RG 8 AIRFOIL (rg8-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: RG 8 AIRFOIL (rg8-il) Reynolds number: 200,000 Max Cl/Cd: 73.64 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-rg8-il-200000.txt Download as CSV file: xf-rg8-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: RG 8 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.4780 0.09569 0.09216 -0.0407 1.0000 0.0626
-9.500 -0.4951 0.08959 0.08614 -0.0459 1.0000 0.0629
-9.250 -0.5202 0.08392 0.08049 -0.0502 1.0000 0.0630
-9.000 -0.4985 0.08163 0.07826 -0.0432 1.0000 0.0648
-8.750 -0.4822 0.08172 0.07835 -0.0389 1.0000 0.0672
-8.500 -0.4928 0.07779 0.07448 -0.0398 1.0000 0.0679
-8.250 -0.5074 0.07423 0.07099 -0.0402 1.0000 0.0696
-8.000 -0.5408 0.06798 0.06479 -0.0441 1.0000 0.0685
-7.750 -0.5564 0.06368 0.06045 -0.0450 1.0000 0.0697
-7.500 -0.5688 0.05948 0.05614 -0.0454 1.0000 0.0714
-7.250 -0.6144 0.03962 0.03456 -0.0482 1.0000 0.0404
-7.000 -0.6009 0.03604 0.03081 -0.0473 1.0000 0.0386
-6.750 -0.5880 0.03176 0.02612 -0.0468 1.0000 0.0373
-6.500 -0.5702 0.02824 0.02213 -0.0462 1.0000 0.0363
-6.250 -0.5495 0.02559 0.01906 -0.0456 1.0000 0.0360
-6.000 -0.5270 0.02359 0.01672 -0.0450 1.0000 0.0363
-5.750 -0.5041 0.02213 0.01500 -0.0443 1.0000 0.0373
-5.500 -0.4814 0.02120 0.01387 -0.0435 1.0000 0.0389
-5.250 -0.4585 0.02013 0.01262 -0.0428 1.0000 0.0401
-5.000 -0.4357 0.01849 0.01094 -0.0423 1.0000 0.0419
-4.750 -0.4131 0.01765 0.01010 -0.0417 1.0000 0.0444
-4.500 -0.3815 0.01695 0.00935 -0.0428 0.9980 0.0484
-4.250 -0.3423 0.01615 0.00856 -0.0455 0.9945 0.0584
-4.000 -0.3044 0.01505 0.00766 -0.0480 0.9903 0.1010
-3.750 -0.2651 0.01443 0.00734 -0.0510 0.9860 0.1653
-3.500 -0.2268 0.01387 0.00714 -0.0539 0.9816 0.2488
-3.250 -0.1913 0.01301 0.00700 -0.0564 0.9763 0.4022
-3.000 -0.1515 0.01284 0.00724 -0.0589 0.9720 0.5331
-2.750 -0.1177 0.01281 0.00725 -0.0600 0.9646 0.5833
-2.500 -0.0772 0.01287 0.00729 -0.0623 0.9598 0.6206
-2.250 -0.0437 0.01286 0.00726 -0.0633 0.9521 0.6492
-2.000 -0.0041 0.01282 0.00723 -0.0653 0.9470 0.6724
-1.750 0.0299 0.01274 0.00713 -0.0663 0.9394 0.6918
-1.500 0.0690 0.01261 0.00699 -0.0682 0.9338 0.7098
-1.250 0.1043 0.01246 0.00685 -0.0694 0.9269 0.7259
-1.000 0.1419 0.01226 0.00666 -0.0709 0.9206 0.7414
-0.750 0.1854 0.01199 0.00640 -0.0736 0.9173 0.7562
-0.500 0.2163 0.01180 0.00622 -0.0738 0.9078 0.7701
-0.250 0.2599 0.01149 0.00593 -0.0764 0.9039 0.7843
0.000 0.2922 0.01127 0.00574 -0.0769 0.8941 0.7976
0.250 0.3334 0.01094 0.00544 -0.0790 0.8886 0.8098
0.500 0.3640 0.01072 0.00525 -0.0790 0.8768 0.8217
0.750 0.3964 0.01049 0.00506 -0.0794 0.8650 0.8335
1.000 0.4290 0.01029 0.00487 -0.0799 0.8521 0.8454
1.250 0.4600 0.01012 0.00471 -0.0801 0.8376 0.8579
1.500 0.4890 0.00999 0.00459 -0.0798 0.8214 0.8712
1.750 0.5162 0.00988 0.00448 -0.0792 0.8042 0.8856
2.000 0.5422 0.00979 0.00437 -0.0782 0.7864 0.9016
2.250 0.5654 0.00972 0.00430 -0.0767 0.7659 0.9212
2.500 0.5942 0.00967 0.00424 -0.0765 0.7451 0.9450
2.750 0.6332 0.00967 0.00421 -0.0787 0.7216 0.9715
3.000 0.6723 0.00975 0.00419 -0.0811 0.6969 1.0000
3.250 0.6984 0.00992 0.00427 -0.0811 0.6718 1.0000
3.500 0.7248 0.01012 0.00437 -0.0809 0.6463 1.0000
3.750 0.7504 0.01035 0.00449 -0.0805 0.6204 1.0000
4.000 0.7754 0.01061 0.00463 -0.0800 0.5939 1.0000
4.250 0.7996 0.01089 0.00483 -0.0792 0.5664 1.0000
4.500 0.8233 0.01118 0.00503 -0.0784 0.5382 1.0000
4.750 0.8465 0.01150 0.00525 -0.0775 0.5094 1.0000
5.000 0.8694 0.01185 0.00552 -0.0765 0.4803 1.0000
5.250 0.8918 0.01222 0.00580 -0.0755 0.4509 1.0000
5.500 0.9139 0.01261 0.00610 -0.0744 0.4211 1.0000
5.750 0.9356 0.01304 0.00643 -0.0733 0.3908 1.0000
6.000 0.9567 0.01350 0.00681 -0.0721 0.3599 1.0000
6.250 0.9775 0.01400 0.00721 -0.0709 0.3289 1.0000
6.500 0.9982 0.01452 0.00764 -0.0698 0.2977 1.0000
6.750 1.0185 0.01508 0.00812 -0.0685 0.2664 1.0000
7.000 1.0382 0.01570 0.00864 -0.0673 0.2355 1.0000
7.250 1.0572 0.01638 0.00923 -0.0659 0.2046 1.0000
7.500 1.0752 0.01716 0.00987 -0.0644 0.1731 1.0000
7.750 1.0926 0.01800 0.01055 -0.0630 0.1413 1.0000
8.000 1.1097 0.01888 0.01129 -0.0615 0.1131 1.0000
8.250 1.1258 0.01984 0.01214 -0.0598 0.0910 1.0000
8.500 1.1415 0.02084 0.01312 -0.0581 0.0716 1.0000
8.750 1.1525 0.02220 0.01437 -0.0556 0.0543 1.0000
9.000 1.1593 0.02378 0.01592 -0.0524 0.0413 1.0000
9.250 1.1685 0.02506 0.01723 -0.0497 0.0342 1.0000
9.500 1.1760 0.02657 0.01882 -0.0467 0.0304 1.0000
9.750 1.1857 0.02792 0.02026 -0.0442 0.0279 1.0000
10.000 1.1930 0.02956 0.02193 -0.0417 0.0261 1.0000
10.250 1.2010 0.03201 0.02444 -0.0394 0.0247 1.0000
10.500 1.2144 0.03368 0.02628 -0.0376 0.0238 1.0000
10.750 1.2277 0.03561 0.02841 -0.0359 0.0230 1.0000
11.000 1.2395 0.03760 0.03058 -0.0343 0.0222 1.0000
11.250 1.2479 0.03935 0.03249 -0.0324 0.0212 1.0000
11.500 1.2550 0.04126 0.03452 -0.0306 0.0204 1.0000
11.750 1.2608 0.04336 0.03672 -0.0289 0.0197 1.0000
12.000 1.2660 0.04625 0.03978 -0.0275 0.0192 1.0000
12.250 1.2661 0.05000 0.04378 -0.0258 0.0189 1.0000
12.500 1.2613 0.05361 0.04766 -0.0241 0.0188 1.0000
12.750 1.2520 0.05752 0.05185 -0.0227 0.0188 1.0000
13.000 1.2418 0.06126 0.05585 -0.0217 0.0188 1.0000
13.250 1.2284 0.06551 0.06035 -0.0213 0.0188 1.0000
13.500 1.2146 0.06989 0.06496 -0.0217 0.0188 1.0000
13.750 1.1991 0.07474 0.07004 -0.0228 0.0189 1.0000
14.000 1.1836 0.07987 0.07539 -0.0246 0.0189 1.0000
14.250 1.1661 0.08571 0.08145 -0.0274 0.0191 1.0000
14.500 1.1458 0.09254 0.08851 -0.0313 0.0192 1.0000
14.750 1.1199 0.10126 0.09751 -0.0371 0.0195 1.0000
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Polar data table (+)
Polar graphs
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