NREL's S820 Airfoil (s820-nr) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: NREL's S820 Airfoil (s820-nr) Reynolds number: 500,000 Max Cl/Cd: 105.33 at α=6.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s820-nr-500000.txt Download as CSV file: xf-s820-nr-500000.csv |
XFOIL Version 6.96
Calculated polar for: NREL's S820 Airfoil
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
------ -------- --------- --------- -------- -------- --------
-11.500 -0.2641 0.08877 0.08633 -0.0979 0.9214 0.0135
-11.250 -0.2662 0.08337 0.08086 -0.1012 0.9057 0.0134
-11.000 -0.2798 0.07535 0.07273 -0.1066 0.8923 0.0134
-10.750 -0.2948 0.07004 0.06732 -0.1095 0.8817 0.0131
-10.500 -0.3145 0.06505 0.06217 -0.1114 0.8724 0.0132
-10.250 -0.3320 0.06118 0.05819 -0.1121 0.8641 0.0131
-10.000 -0.3487 0.05787 0.05473 -0.1118 0.8574 0.0130
-9.750 -0.3657 0.05472 0.05144 -0.1107 0.8507 0.0133
-9.500 -0.3789 0.05227 0.04883 -0.1088 0.8449 0.0133
-9.250 -0.3918 0.04996 0.04637 -0.1058 0.8393 0.0136
-9.000 -0.4010 0.04835 0.04452 -0.1019 0.8342 0.0139
-8.750 -0.4054 0.04712 0.04299 -0.0985 0.8301 0.0142
-8.500 -0.4078 0.04527 0.04089 -0.0956 0.8264 0.0143
-8.250 -0.4170 0.04028 0.03563 -0.0928 0.8226 0.0146
-8.000 -0.4075 0.03719 0.03247 -0.0920 0.8195 0.0150
-7.750 -0.3956 0.03522 0.03039 -0.0909 0.8166 0.0154
-7.500 -0.3822 0.03349 0.02850 -0.0898 0.8138 0.0159
-7.250 -0.3674 0.03173 0.02659 -0.0886 0.8110 0.0167
-7.000 -0.3502 0.03013 0.02478 -0.0872 0.8082 0.0180
-6.750 -0.3295 0.03119 0.02547 -0.0852 0.8054 0.0196
-6.500 -0.3160 0.02626 0.02031 -0.0843 0.8032 0.0209
-6.250 -0.2935 0.02471 0.01870 -0.0841 0.8010 0.0221
-6.000 -0.2706 0.02364 0.01748 -0.0835 0.7987 0.0240
-5.750 -0.2479 0.02528 0.01887 -0.0822 0.7959 0.0267
-5.500 -0.2042 0.01783 0.01096 -0.0821 0.7944 0.0106
-5.250 -0.1777 0.01685 0.00998 -0.0819 0.7922 0.0099
-5.000 -0.1549 0.01568 0.00877 -0.0811 0.7900 0.0094
-4.750 -0.1346 0.01487 0.00789 -0.0800 0.7878 0.0092
-4.500 -0.1153 0.01418 0.00712 -0.0787 0.7858 0.0092
-4.250 -0.0958 0.01358 0.00648 -0.0775 0.7836 0.0094
-4.000 -0.0746 0.01310 0.00597 -0.0767 0.7810 0.0099
-3.750 -0.0539 0.01253 0.00533 -0.0757 0.7784 0.0112
-3.500 -0.0296 0.01220 0.00497 -0.0753 0.7761 0.0137
-3.250 -0.0062 0.01175 0.00449 -0.0748 0.7740 0.0262
-3.000 -0.0108 0.00883 0.00379 -0.0710 0.7717 0.6183
-2.750 0.0161 0.00920 0.00419 -0.0706 0.7698 0.6565
-2.500 0.0424 0.00974 0.00480 -0.0698 0.7676 0.6830
-2.250 0.0705 0.00987 0.00492 -0.0699 0.7654 0.6889
-2.000 0.0992 0.00986 0.00483 -0.0704 0.7631 0.6914
-1.750 0.1282 0.00984 0.00473 -0.0709 0.7610 0.6939
-1.500 0.1574 0.00982 0.00462 -0.0715 0.7592 0.6959
-1.250 0.1866 0.00980 0.00456 -0.0720 0.7576 0.6976
-1.000 0.2158 0.00985 0.00457 -0.0726 0.7559 0.6995
-0.750 0.2436 0.00985 0.00459 -0.0729 0.7537 0.7015
-0.500 0.2717 0.00987 0.00459 -0.0732 0.7513 0.7037
-0.250 0.3002 0.00988 0.00458 -0.0737 0.7490 0.7060
0.000 0.3290 0.00990 0.00457 -0.0742 0.7471 0.7083
0.250 0.3582 0.00992 0.00455 -0.0748 0.7452 0.7107
0.500 0.3874 0.00991 0.00454 -0.0753 0.7435 0.7127
0.750 0.4168 0.00997 0.00459 -0.0759 0.7418 0.7147
1.000 0.4442 0.01002 0.00468 -0.0762 0.7396 0.7169
1.250 0.4718 0.01006 0.00476 -0.0765 0.7370 0.7193
1.500 0.5000 0.01009 0.00481 -0.0769 0.7345 0.7219
1.750 0.5287 0.01011 0.00482 -0.0774 0.7321 0.7244
2.000 0.5581 0.01008 0.00479 -0.0779 0.7297 0.7267
2.250 0.5881 0.01010 0.00480 -0.0786 0.7272 0.7290
2.500 0.6136 0.01005 0.00483 -0.0783 0.7221 0.7316
2.750 0.6423 0.00988 0.00468 -0.0786 0.7163 0.7343
3.000 0.6710 0.00976 0.00454 -0.0789 0.7106 0.7371
3.250 0.6979 0.00968 0.00449 -0.0789 0.7045 0.7399
3.500 0.7270 0.00955 0.00438 -0.0792 0.6997 0.7423
3.750 0.7531 0.00952 0.00443 -0.0791 0.6944 0.7448
4.000 0.7802 0.00945 0.00442 -0.0791 0.6886 0.7476
4.250 0.8079 0.00939 0.00437 -0.0793 0.6826 0.7507
4.500 0.8335 0.00933 0.00439 -0.0790 0.6747 0.7541
4.750 0.8603 0.00929 0.00438 -0.0790 0.6682 0.7570
5.000 0.8852 0.00925 0.00444 -0.0786 0.6596 0.7599
5.250 0.9102 0.00924 0.00451 -0.0782 0.6499 0.7631
5.500 0.9351 0.00924 0.00455 -0.0778 0.6389 0.7666
5.750 0.9583 0.00928 0.00460 -0.0771 0.6232 0.7700
6.000 0.9800 0.00933 0.00470 -0.0761 0.6049 0.7731
6.250 0.9985 0.00948 0.00484 -0.0744 0.5765 0.7766
6.500 1.0070 0.00989 0.00505 -0.0708 0.5229 0.7809
6.750 0.9999 0.01066 0.00549 -0.0644 0.4587 0.7856
7.000 0.9908 0.01151 0.00612 -0.0578 0.4066 0.7903
7.250 0.9850 0.01252 0.00690 -0.0523 0.3567 0.7957
7.500 0.9821 0.01356 0.00773 -0.0476 0.3103 0.8009
7.750 0.9821 0.01459 0.00859 -0.0436 0.2691 0.8061
8.000 0.9859 0.01559 0.00944 -0.0405 0.2334 0.8120
8.250 0.9911 0.01656 0.01032 -0.0377 0.2023 0.8176
8.500 0.9978 0.01753 0.01119 -0.0352 0.1744 0.8241
8.750 1.0063 0.01846 0.01204 -0.0330 0.1522 0.8310
9.000 1.0159 0.01933 0.01288 -0.0310 0.1327 0.8387
9.250 1.0261 0.02021 0.01374 -0.0292 0.1170 0.8470
9.500 1.0368 0.02108 0.01459 -0.0275 0.1030 0.8570
9.750 1.0481 0.02187 0.01542 -0.0258 0.0918 0.8686
10.000 1.0590 0.02265 0.01628 -0.0240 0.0826 0.8843
10.250 1.0674 0.02345 0.01716 -0.0218 0.0742 0.9133
10.500 1.0872 0.02426 0.01805 -0.0222 0.0649 1.0000
10.750 1.1021 0.02516 0.01897 -0.0215 0.0579 1.0000
11.000 1.1139 0.02627 0.02004 -0.0205 0.0505 1.0000
11.250 1.1272 0.02728 0.02101 -0.0196 0.0421 1.0000
11.500 1.1396 0.02835 0.02211 -0.0187 0.0356 1.0000
11.750 1.1508 0.02953 0.02327 -0.0177 0.0287 1.0000
12.000 1.1612 0.03077 0.02446 -0.0167 0.0225 1.0000
12.250 1.1713 0.03208 0.02578 -0.0157 0.0187 1.0000
12.500 1.1823 0.03333 0.02706 -0.0148 0.0155 1.0000
12.750 1.1906 0.03484 0.02858 -0.0137 0.0132 1.0000
13.000 1.2009 0.03619 0.03000 -0.0129 0.0112 1.0000
13.250 1.2099 0.03770 0.03155 -0.0121 0.0097 1.0000
13.500 1.2162 0.03948 0.03341 -0.0110 0.0082 1.0000
13.750 1.2235 0.04120 0.03519 -0.0102 0.0067 1.0000
14.000 1.2262 0.04342 0.03752 -0.0092 0.0056 1.0000
14.250 1.2321 0.04536 0.03955 -0.0085 0.0047 1.0000
14.500 1.2300 0.04817 0.04246 -0.0075 0.0039 1.0000
14.750 1.2330 0.05056 0.04497 -0.0070 0.0037 1.0000
15.000 1.2360 0.05298 0.04751 -0.0066 0.0034 1.0000
15.250 1.2376 0.05566 0.05028 -0.0063 0.0028 1.0000
15.500 1.2303 0.05945 0.05419 -0.0061 0.0025 1.0000
15.750 1.2282 0.06277 0.05765 -0.0061 0.0024 1.0000
16.000 1.2255 0.06630 0.06133 -0.0063 0.0023 1.0000
16.250 1.2240 0.06977 0.06492 -0.0068 0.0022 1.0000
16.500 1.2203 0.07368 0.06898 -0.0075 0.0020 1.0000
16.750 1.2162 0.07780 0.07324 -0.0085 0.0019 1.0000
17.000 1.2060 0.08289 0.07849 -0.0098 0.0020 1.0000
17.250 1.1991 0.08775 0.08349 -0.0114 0.0020 1.0000
17.500 1.1894 0.09323 0.08912 -0.0135 0.0020 1.0000
17.750 1.1811 0.09873 0.09477 -0.0158 0.0018 1.0000
18.000 1.1682 0.10516 0.10135 -0.0187 0.0018 1.0000
18.250 1.1582 0.11137 0.10769 -0.0219 0.0016 1.0000
18.500 1.1468 0.11786 0.11436 -0.0252 0.0018 1.0000
18.750 1.1327 0.12515 0.12180 -0.0291 0.0017 1.0000
19.000 1.1212 0.13207 0.12885 -0.0330 0.0017 1.0000
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