S2048 (s2048-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: S2048 (s2048-il) Reynolds number: 200,000 Max Cl/Cd: 67.53 at α=3.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s2048-il-200000-n5.txt Download as CSV file: xf-s2048-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: S2048
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.4690 0.08813 0.08455 -0.0325 1.0000 0.0141
-9.000 -0.4744 0.08359 0.08006 -0.0342 1.0000 0.0139
-8.750 -0.4835 0.07848 0.07502 -0.0363 1.0000 0.0134
-8.500 -0.4957 0.07356 0.07018 -0.0383 1.0000 0.0134
-8.250 -0.5286 0.06425 0.06095 -0.0444 1.0000 0.0125
-8.000 -0.5455 0.05771 0.05432 -0.0463 1.0000 0.0123
-7.750 -0.5569 0.05187 0.04831 -0.0464 1.0000 0.0121
-7.500 -0.5650 0.04698 0.04324 -0.0457 1.0000 0.0122
-7.250 -0.5679 0.04241 0.03836 -0.0447 1.0000 0.0123
-7.000 -0.5635 0.03847 0.03411 -0.0440 0.9997 0.0126
-6.750 -0.5378 0.03520 0.03051 -0.0467 0.9962 0.0133
-6.500 -0.5100 0.03290 0.02792 -0.0489 0.9931 0.0148
-6.250 -0.4837 0.02907 0.02353 -0.0504 0.9892 0.0162
-6.000 -0.4552 0.02545 0.01930 -0.0516 0.9859 0.0169
-5.750 -0.4241 0.02298 0.01632 -0.0529 0.9835 0.0176
-5.500 -0.3942 0.02161 0.01459 -0.0535 0.9802 0.0184
-5.250 -0.3668 0.01949 0.01226 -0.0542 0.9765 0.0206
-5.000 -0.3358 0.01826 0.01082 -0.0551 0.9735 0.0215
-4.750 -0.3035 0.01713 0.00955 -0.0562 0.9711 0.0226
-4.500 -0.2724 0.01619 0.00850 -0.0571 0.9680 0.0238
-4.250 -0.2444 0.01543 0.00763 -0.0573 0.9632 0.0250
-4.000 -0.2123 0.01487 0.00698 -0.0583 0.9598 0.0269
-3.750 -0.1791 0.01412 0.00615 -0.0597 0.9572 0.0296
-3.500 -0.1491 0.01363 0.00559 -0.0603 0.9528 0.0318
-3.250 -0.1189 0.01322 0.00510 -0.0608 0.9481 0.0359
-3.000 -0.0853 0.01277 0.00466 -0.0621 0.9449 0.0508
-2.750 -0.0508 0.01226 0.00431 -0.0638 0.9426 0.0957
-2.500 -0.0247 0.01178 0.00405 -0.0638 0.9359 0.1592
-2.250 0.0045 0.01080 0.00381 -0.0649 0.9318 0.3479
-2.000 0.0337 0.00998 0.00384 -0.0654 0.9287 0.5681
-1.750 0.0582 0.00981 0.00384 -0.0645 0.9212 0.6360
-1.500 0.0892 0.00967 0.00375 -0.0649 0.9169 0.6782
-1.250 0.1162 0.00954 0.00373 -0.0644 0.9107 0.7212
-1.000 0.1441 0.00941 0.00368 -0.0640 0.9045 0.7605
-0.750 0.1722 0.00928 0.00361 -0.0637 0.8976 0.7873
-0.500 0.2018 0.00914 0.00347 -0.0636 0.8896 0.8056
-0.250 0.2298 0.00901 0.00334 -0.0633 0.8791 0.8219
0.000 0.2589 0.00886 0.00318 -0.0631 0.8671 0.8384
0.250 0.2878 0.00872 0.00304 -0.0628 0.8536 0.8559
0.500 0.3165 0.00861 0.00292 -0.0625 0.8399 0.8748
0.750 0.3453 0.00853 0.00283 -0.0622 0.8264 0.8962
1.000 0.3762 0.00847 0.00277 -0.0625 0.8128 0.9200
1.250 0.4111 0.00843 0.00273 -0.0638 0.7987 0.9462
1.500 0.4490 0.00841 0.00268 -0.0658 0.7834 0.9763
1.750 0.4817 0.00844 0.00266 -0.0668 0.7663 1.0000
2.000 0.5079 0.00852 0.00270 -0.0664 0.7477 1.0000
2.250 0.5338 0.00862 0.00274 -0.0659 0.7262 1.0000
2.500 0.5595 0.00874 0.00279 -0.0654 0.7017 1.0000
2.750 0.5848 0.00889 0.00286 -0.0647 0.6721 1.0000
3.000 0.6094 0.00909 0.00296 -0.0639 0.6351 1.0000
3.250 0.6328 0.00937 0.00306 -0.0629 0.5879 1.0000
3.500 0.6548 0.00976 0.00321 -0.0617 0.5311 1.0000
3.750 0.6751 0.01030 0.00343 -0.0603 0.4650 1.0000
4.000 0.6951 0.01092 0.00372 -0.0589 0.3997 1.0000
4.250 0.7163 0.01150 0.00408 -0.0578 0.3465 1.0000
4.500 0.7385 0.01202 0.00442 -0.0570 0.3052 1.0000
4.750 0.7617 0.01248 0.00477 -0.0563 0.2722 1.0000
5.000 0.7849 0.01294 0.00513 -0.0556 0.2425 1.0000
5.250 0.8082 0.01341 0.00551 -0.0550 0.2137 1.0000
5.500 0.8313 0.01390 0.00592 -0.0543 0.1848 1.0000
5.750 0.8540 0.01445 0.00640 -0.0536 0.1518 1.0000
6.000 0.8762 0.01508 0.00689 -0.0529 0.1170 1.0000
6.250 0.8974 0.01583 0.00749 -0.0520 0.0872 1.0000
6.500 0.9192 0.01655 0.00815 -0.0512 0.0682 1.0000
6.750 0.9411 0.01724 0.00887 -0.0503 0.0571 1.0000
7.000 0.9623 0.01801 0.00965 -0.0493 0.0486 1.0000
7.250 0.9836 0.01875 0.01046 -0.0484 0.0402 1.0000
7.500 1.0057 0.01936 0.01114 -0.0477 0.0322 1.0000
7.750 1.0261 0.02016 0.01197 -0.0467 0.0260 1.0000
8.000 1.0465 0.02096 0.01287 -0.0456 0.0212 1.0000
8.250 1.0639 0.02215 0.01416 -0.0441 0.0173 1.0000
8.500 1.0824 0.02315 0.01528 -0.0428 0.0145 1.0000
8.750 1.0982 0.02444 0.01663 -0.0413 0.0124 1.0000
9.000 1.1160 0.02547 0.01783 -0.0400 0.0107 1.0000
9.250 1.1314 0.02675 0.01931 -0.0383 0.0098 1.0000
9.500 1.1458 0.02807 0.02077 -0.0367 0.0091 1.0000
9.750 1.1576 0.02963 0.02248 -0.0347 0.0086 1.0000
10.000 1.1647 0.03173 0.02476 -0.0323 0.0082 1.0000
10.250 1.1721 0.03366 0.02691 -0.0298 0.0079 1.0000
10.500 1.1780 0.03569 0.02920 -0.0273 0.0077 1.0000
10.750 1.1811 0.03797 0.03174 -0.0246 0.0076 1.0000
11.000 1.1813 0.04040 0.03445 -0.0220 0.0075 1.0000
11.250 1.1780 0.04315 0.03749 -0.0194 0.0073 1.0000
11.500 1.1714 0.04620 0.04083 -0.0172 0.0073 1.0000
11.750 1.1623 0.04953 0.04444 -0.0154 0.0072 1.0000
12.000 1.1499 0.05340 0.04859 -0.0144 0.0072 1.0000
12.250 1.1343 0.05796 0.05341 -0.0144 0.0071 1.0000
12.500 1.1182 0.06299 0.05868 -0.0154 0.0071 1.0000
12.750 1.1007 0.06883 0.06475 -0.0178 0.0072 1.0000
13.000 1.0825 0.07558 0.07170 -0.0216 0.0072 1.0000
13.250 1.0614 0.08398 0.08031 -0.0271 0.0072 1.0000
13.500 1.0407 0.09345 0.08995 -0.0337 0.0073 1.0000
13.750 1.0208 0.10358 0.10022 -0.0404 0.0074 1.0000
14.000 0.9972 0.11527 0.11201 -0.0477 0.0076 1.0000
14.250 0.9708 0.12833 0.12514 -0.0553 0.0078 1.0000
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Polar data table (+)
Polar graphs
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