GOE 187 (SCHTTE-LANZ 2U10) AIRFOIL (goe187-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 187 (SCHTTE-LANZ 2U10) AIRFOIL (goe187-il) Reynolds number: 100,000 Max Cl/Cd: 53.66 at α=8.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe187-il-100000.txt Download as CSV file: xf-goe187-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 187 (SCHTTE-LANZ 2U10) AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-9.000 -0.3840 0.11643 0.11166 -0.0147 1.0000 0.0381
-8.750 -0.3818 0.11434 0.10964 -0.0178 1.0000 0.0383
-8.500 -0.3798 0.11208 0.10745 -0.0208 1.0000 0.0384
-8.250 -0.3748 0.10944 0.10486 -0.0249 1.0000 0.0385
-8.000 -0.3665 0.10645 0.10189 -0.0294 1.0000 0.0386
-7.750 -0.3558 0.09733 0.09281 -0.0190 1.0000 0.0406
-7.500 -0.3498 0.09395 0.08948 -0.0192 1.0000 0.0417
-7.250 -0.3439 0.09077 0.08635 -0.0205 1.0000 0.0428
-7.000 -0.3370 0.08759 0.08322 -0.0224 1.0000 0.0439
-6.750 -0.3295 0.08440 0.08005 -0.0247 1.0000 0.0452
-6.500 -0.3212 0.08124 0.07693 -0.0272 1.0000 0.0466
-6.250 -0.3121 0.07815 0.07388 -0.0299 1.0000 0.0481
-6.000 -0.3006 0.07537 0.07111 -0.0337 1.0000 0.0499
-5.750 -0.2829 0.07373 0.06934 -0.0396 1.0000 0.0512
-5.500 -0.2713 0.07245 0.06786 -0.0417 1.0000 0.0516
-5.250 -0.2747 0.06713 0.06278 -0.0389 1.0000 0.0525
-5.000 -0.2789 0.06422 0.06000 -0.0356 1.0000 0.0537
-4.750 -0.2805 0.06214 0.05799 -0.0333 1.0000 0.0552
-4.500 -0.2783 0.06016 0.05601 -0.0322 1.0000 0.0571
-4.250 -0.2563 0.05728 0.05301 -0.0353 0.9976 0.0614
-4.000 -0.2025 0.05215 0.04758 -0.0446 0.9891 0.0685
-3.750 -0.1511 0.04796 0.04306 -0.0524 0.9805 0.0817
-3.500 -0.1066 0.04391 0.03883 -0.0582 0.9723 0.0968
-3.250 -0.0667 0.04046 0.03525 -0.0627 0.9631 0.1154
-3.000 -0.0203 0.03717 0.03171 -0.0685 0.9568 0.1541
-2.750 0.0131 0.03444 0.02900 -0.0711 0.9467 0.2049
-2.500 0.0453 0.03208 0.02674 -0.0731 0.9384 0.2949
-2.250 0.0720 0.02914 0.02412 -0.0725 0.9302 0.3845
-2.000 0.0931 0.02676 0.02202 -0.0696 0.9193 0.4716
-1.750 0.1856 0.02437 0.01792 -0.0829 0.9102 0.2770
-1.500 0.2478 0.02317 0.01519 -0.0835 0.9011 0.1210
-1.250 0.2844 0.02203 0.01355 -0.0828 0.8884 0.0931
-1.000 0.3165 0.02044 0.01175 -0.0823 0.8753 0.0826
-0.750 0.3467 0.01966 0.01076 -0.0813 0.8614 0.0805
-0.500 0.3743 0.01852 0.00962 -0.0804 0.8471 0.0827
-0.250 0.4005 0.01771 0.00878 -0.0790 0.8324 0.0830
0.000 0.4259 0.01707 0.00809 -0.0776 0.8172 0.0870
0.250 0.4516 0.01660 0.00747 -0.0763 0.8017 0.0990
0.500 0.4783 0.01625 0.00698 -0.0751 0.7856 0.1165
0.750 0.5120 0.01396 0.00665 -0.0755 0.7684 1.0000
1.000 0.5373 0.01412 0.00643 -0.0742 0.7500 1.0000
1.250 0.5626 0.01427 0.00630 -0.0731 0.7319 1.0000
1.500 0.5878 0.01447 0.00627 -0.0720 0.7129 1.0000
1.750 0.6130 0.01471 0.00632 -0.0712 0.6928 1.0000
2.000 0.6387 0.01495 0.00637 -0.0704 0.6746 1.0000
2.250 0.6644 0.01523 0.00646 -0.0696 0.6566 1.0000
2.500 0.6900 0.01552 0.00664 -0.0691 0.6380 1.0000
2.750 0.7160 0.01581 0.00684 -0.0685 0.6214 1.0000
3.000 0.7421 0.01614 0.00706 -0.0681 0.6065 1.0000
3.250 0.7683 0.01648 0.00732 -0.0678 0.5928 1.0000
3.500 0.7946 0.01682 0.00761 -0.0674 0.5799 1.0000
3.750 0.8208 0.01716 0.00793 -0.0671 0.5676 1.0000
4.000 0.8469 0.01746 0.00818 -0.0667 0.5552 1.0000
4.250 0.8727 0.01771 0.00837 -0.0662 0.5419 1.0000
4.500 0.8983 0.01793 0.00855 -0.0656 0.5278 1.0000
4.750 0.9238 0.01817 0.00875 -0.0651 0.5141 1.0000
5.000 0.9495 0.01844 0.00903 -0.0646 0.5017 1.0000
5.250 0.9751 0.01878 0.00940 -0.0642 0.4898 1.0000
5.500 1.0003 0.01914 0.00982 -0.0638 0.4778 1.0000
5.750 1.0255 0.01952 0.01025 -0.0634 0.4659 1.0000
6.000 1.0507 0.01992 0.01075 -0.0630 0.4545 1.0000
6.250 1.0758 0.02032 0.01119 -0.0625 0.4429 1.0000
6.500 1.1008 0.02072 0.01163 -0.0620 0.4306 1.0000
6.750 1.1256 0.02115 0.01212 -0.0615 0.4182 1.0000
7.000 1.1495 0.02158 0.01273 -0.0609 0.4048 1.0000
7.250 1.1732 0.02201 0.01326 -0.0602 0.3902 1.0000
7.500 1.1956 0.02240 0.01382 -0.0593 0.3732 1.0000
7.750 1.2168 0.02275 0.01435 -0.0582 0.3530 1.0000
8.000 1.2372 0.02307 0.01481 -0.0569 0.3300 1.0000
8.250 1.2550 0.02339 0.01525 -0.0553 0.3004 1.0000
8.500 1.2708 0.02375 0.01565 -0.0535 0.2657 1.0000
8.750 1.2858 0.02436 0.01624 -0.0518 0.2309 1.0000
9.000 1.3006 0.02531 0.01712 -0.0503 0.2052 1.0000
9.250 1.3150 0.02641 0.01822 -0.0487 0.1866 1.0000
9.500 1.3270 0.02761 0.01944 -0.0470 0.1672 1.0000
9.750 1.3379 0.02881 0.02074 -0.0453 0.1442 1.0000
10.000 1.3476 0.03016 0.02217 -0.0435 0.1117 1.0000
10.250 1.3436 0.03261 0.02442 -0.0403 0.0815 1.0000
10.500 1.3360 0.03503 0.02684 -0.0365 0.0618 1.0000
10.750 1.3326 0.03732 0.02914 -0.0338 0.0505 1.0000
11.000 1.3271 0.03999 0.03179 -0.0317 0.0452 1.0000
11.250 1.3220 0.04288 0.03481 -0.0301 0.0425 1.0000
11.500 1.3173 0.04596 0.03804 -0.0290 0.0402 1.0000
11.750 1.3124 0.04924 0.04144 -0.0283 0.0386 1.0000
12.000 1.3070 0.05269 0.04498 -0.0277 0.0372 1.0000
12.250 1.3027 0.05605 0.04836 -0.0266 0.0360 1.0000
12.500 1.3049 0.05885 0.05131 -0.0251 0.0351 1.0000
12.750 1.3082 0.06170 0.05437 -0.0239 0.0340 1.0000
13.000 1.3089 0.06494 0.05782 -0.0232 0.0327 1.0000
13.250 1.3080 0.06844 0.06152 -0.0228 0.0315 1.0000
13.500 1.3058 0.07218 0.06546 -0.0226 0.0306 1.0000
13.750 1.3025 0.07623 0.06973 -0.0225 0.0302 1.0000
14.000 1.2963 0.08082 0.07458 -0.0229 0.0301 1.0000
14.250 1.2863 0.08599 0.08001 -0.0240 0.0301 1.0000
14.500 1.2728 0.09178 0.08606 -0.0258 0.0302 1.0000
14.750 1.2566 0.09820 0.09274 -0.0284 0.0304 1.0000
15.000 1.2383 0.10530 0.10008 -0.0318 0.0306 1.0000
15.250 1.2166 0.11349 0.10851 -0.0365 0.0310 1.0000
15.500 1.1930 0.12265 0.11789 -0.0421 0.0315 1.0000
15.750 1.1674 0.13295 0.12838 -0.0488 0.0321 1.0000
16.000 1.1394 0.14481 0.14038 -0.0566 0.0330 1.0000
16.250 1.1143 0.15687 0.15251 -0.0641 0.0345 1.0000
16.500 1.0977 0.16716 0.16276 -0.0699 0.0354 1.0000
16.750 1.0507 0.19479 0.19018 -0.0849 0.0434 1.0000
17.000 1.0535 0.20025 0.19563 -0.0871 0.0442 1.0000
17.250 1.0585 0.20495 0.20033 -0.0886 0.0449 1.0000
17.500 0.7739 0.18336 0.17898 -0.0582 0.0536 1.0000
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Polar data table (+)
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