NREL's S810 Airfoil (s810-nr) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: NREL's S810 Airfoil (s810-nr) Reynolds number: 1,000,000 Max Cl/Cd: 105.36 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s810-nr-1000000.txt Download as CSV file: xf-s810-nr-1000000.csv |
XFOIL Version 6.96
Calculated polar for: NREL's S810 Airfoil
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.750 -0.4875 0.07625 0.07319 -0.0796 0.7331 0.0074
-11.500 -0.5027 0.07258 0.06943 -0.0796 0.7319 0.0074
-11.000 -0.5312 0.06621 0.06287 -0.0781 0.7295 0.0075
-10.750 -0.5451 0.06328 0.05985 -0.0766 0.7286 0.0075
-10.500 -0.5582 0.06064 0.05711 -0.0747 0.7276 0.0075
-10.250 -0.5696 0.05828 0.05467 -0.0726 0.7265 0.0075
-10.000 -0.5827 0.05586 0.05212 -0.0693 0.7254 0.0076
-9.750 -0.5940 0.05382 0.04999 -0.0656 0.7242 0.0076
-9.500 -0.6005 0.05173 0.04777 -0.0623 0.7231 0.0076
-9.250 -0.6030 0.04923 0.04512 -0.0594 0.7221 0.0076
-9.000 -0.6025 0.04663 0.04235 -0.0567 0.7211 0.0076
-8.750 -0.5980 0.04426 0.03983 -0.0545 0.7202 0.0076
-8.500 -0.5928 0.04155 0.03691 -0.0519 0.7193 0.0076
-8.250 -0.5853 0.02256 0.01784 -0.0458 0.7167 0.0082
-8.000 -0.5738 0.02096 0.01616 -0.0448 0.7157 0.0085
-7.750 -0.5595 0.01937 0.01447 -0.0438 0.7151 0.0088
-7.500 -0.5429 0.01770 0.01268 -0.0429 0.7144 0.0092
-7.250 -0.5242 0.01627 0.01113 -0.0422 0.7138 0.0100
-7.000 -0.4986 0.01585 0.01060 -0.0415 0.7131 0.0116
-6.750 -0.4768 0.01556 0.01018 -0.0406 0.7123 0.0121
-6.500 -0.4563 0.01420 0.00866 -0.0398 0.7116 0.0121
-6.250 -0.4350 0.01289 0.00718 -0.0392 0.7109 0.0122
-6.000 -0.3976 0.00869 0.00281 -0.0411 0.7104 0.0135
-5.750 -0.3674 0.00766 0.00177 -0.0419 0.7098 0.0140
-5.500 -0.2782 0.01705 0.01082 -0.0518 0.7107 0.0097
-5.250 -0.2614 0.01641 0.01017 -0.0502 0.7100 0.0103
-5.000 -0.2491 0.01569 0.00941 -0.0483 0.7092 0.0105
-4.750 -0.2405 0.01484 0.00854 -0.0460 0.7084 0.0107
-4.500 -0.2317 0.01414 0.00781 -0.0437 0.7075 0.0113
-4.250 -0.2277 0.01355 0.00717 -0.0406 0.7067 0.0115
-4.000 -0.2128 0.01307 0.00665 -0.0391 0.7060 0.0118
-3.750 -0.1929 0.01274 0.00628 -0.0383 0.7053 0.0122
-3.500 -0.1821 0.01189 0.00533 -0.0362 0.7044 0.0131
-3.250 -0.1616 0.01144 0.00481 -0.0355 0.7035 0.0141
-3.000 -0.1378 0.01116 0.00450 -0.0353 0.7028 0.0162
-2.750 -0.1124 0.01099 0.00430 -0.0354 0.7020 0.0186
-2.500 -0.0877 0.01070 0.00398 -0.0353 0.7014 0.0274
-2.250 -0.0688 0.00982 0.00354 -0.0347 0.7010 0.1894
-2.000 -0.0612 0.00739 0.00256 -0.0333 0.7004 0.5909
-1.750 -0.0317 0.00754 0.00270 -0.0339 0.6999 0.6098
-1.500 -0.0020 0.00774 0.00289 -0.0345 0.6994 0.6202
-1.250 0.0273 0.00782 0.00299 -0.0351 0.6987 0.6258
-1.000 0.0568 0.00788 0.00305 -0.0358 0.6979 0.6283
-0.750 0.0864 0.00794 0.00310 -0.0365 0.6973 0.6306
-0.500 0.1160 0.00801 0.00315 -0.0372 0.6967 0.6329
-0.250 0.1454 0.00809 0.00322 -0.0379 0.6961 0.6366
0.000 0.1747 0.00813 0.00329 -0.0385 0.6953 0.6391
0.250 0.2042 0.00814 0.00331 -0.0393 0.6945 0.6401
0.500 0.2337 0.00816 0.00333 -0.0400 0.6937 0.6410
0.750 0.2632 0.00818 0.00336 -0.0407 0.6929 0.6420
1.000 0.2927 0.00820 0.00338 -0.0414 0.6921 0.6430
1.250 0.3222 0.00823 0.00341 -0.0422 0.6912 0.6441
1.500 0.3518 0.00825 0.00344 -0.0429 0.6901 0.6451
1.750 0.3814 0.00831 0.00349 -0.0436 0.6888 0.6463
2.000 0.4105 0.00839 0.00358 -0.0443 0.6870 0.6473
2.250 0.4396 0.00832 0.00355 -0.0449 0.6848 0.6482
2.500 0.4687 0.00824 0.00349 -0.0455 0.6816 0.6490
2.750 0.4981 0.00807 0.00332 -0.0461 0.6777 0.6501
3.000 0.5276 0.00802 0.00325 -0.0467 0.6735 0.6513
3.250 0.5559 0.00787 0.00319 -0.0471 0.6697 0.6523
3.500 0.5848 0.00776 0.00312 -0.0476 0.6655 0.6533
3.750 0.6140 0.00766 0.00302 -0.0481 0.6607 0.6543
4.000 0.6421 0.00755 0.00298 -0.0485 0.6543 0.6555
4.250 0.6706 0.00744 0.00291 -0.0489 0.6476 0.6567
4.500 0.6988 0.00738 0.00292 -0.0493 0.6402 0.6579
4.750 0.7270 0.00734 0.00289 -0.0497 0.6319 0.6590
5.000 0.7548 0.00729 0.00289 -0.0500 0.6167 0.6601
5.250 0.7786 0.00739 0.00289 -0.0495 0.5684 0.6611
5.500 0.7857 0.00840 0.00339 -0.0461 0.4628 0.6621
5.750 0.7874 0.00962 0.00409 -0.0420 0.3546 0.6629
6.000 0.7916 0.01054 0.00464 -0.0383 0.2761 0.6642
6.250 0.7969 0.01127 0.00512 -0.0347 0.2188 0.6656
6.500 0.7987 0.01187 0.00555 -0.0304 0.1776 0.6670
6.750 0.8036 0.01250 0.00606 -0.0268 0.1463 0.6682
7.000 0.8086 0.01326 0.00667 -0.0235 0.1145 0.6694
7.250 0.8159 0.01402 0.00731 -0.0208 0.0884 0.6707
7.500 0.8250 0.01477 0.00798 -0.0185 0.0672 0.6719
7.750 0.8363 0.01548 0.00862 -0.0167 0.0521 0.6732
8.000 0.8485 0.01620 0.00929 -0.0151 0.0397 0.6744
8.250 0.8636 0.01680 0.00988 -0.0139 0.0347 0.6755
8.500 0.8791 0.01742 0.01051 -0.0128 0.0296 0.6766
8.750 0.8944 0.01806 0.01113 -0.0117 0.0257 0.6777
9.000 0.9095 0.01869 0.01178 -0.0107 0.0208 0.6796
9.500 0.9320 0.02049 0.01352 -0.0077 0.0071 0.6823
9.750 0.9461 0.02127 0.01436 -0.0066 0.0062 0.6837
10.000 0.9607 0.02203 0.01518 -0.0056 0.0059 0.6851
10.250 0.9729 0.02297 0.01618 -0.0044 0.0052 0.6864
10.500 0.9878 0.02374 0.01700 -0.0035 0.0050 0.6878
10.750 1.0001 0.02470 0.01802 -0.0024 0.0046 0.6892
11.000 1.0105 0.02582 0.01921 -0.0010 0.0044 0.6904
11.250 1.0205 0.02700 0.02047 0.0003 0.0042 0.6915
11.500 1.0314 0.02808 0.02165 0.0014 0.0041 0.6934
11.750 1.0355 0.02971 0.02343 0.0031 0.0040 0.6951
12.000 1.0404 0.03135 0.02520 0.0047 0.0039 0.6967
12.250 1.0489 0.03274 0.02668 0.0058 0.0038 0.6983
12.500 1.0598 0.03398 0.02800 0.0066 0.0038 0.7000
12.750 1.0679 0.03548 0.02960 0.0076 0.0038 0.7016
13.000 1.0794 0.03671 0.03091 0.0082 0.0037 0.7032
13.250 1.0863 0.03838 0.03268 0.0091 0.0037 0.7047
13.500 1.0957 0.03986 0.03425 0.0098 0.0035 0.7062
13.750 1.0985 0.04201 0.03656 0.0108 0.0036 0.7081
14.000 1.1047 0.04387 0.03854 0.0115 0.0035 0.7100
14.250 1.1110 0.04577 0.04055 0.0121 0.0033 0.7118
14.500 1.1146 0.04800 0.04292 0.0126 0.0033 0.7137
14.750 1.1150 0.05066 0.04574 0.0132 0.0033 0.7155
15.000 1.1150 0.05343 0.04867 0.0137 0.0032 0.7173
15.250 1.1158 0.05620 0.05155 0.0138 0.0031 0.7190
15.500 1.1143 0.05930 0.05481 0.0138 0.0031 0.7210
15.750 1.1078 0.06318 0.05888 0.0137 0.0031 0.7230
16.000 1.1011 0.06722 0.06310 0.0132 0.0031 0.7251
16.250 1.0924 0.07176 0.06781 0.0124 0.0031 0.7271
16.500 1.0816 0.07684 0.07307 0.0110 0.0030 0.7290
16.750 1.0703 0.08223 0.07863 0.0092 0.0031 0.7308
17.000 1.0542 0.08872 0.08531 0.0068 0.0031 0.7324
17.250 1.0370 0.09582 0.09259 0.0036 0.0031 0.7337
17.500 1.0208 0.10312 0.10006 -0.0002 0.0031 0.7353
17.750 1.0057 0.11058 0.10768 -0.0043 0.0030 0.7370
18.000 0.9833 0.12005 0.11733 -0.0097 0.0031 0.7381
18.250 0.9626 0.12967 0.12711 -0.0154 0.0031 0.7393
18.500 0.9405 0.14007 0.13766 -0.0217 0.0032 0.7402
18.750 0.9096 0.15359 0.15134 -0.0295 0.0032 0.7404
19.000 0.8676 0.17131 0.16919 -0.0390 0.0034 0.7394
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