S1091 (s1091-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: S1091 (s1091-il) Reynolds number: 200,000 Max Cl/Cd: 96.18 at α=4° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s1091-il-200000.txt Download as CSV file: xf-s1091-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: S1091
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
------ -------- --------- --------- -------- -------- --------
-7.000 -0.2922 0.09946 0.09613 -0.0164 1.0000 0.0187
-6.750 -0.2997 0.09878 0.09552 -0.0146 1.0000 0.0190
-6.500 -0.3023 0.09782 0.09464 -0.0148 1.0000 0.0192
-6.250 -0.3020 0.09639 0.09327 -0.0153 1.0000 0.0193
-6.000 -0.2991 0.09552 0.09245 -0.0181 1.0000 0.0195
-5.750 -0.3007 0.09181 0.08883 -0.0166 1.0000 0.0198
-5.500 -0.3027 0.08860 0.08566 -0.0128 1.0000 0.0202
-5.250 -0.2979 0.08585 0.08293 -0.0119 0.9991 0.0209
-5.000 -0.2656 0.08171 0.07877 -0.0185 0.9948 0.0226
-4.750 -0.2302 0.07758 0.07463 -0.0263 0.9889 0.0239
-4.500 -0.1855 0.07334 0.07034 -0.0365 0.9845 0.0258
-4.250 -0.1178 0.06995 0.06683 -0.0537 0.9766 0.0273
-4.000 -0.0697 0.06468 0.06150 -0.0640 0.9729 0.0278
-3.750 -0.0581 0.06026 0.05711 -0.0631 0.9660 0.0289
-3.500 -0.0233 0.05667 0.05350 -0.0680 0.9614 0.0308
-3.250 0.0198 0.05305 0.04982 -0.0751 0.9561 0.0334
-3.000 0.0999 0.04960 0.04612 -0.0908 0.9506 0.0380
-2.750 0.1354 0.04415 0.04066 -0.0961 0.9472 0.0396
-2.500 0.1642 0.04149 0.03798 -0.0981 0.9395 0.0427
-2.250 0.2446 0.03830 0.03432 -0.1108 0.9360 0.0507
-2.000 0.2727 0.03385 0.03003 -0.1136 0.9330 0.0545
-1.750 0.3260 0.03040 0.02619 -0.1200 0.9252 0.0653
-1.500 0.3638 0.02804 0.02387 -0.1229 0.9212 0.0743
-0.750 0.5122 0.01632 0.01036 -0.1341 0.9071 0.0419
-0.500 0.5508 0.01505 0.00863 -0.1350 0.8982 0.0382
-0.250 0.5926 0.01319 0.00655 -0.1374 0.8920 0.0428
0.000 0.6281 0.01224 0.00550 -0.1382 0.8806 0.0463
0.250 0.6638 0.01147 0.00469 -0.1392 0.8688 0.0557
0.500 0.6981 0.01064 0.00420 -0.1400 0.8561 0.1747
0.750 0.7294 0.01027 0.00419 -0.1406 0.8421 0.3368
1.000 0.7631 0.00906 0.00405 -0.1414 0.8283 1.0000
1.250 0.7920 0.00916 0.00392 -0.1412 0.8130 1.0000
1.500 0.8197 0.00929 0.00386 -0.1407 0.7973 1.0000
1.750 0.8466 0.00944 0.00383 -0.1400 0.7812 1.0000
2.000 0.8729 0.00960 0.00384 -0.1393 0.7648 1.0000
2.250 0.8989 0.00977 0.00386 -0.1385 0.7481 1.0000
2.500 0.9236 0.00993 0.00392 -0.1375 0.7297 1.0000
2.750 0.9482 0.01010 0.00401 -0.1364 0.7106 1.0000
3.000 0.9728 0.01029 0.00407 -0.1353 0.6914 1.0000
3.250 0.9967 0.01047 0.00416 -0.1342 0.6701 1.0000
3.500 1.0204 0.01067 0.00425 -0.1330 0.6478 1.0000
3.750 1.0436 0.01086 0.00437 -0.1317 0.6234 1.0000
4.000 1.0666 0.01109 0.00453 -0.1304 0.5971 1.0000
4.250 1.0889 0.01133 0.00466 -0.1290 0.5667 1.0000
4.500 1.1103 0.01163 0.00481 -0.1275 0.5304 1.0000
4.750 1.1311 0.01200 0.00500 -0.1259 0.4894 1.0000
5.000 1.1513 0.01248 0.00527 -0.1242 0.4483 1.0000
5.250 1.1715 0.01301 0.00566 -0.1227 0.4105 1.0000
5.500 1.1914 0.01360 0.00605 -0.1212 0.3735 1.0000
5.750 1.2113 0.01419 0.00648 -0.1197 0.3356 1.0000
6.000 1.2306 0.01485 0.00696 -0.1182 0.2968 1.0000
6.250 1.2494 0.01559 0.00752 -0.1166 0.2565 1.0000
6.500 1.2676 0.01640 0.00812 -0.1150 0.2168 1.0000
6.750 1.2853 0.01730 0.00883 -0.1134 0.1829 1.0000
7.000 1.3023 0.01829 0.00964 -0.1116 0.1580 1.0000
7.250 1.3203 0.01921 0.01049 -0.1100 0.1402 1.0000
7.500 1.3378 0.02018 0.01143 -0.1082 0.1280 1.0000
7.750 1.3543 0.02128 0.01243 -0.1064 0.1186 1.0000
8.000 1.3741 0.02199 0.01326 -0.1051 0.1112 1.0000
8.250 1.3906 0.02324 0.01441 -0.1034 0.1053 1.0000
8.500 1.4106 0.02404 0.01537 -0.1020 0.1010 1.0000
8.750 1.4297 0.02498 0.01640 -0.1006 0.0970 1.0000
9.000 1.4489 0.02632 0.01770 -0.0994 0.0935 1.0000
9.250 1.4701 0.02766 0.01915 -0.0985 0.0909 1.0000
9.500 1.4906 0.02873 0.02041 -0.0973 0.0885 1.0000
9.750 1.5102 0.02980 0.02165 -0.0961 0.0855 1.0000
10.000 1.5299 0.03095 0.02287 -0.0951 0.0828 1.0000
10.250 1.5540 0.03313 0.02510 -0.0950 0.0801 1.0000
10.500 1.5729 0.03471 0.02695 -0.0937 0.0783 1.0000
10.750 1.5885 0.03588 0.02839 -0.0920 0.0760 1.0000
11.000 1.6033 0.03709 0.02982 -0.0902 0.0733 1.0000
11.250 1.6178 0.03824 0.03111 -0.0885 0.0705 1.0000
11.500 1.6341 0.04087 0.03382 -0.0878 0.0669 1.0000
11.750 1.6360 0.04111 0.03438 -0.0841 0.0642 1.0000
12.000 1.6349 0.04126 0.03466 -0.0800 0.0607 1.0000
12.250 1.6343 0.04137 0.03466 -0.0766 0.0568 1.0000
12.500 1.6309 0.04260 0.03610 -0.0732 0.0537 1.0000
12.750 1.6268 0.04336 0.03709 -0.0699 0.0505 1.0000
13.000 1.6267 0.04433 0.03817 -0.0677 0.0476 1.0000
13.250 1.6258 0.04630 0.04013 -0.0659 0.0444 1.0000
13.500 1.6247 0.04773 0.04195 -0.0644 0.0412 1.0000
13.750 1.6240 0.04914 0.04342 -0.0639 0.0347 1.0000
14.000 1.6225 0.05203 0.04629 -0.0638 0.0166 1.0000
14.250 1.6071 0.05689 0.05124 -0.0636 0.0141 1.0000
14.500 1.5931 0.06190 0.05645 -0.0639 0.0129 1.0000
14.750 1.5801 0.06707 0.06187 -0.0647 0.0118 1.0000
15.000 1.5653 0.07279 0.06780 -0.0662 0.0111 1.0000
15.250 1.5484 0.07926 0.07445 -0.0685 0.0106 1.0000
15.500 1.5309 0.08622 0.08162 -0.0714 0.0105 1.0000
15.750 1.5123 0.09386 0.08946 -0.0750 0.0103 1.0000
16.000 1.4935 0.10199 0.09779 -0.0791 0.0102 1.0000
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Polar data table (+)
Polar graphs
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