S2050 8.93% (s2050-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: S2050 8.93% (s2050-il) Reynolds number: 500,000 Max Cl/Cd: 80.88 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s2050-il-500000.txt Download as CSV file: xf-s2050-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: S2050 8.93%
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.5540 0.08338 0.08111 -0.0251 1.0000 0.0241
-9.250 -0.5561 0.07934 0.07710 -0.0271 1.0000 0.0246
-9.000 -0.7402 0.03712 0.03375 -0.0465 1.0000 0.0123
-8.750 -0.7393 0.03347 0.02977 -0.0452 1.0000 0.0123
-8.500 -0.7303 0.03071 0.02667 -0.0439 1.0000 0.0122
-8.250 -0.7201 0.02769 0.02330 -0.0427 1.0000 0.0122
-8.000 -0.7041 0.02566 0.02100 -0.0416 1.0000 0.0121
-7.750 -0.6860 0.02393 0.01903 -0.0405 1.0000 0.0120
-7.500 -0.6678 0.02187 0.01671 -0.0395 1.0000 0.0119
-7.250 -0.6485 0.01979 0.01436 -0.0385 1.0000 0.0119
-7.000 -0.6291 0.01746 0.01176 -0.0375 1.0000 0.0121
-6.750 -0.6082 0.01570 0.00982 -0.0367 1.0000 0.0125
-6.500 -0.5857 0.01463 0.00868 -0.0360 1.0000 0.0132
-6.250 -0.5623 0.01389 0.00788 -0.0354 1.0000 0.0139
-6.000 -0.5384 0.01323 0.00715 -0.0348 1.0000 0.0149
-5.750 -0.5142 0.01264 0.00647 -0.0342 1.0000 0.0159
-5.500 -0.4898 0.01185 0.00560 -0.0338 1.0000 0.0175
-5.250 -0.4651 0.01140 0.00515 -0.0333 1.0000 0.0206
-5.000 -0.4398 0.01080 0.00454 -0.0330 1.0000 0.0288
-4.750 -0.4146 0.01029 0.00412 -0.0327 1.0000 0.0468
-4.500 -0.3896 0.01004 0.00389 -0.0323 1.0000 0.0589
-4.250 -0.3634 0.00982 0.00371 -0.0322 0.9997 0.0719
-4.000 -0.3250 0.00961 0.00354 -0.0346 0.9969 0.0897
-3.750 -0.2861 0.00935 0.00338 -0.0372 0.9943 0.1145
-3.500 -0.2491 0.00903 0.00317 -0.0393 0.9906 0.1428
-3.250 -0.2108 0.00869 0.00298 -0.0418 0.9870 0.1818
-3.000 -0.1712 0.00830 0.00282 -0.0446 0.9843 0.2406
-2.750 -0.1363 0.00782 0.00262 -0.0463 0.9795 0.3177
-2.500 -0.0996 0.00722 0.00244 -0.0486 0.9751 0.4333
-2.250 -0.0611 0.00664 0.00236 -0.0511 0.9718 0.5680
-2.000 -0.0279 0.00641 0.00230 -0.0521 0.9645 0.6367
-1.750 0.0105 0.00627 0.00222 -0.0541 0.9594 0.6717
-1.500 0.0444 0.00614 0.00213 -0.0551 0.9510 0.6936
-1.250 0.0818 0.00602 0.00201 -0.0568 0.9440 0.7131
-1.000 0.1155 0.00592 0.00192 -0.0578 0.9318 0.7282
-0.750 0.1511 0.00582 0.00184 -0.0591 0.9180 0.7433
-0.500 0.1861 0.00577 0.00175 -0.0603 0.8997 0.7564
-0.250 0.2175 0.00575 0.00170 -0.0606 0.8752 0.7673
0.000 0.2461 0.00580 0.00167 -0.0604 0.8477 0.7771
0.250 0.2733 0.00589 0.00167 -0.0600 0.8197 0.7875
0.500 0.2994 0.00600 0.00169 -0.0593 0.7923 0.7986
0.750 0.3251 0.00610 0.00173 -0.0585 0.7661 0.8089
1.000 0.3509 0.00622 0.00177 -0.0578 0.7405 0.8186
1.250 0.3769 0.00634 0.00181 -0.0572 0.7146 0.8289
1.500 0.4023 0.00643 0.00186 -0.0565 0.6885 0.8380
1.750 0.4280 0.00655 0.00191 -0.0558 0.6612 0.8470
2.000 0.4535 0.00668 0.00198 -0.0552 0.6318 0.8560
2.250 0.4785 0.00681 0.00204 -0.0544 0.6009 0.8646
2.500 0.5036 0.00697 0.00211 -0.0538 0.5689 0.8746
3.000 0.5520 0.00730 0.00231 -0.0520 0.5048 0.8962
3.250 0.5756 0.00748 0.00241 -0.0510 0.4710 0.9087
3.500 0.5978 0.00768 0.00252 -0.0497 0.4340 0.9237
3.750 0.6194 0.00787 0.00262 -0.0483 0.3968 0.9443
4.000 0.6471 0.00808 0.00274 -0.0483 0.3620 0.9734
4.250 0.6786 0.00839 0.00292 -0.0493 0.3249 1.0000
4.500 0.7055 0.00879 0.00314 -0.0494 0.2828 1.0000
4.750 0.7317 0.00924 0.00340 -0.0494 0.2390 1.0000
5.000 0.7573 0.00973 0.00368 -0.0493 0.1955 1.0000
5.250 0.7830 0.01020 0.00399 -0.0491 0.1613 1.0000
5.500 0.8086 0.01066 0.00432 -0.0489 0.1315 1.0000
5.750 0.8339 0.01114 0.00469 -0.0486 0.1043 1.0000
6.000 0.8588 0.01167 0.00510 -0.0482 0.0790 1.0000
6.250 0.8831 0.01228 0.00557 -0.0478 0.0541 1.0000
6.500 0.9062 0.01310 0.00626 -0.0471 0.0333 1.0000
6.750 0.9291 0.01395 0.00711 -0.0463 0.0259 1.0000
7.000 0.9538 0.01447 0.00772 -0.0457 0.0239 1.0000
7.250 0.9777 0.01509 0.00840 -0.0451 0.0222 1.0000
7.500 1.0002 0.01587 0.00922 -0.0443 0.0205 1.0000
7.750 1.0187 0.01723 0.01069 -0.0429 0.0190 1.0000
8.000 1.0418 0.01792 0.01146 -0.0421 0.0184 1.0000
8.250 1.0634 0.01881 0.01247 -0.0412 0.0177 1.0000
8.500 1.0844 0.01980 0.01356 -0.0402 0.0171 1.0000
8.750 1.1050 0.02086 0.01472 -0.0392 0.0165 1.0000
9.000 1.1250 0.02200 0.01596 -0.0381 0.0160 1.0000
9.250 1.1449 0.02309 0.01713 -0.0371 0.0154 1.0000
9.500 1.1632 0.02441 0.01852 -0.0360 0.0147 1.0000
9.750 1.1752 0.02741 0.02175 -0.0343 0.0140 1.0000
10.000 1.1891 0.02976 0.02435 -0.0327 0.0137 1.0000
10.250 1.2043 0.03132 0.02612 -0.0312 0.0135 1.0000
10.500 1.2170 0.03311 0.02815 -0.0296 0.0132 1.0000
10.750 1.2255 0.03539 0.03068 -0.0276 0.0130 1.0000
11.000 1.2298 0.03787 0.03343 -0.0253 0.0128 1.0000
11.250 1.2285 0.04035 0.03617 -0.0224 0.0126 1.0000
11.500 1.2204 0.04288 0.03893 -0.0190 0.0125 1.0000
11.750 1.2100 0.04557 0.04184 -0.0161 0.0123 1.0000
12.000 1.1975 0.04867 0.04515 -0.0143 0.0122 1.0000
12.250 1.1824 0.05243 0.04912 -0.0137 0.0121 1.0000
12.500 1.1673 0.05672 0.05359 -0.0144 0.0120 1.0000
12.750 1.1482 0.06225 0.05932 -0.0167 0.0120 1.0000
13.000 1.1238 0.06957 0.06686 -0.0209 0.0121 1.0000
13.250 1.0958 0.07875 0.07624 -0.0271 0.0124 1.0000
13.500 1.0645 0.08993 0.08760 -0.0351 0.0128 1.0000
13.750 1.0350 0.10203 0.09985 -0.0437 0.0130 1.0000
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Polar data table (+)
Polar graphs
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