NREL's S810 Airfoil (s810-nr) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: NREL's S810 Airfoil (s810-nr) Reynolds number: 200,000 Max Cl/Cd: 52.21 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s810-nr-200000-n5.txt Download as CSV file: xf-s810-nr-200000-n5.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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.000 -0.4726 0.06808 0.06320 -0.0745 0.7755 0.0190
-8.250 -0.5627 0.04409 0.03703 -0.0554 0.7612 0.0177
-8.000 -0.5501 0.04066 0.03339 -0.0541 0.7600 0.0161
-7.750 -0.5310 0.03770 0.03010 -0.0528 0.7590 0.0145
-7.500 -0.4991 0.03440 0.02627 -0.0518 0.7581 0.0127
-7.250 -0.4721 0.03272 0.02437 -0.0517 0.7569 0.0125
-7.000 -0.4413 0.03099 0.02246 -0.0522 0.7558 0.0124
-6.750 -0.3801 0.02807 0.01936 -0.0569 0.7553 0.0126
-6.500 -0.3242 0.02660 0.01780 -0.0598 0.7547 0.0131
-6.250 -0.2918 0.02590 0.01709 -0.0602 0.7536 0.0141
-6.000 -0.2666 0.02540 0.01657 -0.0600 0.7522 0.0159
-5.750 -0.2387 0.02491 0.01602 -0.0596 0.7510 0.0172
-5.500 -0.2156 0.02438 0.01545 -0.0586 0.7499 0.0175
-5.250 -0.1985 0.02375 0.01481 -0.0572 0.7488 0.0179
-5.000 -0.1851 0.02306 0.01408 -0.0556 0.7477 0.0182
-4.750 -0.1735 0.02231 0.01330 -0.0539 0.7466 0.0187
-4.500 -0.1675 0.02132 0.01227 -0.0517 0.7455 0.0194
-4.250 -0.1661 0.02019 0.01107 -0.0490 0.7445 0.0203
-4.000 -0.1638 0.01939 0.01021 -0.0462 0.7432 0.0215
-3.750 -0.1590 0.01884 0.00962 -0.0435 0.7418 0.0235
-3.500 -0.1460 0.01843 0.00915 -0.0419 0.7404 0.0275
-3.250 -0.1326 0.01798 0.00857 -0.0403 0.7388 0.0309
-3.000 -0.1163 0.01759 0.00811 -0.0390 0.7375 0.0389
-2.750 -0.1182 0.01611 0.00727 -0.0358 0.7360 0.2423
-2.500 -0.1216 0.01479 0.00743 -0.0316 0.7347 0.5967
-2.250 -0.0936 0.01572 0.00836 -0.0312 0.7338 0.6271
-2.000 -0.0660 0.01617 0.00872 -0.0312 0.7330 0.6377
-1.750 -0.0383 0.01669 0.00918 -0.0311 0.7321 0.6482
-1.500 -0.0092 0.01731 0.00983 -0.0309 0.7313 0.6539
-1.250 0.0184 0.01729 0.00974 -0.0314 0.7304 0.6555
-1.000 0.0451 0.01728 0.00967 -0.0318 0.7294 0.6571
-0.750 0.0709 0.01728 0.00964 -0.0321 0.7282 0.6590
-0.500 0.0966 0.01725 0.00957 -0.0326 0.7268 0.6611
-0.250 0.1225 0.01719 0.00945 -0.0330 0.7252 0.6631
0.000 0.1490 0.01725 0.00951 -0.0334 0.7238 0.6640
0.250 0.1756 0.01732 0.00960 -0.0337 0.7225 0.6649
0.500 0.2025 0.01739 0.00967 -0.0340 0.7211 0.6659
0.750 0.2296 0.01745 0.00976 -0.0343 0.7199 0.6671
1.000 0.2569 0.01752 0.00984 -0.0347 0.7187 0.6684
1.250 0.2846 0.01756 0.00989 -0.0352 0.7176 0.6698
1.500 0.3126 0.01759 0.00993 -0.0358 0.7166 0.6712
1.750 0.3390 0.01768 0.01004 -0.0361 0.7151 0.6727
2.000 0.3616 0.01788 0.01031 -0.0360 0.7122 0.6743
2.250 0.3864 0.01801 0.01048 -0.0362 0.7098 0.6760
2.500 0.4126 0.01809 0.01061 -0.0365 0.7076 0.6776
2.750 0.4396 0.01816 0.01074 -0.0368 0.7057 0.6787
3.000 0.4677 0.01818 0.01083 -0.0372 0.7040 0.6798
3.250 0.4969 0.01817 0.01088 -0.0378 0.7025 0.6810
3.500 0.5187 0.01840 0.01125 -0.0373 0.6987 0.6822
3.750 0.5418 0.01852 0.01147 -0.0370 0.6943 0.6835
4.000 0.5713 0.01836 0.01138 -0.0375 0.6910 0.6849
4.250 0.6053 0.01797 0.01101 -0.0386 0.6881 0.6863
4.500 0.6250 0.01797 0.01117 -0.0375 0.6797 0.6880
4.750 0.6619 0.01721 0.01041 -0.0388 0.6739 0.6898
5.000 0.6825 0.01706 0.01038 -0.0378 0.6638 0.6916
5.250 0.7075 0.01671 0.01015 -0.0373 0.6542 0.6927
5.500 0.7328 0.01632 0.00989 -0.0367 0.6433 0.6939
5.750 0.7525 0.01618 0.00993 -0.0355 0.6296 0.6952
6.000 0.7667 0.01616 0.01006 -0.0333 0.6073 0.6966
6.250 0.7941 0.01521 0.00890 -0.0323 0.5378 0.6980
6.500 0.7948 0.01561 0.00863 -0.0273 0.4399 0.6997
6.750 0.7849 0.01648 0.00918 -0.0212 0.3825 0.7016
7.000 0.7763 0.01760 0.01004 -0.0160 0.3308 0.7037
7.250 0.7716 0.01889 0.01108 -0.0120 0.2830 0.7057
7.500 0.7700 0.02017 0.01219 -0.0086 0.2394 0.7071
7.750 0.7710 0.02146 0.01334 -0.0059 0.1977 0.7085
8.000 0.7749 0.02271 0.01443 -0.0037 0.1597 0.7100
8.250 0.7812 0.02388 0.01547 -0.0018 0.1281 0.7116
8.500 0.7894 0.02501 0.01648 -0.0002 0.1021 0.7132
8.750 0.8001 0.02603 0.01746 0.0011 0.0835 0.7150
9.000 0.8115 0.02704 0.01844 0.0022 0.0701 0.7168
9.250 0.8234 0.02805 0.01945 0.0033 0.0603 0.7188
9.500 0.8345 0.02911 0.02050 0.0044 0.0513 0.7205
9.750 0.8474 0.03005 0.02147 0.0053 0.0431 0.7222
10.000 0.8608 0.03098 0.02250 0.0061 0.0369 0.7240
10.250 0.8724 0.03207 0.02361 0.0070 0.0309 0.7258
10.500 0.8866 0.03301 0.02467 0.0078 0.0276 0.7278
10.750 0.8989 0.03412 0.02585 0.0085 0.0232 0.7297
11.000 0.9102 0.03535 0.02715 0.0094 0.0183 0.7318
11.250 0.9212 0.03665 0.02845 0.0101 0.0146 0.7338
11.500 0.9315 0.03795 0.02990 0.0111 0.0128 0.7354
11.750 0.9420 0.03928 0.03131 0.0118 0.0107 0.7372
12.000 0.9496 0.04092 0.03305 0.0128 0.0099 0.7392
12.250 0.9575 0.04258 0.03487 0.0136 0.0093 0.7414
12.500 0.9653 0.04430 0.03678 0.0144 0.0088 0.7439
12.750 0.9726 0.04613 0.03875 0.0151 0.0083 0.7464
13.000 0.9794 0.04803 0.04081 0.0157 0.0081 0.7487
13.250 0.9854 0.05004 0.04298 0.0164 0.0078 0.7508
13.500 0.9911 0.05211 0.04521 0.0168 0.0075 0.7531
13.750 0.9948 0.05447 0.04773 0.0173 0.0072 0.7555
14.000 0.9985 0.05691 0.05033 0.0176 0.0071 0.7580
14.250 0.9988 0.05985 0.05343 0.0178 0.0069 0.7605
14.500 0.9996 0.06280 0.05657 0.0179 0.0068 0.7628
14.750 0.9968 0.06630 0.06029 0.0179 0.0067 0.7649
15.000 0.9941 0.06992 0.06413 0.0177 0.0066 0.7673
15.250 0.9898 0.07385 0.06830 0.0171 0.0066 0.7699
15.500 0.9841 0.07812 0.07279 0.0161 0.0065 0.7726
15.750 0.9749 0.08312 0.07804 0.0147 0.0065 0.7751
16.000 0.9644 0.08849 0.08366 0.0129 0.0065 0.7775
16.250 0.9524 0.09438 0.08980 0.0104 0.0065 0.7799
16.500 0.9376 0.10111 0.09678 0.0072 0.0064 0.7824
16.750 0.9237 0.10800 0.10386 0.0036 0.0065 0.7851
17.000 0.9064 0.11608 0.11216 -0.0010 0.0065 0.7875
17.250 0.8883 0.12489 0.12116 -0.0063 0.0065 0.7899
17.500 0.8698 0.13428 0.13072 -0.0120 0.0066 0.7918
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