S5010 (s5010-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: S5010 (s5010-il) Reynolds number: 200,000 Max Cl/Cd: 63.22 at α=6.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s5010-il-200000.txt Download as CSV file: xf-s5010-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: S5010
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
------ -------- --------- --------- -------- -------- --------
-8.250 -0.5315 0.08931 0.08638 0.0094 1.0000 0.0444
-8.000 -0.5378 0.08423 0.08138 0.0031 1.0000 0.0456
-7.750 -0.5449 0.07824 0.07537 -0.0055 1.0000 0.0462
-7.500 -0.5482 0.07299 0.06991 -0.0117 1.0000 0.0468
-7.250 -0.5511 0.06569 0.06247 -0.0151 1.0000 0.0475
-7.000 -0.5342 0.06182 0.05882 -0.0148 1.0000 0.0490
-6.750 -0.5177 0.05922 0.05626 -0.0156 1.0000 0.0513
-6.500 -0.5012 0.05512 0.05201 -0.0189 1.0000 0.0562
-6.250 -0.4843 0.04871 0.04508 -0.0237 0.9366 0.0615
-6.000 -0.4691 0.04662 0.04298 -0.0226 0.9118 0.0640
-5.750 -0.4559 0.04415 0.04026 -0.0215 0.8922 0.0684
-5.500 -0.4450 0.04054 0.03614 -0.0206 0.8764 0.0753
-5.250 -0.4189 0.02445 0.02036 -0.0169 0.8381 0.0780
-5.000 -0.4035 0.02120 0.01659 -0.0160 0.8278 0.0885
-4.750 -0.3850 0.02701 0.02085 -0.0150 0.8420 0.0436
-4.500 -0.3616 0.02416 0.01754 -0.0137 0.8308 0.0419
-4.250 -0.3369 0.02218 0.01516 -0.0125 0.8202 0.0423
-4.000 -0.3116 0.02020 0.01280 -0.0112 0.8109 0.0415
-3.750 -0.2853 0.01875 0.01109 -0.0102 0.8007 0.0421
-3.500 -0.2588 0.01783 0.00999 -0.0095 0.7907 0.0446
-3.250 -0.2326 0.01710 0.00908 -0.0086 0.7817 0.0466
-3.000 -0.2074 0.01573 0.00767 -0.0077 0.7720 0.0485
-2.750 -0.1823 0.01488 0.00682 -0.0070 0.7626 0.0521
-2.500 -0.1569 0.01442 0.00626 -0.0061 0.7543 0.0581
-2.250 -0.1313 0.01370 0.00554 -0.0055 0.7443 0.0664
-2.000 -0.1072 0.01266 0.00482 -0.0046 0.7356 0.1370
-1.750 -0.0935 0.01063 0.00454 -0.0025 0.7273 0.5545
-1.500 -0.0754 0.00977 0.00454 0.0005 0.7183 0.7791
-1.250 0.0009 0.00975 0.00463 -0.0072 0.7093 0.9643
-1.000 0.0752 0.00977 0.00438 -0.0163 0.6984 1.0000
-0.750 0.0990 0.00976 0.00422 -0.0156 0.6885 1.0000
-0.500 0.1227 0.00976 0.00406 -0.0148 0.6799 1.0000
-0.250 0.1473 0.00977 0.00394 -0.0141 0.6699 1.0000
0.000 0.1721 0.00980 0.00385 -0.0135 0.6602 1.0000
0.250 0.1965 0.00984 0.00373 -0.0127 0.6517 1.0000
0.500 0.2219 0.00987 0.00368 -0.0122 0.6411 1.0000
0.750 0.2472 0.00992 0.00364 -0.0116 0.6314 1.0000
1.000 0.2722 0.00999 0.00357 -0.0109 0.6227 1.0000
1.250 0.2980 0.01004 0.00357 -0.0104 0.6118 1.0000
1.500 0.3237 0.01011 0.00357 -0.0099 0.6016 1.0000
1.750 0.3492 0.01019 0.00354 -0.0093 0.5922 1.0000
2.000 0.3751 0.01026 0.00356 -0.0088 0.5813 1.0000
2.250 0.4011 0.01034 0.00361 -0.0083 0.5703 1.0000
2.500 0.4270 0.01043 0.00364 -0.0078 0.5597 1.0000
2.750 0.4528 0.01053 0.00364 -0.0073 0.5495 1.0000
3.000 0.4789 0.01062 0.00372 -0.0069 0.5374 1.0000
3.250 0.5051 0.01073 0.00381 -0.0064 0.5254 1.0000
3.500 0.5311 0.01085 0.00390 -0.0060 0.5133 1.0000
3.750 0.5571 0.01097 0.00398 -0.0056 0.5010 1.0000
4.000 0.5831 0.01111 0.00410 -0.0051 0.4884 1.0000
4.250 0.6091 0.01125 0.00420 -0.0047 0.4750 1.0000
4.500 0.6351 0.01141 0.00433 -0.0043 0.4612 1.0000
4.750 0.6610 0.01157 0.00447 -0.0039 0.4466 1.0000
5.000 0.6870 0.01175 0.00466 -0.0035 0.4315 1.0000
5.250 0.7129 0.01195 0.00486 -0.0032 0.4157 1.0000
5.500 0.7387 0.01217 0.00507 -0.0029 0.3994 1.0000
5.750 0.7644 0.01241 0.00531 -0.0025 0.3826 1.0000
6.000 0.7899 0.01269 0.00558 -0.0022 0.3655 1.0000
6.250 0.8152 0.01300 0.00585 -0.0018 0.3484 1.0000
6.500 0.8404 0.01333 0.00618 -0.0015 0.3304 1.0000
6.750 0.8655 0.01369 0.00656 -0.0012 0.3118 1.0000
7.000 0.8901 0.01410 0.00695 -0.0009 0.2937 1.0000
7.250 0.9143 0.01457 0.00737 -0.0005 0.2761 1.0000
7.500 0.9386 0.01503 0.00786 -0.0002 0.2578 1.0000
7.750 0.9624 0.01553 0.00839 0.0001 0.2400 1.0000
8.000 0.9856 0.01610 0.00895 0.0005 0.2230 1.0000
8.250 1.0083 0.01673 0.00954 0.0009 0.2066 1.0000
8.500 1.0303 0.01742 0.01020 0.0013 0.1909 1.0000
8.750 1.0523 0.01809 0.01091 0.0018 0.1755 1.0000
9.000 1.0735 0.01882 0.01169 0.0023 0.1607 1.0000
9.250 1.0938 0.01963 0.01251 0.0029 0.1470 1.0000
9.500 1.1131 0.02049 0.01339 0.0035 0.1341 1.0000
9.750 1.1311 0.02146 0.01435 0.0042 0.1221 1.0000
10.000 1.1486 0.02240 0.01534 0.0050 0.1109 1.0000
10.250 1.1654 0.02336 0.01642 0.0058 0.1006 1.0000
10.500 1.1796 0.02452 0.01764 0.0068 0.0916 1.0000
10.750 1.1906 0.02585 0.01893 0.0080 0.0833 1.0000
11.000 1.2029 0.02683 0.02006 0.0090 0.0752 1.0000
11.250 1.2082 0.02820 0.02149 0.0105 0.0685 1.0000
11.500 1.2115 0.02963 0.02297 0.0118 0.0623 1.0000
11.750 1.2145 0.03142 0.02485 0.0127 0.0567 1.0000
12.000 1.2168 0.03338 0.02688 0.0131 0.0514 1.0000
12.250 1.2168 0.03575 0.02933 0.0134 0.0467 1.0000
12.500 1.2179 0.03812 0.03181 0.0134 0.0421 1.0000
12.750 1.2113 0.04138 0.03507 0.0135 0.0386 1.0000
13.000 1.2103 0.04429 0.03818 0.0129 0.0341 1.0000
13.250 1.2061 0.04758 0.04152 0.0122 0.0318 1.0000
13.500 1.1979 0.05143 0.04544 0.0118 0.0291 1.0000
13.750 1.1948 0.05490 0.04908 0.0107 0.0268 1.0000
14.000 1.1900 0.05861 0.05288 0.0096 0.0252 1.0000
14.250 1.1853 0.06234 0.05667 0.0084 0.0241 1.0000
14.500 1.1751 0.06682 0.06121 0.0072 0.0223 1.0000
14.750 1.1707 0.07091 0.06547 0.0059 0.0216 1.0000
15.000 1.1648 0.07536 0.07010 0.0041 0.0209 1.0000
15.250 1.1582 0.08008 0.07498 0.0021 0.0202 1.0000
15.500 1.1510 0.08502 0.08007 0.0000 0.0198 1.0000
15.750 1.1424 0.09036 0.08553 -0.0027 0.0190 1.0000
16.000 1.1343 0.09578 0.09110 -0.0052 0.0188 1.0000
16.250 1.1248 0.10158 0.09703 -0.0082 0.0184 1.0000
16.500 1.1131 0.10806 0.10368 -0.0116 0.0184 1.0000
16.750 1.1000 0.11508 0.11087 -0.0154 0.0183 1.0000
17.000 1.0839 0.12303 0.11900 -0.0200 0.0183 1.0000
17.250 1.0604 0.13320 0.12938 -0.0261 0.0186 1.0000
17.500 1.0233 0.14768 0.14412 -0.0349 0.0196 1.0000
17.750 0.9340 0.18112 0.17768 -0.0533 0.0235 1.0000
18.000 0.8949 0.20541 0.20177 -0.0635 0.0285 1.0000
18.250 0.8963 0.21180 0.20814 -0.0666 0.0283 1.0000
18.500 0.9018 0.21634 0.21267 -0.0686 0.0291 1.0000
18.750 0.7062 0.20785 0.20476 -0.0586 0.0488 1.0000
19.000 0.6951 0.21181 0.20870 -0.0632 0.0476 1.0000
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Polar data table (+)
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