0.03790 wing drag coefficient cde 1.1 drag correction coefficient Cm 0.0 wing moment coefficient Spilot 0.438 m2 pilot+harness frontal surface Cdpilot 0.6 pilot+harness drag coefficient Mw 5.0 kg wing mass Mp 85.0 kg pilot mass included harness and instruments Pmc 0.2 m pilot mass center below main karabiners Mql 8.0 g one quick link mass (riser-lines) Ycp 0.575 m y-coordinate center of pressure Zcp 0.395 m z-coordinate center of pressure ******************************************************* * 36. CREATE FILES FOR XFLR5 ANALYSIS ******************************************************* 1 * Panel parameters 10 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 8 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 1 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)