D.G.A. 1138 (dga1138-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: D.G.A. 1138 (dga1138-il) Reynolds number: 100,000 Max Cl/Cd: 54.54 at α=3.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-dga1138-il-100000.txt Download as CSV file: xf-dga1138-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: D.G.A. 1138
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.4823 0.10431 0.09928 -0.0131 1.0000 0.0869
-9.250 -0.4919 0.10200 0.09707 -0.0176 1.0000 0.0903
-9.000 -0.5058 0.09965 0.09482 -0.0248 1.0000 0.0911
-8.750 -0.4783 0.09463 0.08975 -0.0164 1.0000 0.0997
-8.500 -0.4886 0.09209 0.08730 -0.0223 1.0000 0.1034
-8.250 -0.4875 0.08765 0.08290 -0.0247 1.0000 0.1060
-8.000 -0.4749 0.08455 0.07979 -0.0209 1.0000 0.1117
-7.750 -0.4807 0.08211 0.07723 -0.0352 1.0000 0.1182
-7.500 -0.4682 0.07713 0.07241 -0.0262 1.0000 0.1216
-7.250 -0.4635 0.07518 0.07020 -0.0360 1.0000 0.1322
-7.000 -0.4544 0.07015 0.06540 -0.0293 1.0000 0.1351
-6.750 -0.4443 0.06740 0.06243 -0.0346 1.0000 0.1469
-6.500 -0.4360 0.06391 0.05914 -0.0288 1.0000 0.1521
-6.250 -0.4254 0.06050 0.05562 -0.0309 1.0000 0.1633
-6.000 -0.4140 0.05766 0.05277 -0.0296 1.0000 0.1707
-5.750 -0.4015 0.05412 0.04910 -0.0306 1.0000 0.1786
-5.500 -0.3855 0.05137 0.04608 -0.0320 1.0000 0.1909
-5.250 -0.3741 0.04823 0.04302 -0.0297 1.0000 0.1953
-5.000 -0.3302 0.03460 0.02737 -0.0373 1.0000 0.1045
-4.750 -0.3114 0.03117 0.02391 -0.0364 1.0000 0.1006
-4.500 -0.2860 0.02647 0.01820 -0.0359 1.0000 0.0930
-4.250 -0.2644 0.02526 0.01694 -0.0350 1.0000 0.0968
-4.000 -0.2394 0.02327 0.01449 -0.0343 1.0000 0.0967
-3.750 -0.2137 0.02168 0.01254 -0.0336 1.0000 0.0968
-3.500 -0.1882 0.02051 0.01113 -0.0330 1.0000 0.0982
-3.250 -0.1627 0.01969 0.01011 -0.0324 1.0000 0.1018
-3.000 -0.1370 0.01894 0.00929 -0.0320 1.0000 0.1066
-2.750 -0.1115 0.01832 0.00869 -0.0316 1.0000 0.1106
-2.500 -0.0861 0.01781 0.00814 -0.0311 1.0000 0.1164
-2.250 -0.0610 0.01737 0.00776 -0.0307 1.0000 0.1257
-2.000 -0.0356 0.01700 0.00750 -0.0303 1.0000 0.1468
-1.750 -0.0097 0.01657 0.00746 -0.0302 1.0000 0.2239
-1.500 0.0155 0.01637 0.00750 -0.0301 1.0000 0.3035
-1.250 0.0422 0.01604 0.00751 -0.0304 1.0000 0.3850
-1.000 0.0737 0.01463 0.00763 -0.0309 1.0000 1.0000
-0.750 0.0956 0.01494 0.00775 -0.0303 1.0000 1.0000
-0.500 0.1172 0.01529 0.00795 -0.0297 1.0000 1.0000
-0.250 0.1387 0.01567 0.00820 -0.0292 1.0000 1.0000
0.000 0.1723 0.01607 0.00848 -0.0311 0.9961 1.0000
0.250 0.2275 0.01639 0.00870 -0.0372 0.9848 1.0000
0.500 0.2803 0.01657 0.00884 -0.0426 0.9725 1.0000
0.750 0.3309 0.01665 0.00890 -0.0475 0.9596 1.0000
1.000 0.3814 0.01660 0.00888 -0.0521 0.9461 1.0000
1.250 0.4338 0.01638 0.00873 -0.0568 0.9321 1.0000
1.500 0.4891 0.01596 0.00840 -0.0618 0.9177 1.0000
1.750 0.5389 0.01548 0.00804 -0.0653 0.9024 1.0000
2.000 0.5777 0.01507 0.00774 -0.0664 0.8817 1.0000
2.250 0.6141 0.01464 0.00740 -0.0667 0.8599 1.0000
2.500 0.6420 0.01436 0.00722 -0.0655 0.8332 1.0000
2.750 0.6683 0.01409 0.00701 -0.0639 0.8036 1.0000
3.000 0.6938 0.01390 0.00686 -0.0622 0.7712 1.0000
3.250 0.7181 0.01381 0.00676 -0.0604 0.7315 1.0000
3.500 0.7410 0.01384 0.00678 -0.0584 0.6820 1.0000
3.750 0.7630 0.01399 0.00683 -0.0563 0.6184 1.0000
4.000 0.7831 0.01453 0.00691 -0.0539 0.5398 1.0000
4.250 0.8000 0.01547 0.00742 -0.0514 0.4373 1.0000
4.500 0.8150 0.01659 0.00782 -0.0490 0.3233 1.0000
4.750 0.8336 0.01769 0.00856 -0.0476 0.2714 1.0000
5.000 0.8543 0.01854 0.00928 -0.0465 0.2354 1.0000
5.250 0.8750 0.01935 0.01001 -0.0455 0.2048 1.0000
5.500 0.8952 0.02018 0.01079 -0.0445 0.1659 1.0000
5.750 0.9135 0.02148 0.01165 -0.0430 0.0857 1.0000
6.000 0.9283 0.02338 0.01339 -0.0407 0.0662 1.0000
6.250 0.9476 0.02485 0.01496 -0.0389 0.0586 1.0000
6.500 0.9657 0.02672 0.01674 -0.0374 0.0536 1.0000
6.750 0.9880 0.02814 0.01836 -0.0362 0.0493 1.0000
7.000 1.0098 0.02988 0.02020 -0.0351 0.0462 1.0000
7.250 1.0324 0.03214 0.02258 -0.0341 0.0447 1.0000
7.500 1.0550 0.03502 0.02570 -0.0332 0.0439 1.0000
7.750 1.0755 0.03825 0.02928 -0.0319 0.0437 1.0000
8.000 1.0920 0.04160 0.03314 -0.0300 0.0442 1.0000
8.250 1.1033 0.04538 0.03747 -0.0276 0.0446 1.0000
8.500 1.1102 0.04924 0.04182 -0.0252 0.0446 1.0000
8.750 1.1125 0.05327 0.04630 -0.0225 0.0446 1.0000
9.000 1.0896 0.05993 0.05385 -0.0179 0.0473 1.0000
9.250 1.0733 0.06512 0.05943 -0.0149 0.0486 1.0000
9.500 1.0543 0.06972 0.06429 -0.0121 0.0496 1.0000
9.750 1.0328 0.07406 0.06880 -0.0098 0.0505 1.0000
10.000 1.0118 0.07886 0.07374 -0.0092 0.0513 1.0000
10.250 0.9929 0.08419 0.07916 -0.0100 0.0520 1.0000
10.500 0.9778 0.08997 0.08500 -0.0117 0.0528 1.0000
10.750 0.8479 0.08720 0.08245 -0.0025 0.0531 1.0000
11.000 0.7893 0.10089 0.09628 -0.0123 0.0553 1.0000
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Polar data table (+)
Polar graphs
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