NREL's S810 Airfoil (s810-nr) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: NREL's S810 Airfoil (s810-nr) Reynolds number: 1,000,000 Max Cl/Cd: 92.5 at α=4° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s810-nr-1000000-n5.txt Download as CSV file: xf-s810-nr-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.500 -0.4944 0.08262 0.07961 -0.0768 0.7068 0.0029
-12.250 -0.5166 0.07749 0.07440 -0.0782 0.7059 0.0031
-12.000 -0.5419 0.07248 0.06929 -0.0786 0.7050 0.0028
-11.750 -0.5613 0.06861 0.06533 -0.0783 0.7040 0.0028
-11.500 -0.5855 0.06451 0.06112 -0.0771 0.7030 0.0028
-11.000 -0.6190 0.05847 0.05487 -0.0736 0.7011 0.0028
-10.750 -0.6333 0.05588 0.05219 -0.0711 0.7003 0.0029
-10.500 -0.6467 0.05345 0.04965 -0.0681 0.6994 0.0030
-10.250 -0.6646 0.05068 0.04674 -0.0636 0.6984 0.0028
-10.000 -0.6697 0.04886 0.04481 -0.0604 0.6975 0.0031
-9.750 -0.6737 0.04609 0.04188 -0.0573 0.6966 0.0031
-9.500 -0.6721 0.04343 0.03905 -0.0546 0.6957 0.0032
-9.250 -0.6681 0.04049 0.03592 -0.0519 0.6948 0.0035
-9.000 -0.6593 0.03741 0.03262 -0.0496 0.6940 0.0038
-8.750 -0.6482 0.03434 0.02932 -0.0475 0.6932 0.0038
-8.500 -0.6311 0.03142 0.02618 -0.0460 0.6924 0.0040
-8.250 -0.6090 0.02823 0.02276 -0.0452 0.6917 0.0040
-8.000 -0.5728 0.02495 0.01924 -0.0462 0.6911 0.0043
-7.750 -0.4901 0.02140 0.01537 -0.0537 0.6909 0.0044
-7.250 -0.4188 0.01944 0.01313 -0.0534 0.6898 0.0047
-7.000 -0.4014 0.01891 0.01255 -0.0524 0.6889 0.0046
-6.750 -0.3931 0.01797 0.01154 -0.0501 0.6881 0.0049
-6.500 -0.3817 0.01720 0.01074 -0.0484 0.6873 0.0051
-6.250 -0.3653 0.01666 0.01019 -0.0475 0.6867 0.0054
-6.000 -0.3513 0.01602 0.00952 -0.0462 0.6860 0.0056
-5.750 -0.3392 0.01529 0.00877 -0.0447 0.6852 0.0059
-5.500 -0.3271 0.01459 0.00804 -0.0431 0.6844 0.0061
-5.250 -0.3155 0.01393 0.00735 -0.0414 0.6837 0.0065
-5.000 -0.3120 0.01327 0.00666 -0.0383 0.6829 0.0066
-4.750 -0.2988 0.01275 0.00608 -0.0366 0.6822 0.0067
-4.500 -0.2810 0.01233 0.00561 -0.0355 0.6815 0.0071
-4.250 -0.2610 0.01195 0.00519 -0.0348 0.6808 0.0073
-4.000 -0.2382 0.01168 0.00490 -0.0345 0.6802 0.0076
-3.750 -0.2171 0.01128 0.00445 -0.0339 0.6795 0.0083
-3.500 -0.1936 0.01098 0.00413 -0.0336 0.6789 0.0093
-3.250 -0.1685 0.01075 0.00389 -0.0337 0.6783 0.0104
-3.000 -0.1426 0.01056 0.00368 -0.0338 0.6777 0.0119
-2.750 -0.1168 0.01035 0.00347 -0.0340 0.6771 0.0152
-2.500 -0.0899 0.01021 0.00332 -0.0343 0.6765 0.0189
-2.250 -0.0631 0.01006 0.00317 -0.0346 0.6759 0.0251
-2.000 -0.0371 0.00982 0.00300 -0.0348 0.6752 0.0598
-1.750 -0.0337 0.00685 0.00171 -0.0330 0.6743 0.5630
-1.500 -0.0047 0.00686 0.00176 -0.0336 0.6736 0.5897
-1.250 0.0248 0.00689 0.00180 -0.0343 0.6732 0.5994
-1.000 0.0544 0.00690 0.00180 -0.0350 0.6727 0.6030
-0.750 0.0841 0.00693 0.00180 -0.0357 0.6723 0.6059
-0.500 0.1136 0.00694 0.00180 -0.0365 0.6718 0.6083
-0.250 0.1430 0.00697 0.00186 -0.0371 0.6713 0.6132
0.000 0.1726 0.00700 0.00190 -0.0378 0.6707 0.6165
0.250 0.2022 0.00701 0.00191 -0.0385 0.6700 0.6175
0.500 0.2317 0.00702 0.00192 -0.0393 0.6693 0.6185
0.750 0.2613 0.00704 0.00194 -0.0400 0.6686 0.6194
1.000 0.2908 0.00706 0.00196 -0.0407 0.6679 0.6204
1.250 0.3203 0.00708 0.00198 -0.0414 0.6671 0.6212
1.500 0.3497 0.00708 0.00201 -0.0421 0.6661 0.6223
1.750 0.3791 0.00708 0.00204 -0.0428 0.6650 0.6233
2.000 0.4084 0.00707 0.00205 -0.0435 0.6633 0.6242
2.250 0.4376 0.00706 0.00205 -0.0441 0.6607 0.6251
2.500 0.4665 0.00703 0.00206 -0.0446 0.6569 0.6261
2.750 0.4953 0.00696 0.00203 -0.0452 0.6515 0.6271
3.000 0.5240 0.00693 0.00199 -0.0456 0.6459 0.6281
3.250 0.5530 0.00690 0.00203 -0.0462 0.6397 0.6292
3.500 0.5816 0.00688 0.00203 -0.0467 0.6329 0.6304
3.750 0.6102 0.00687 0.00205 -0.0472 0.6222 0.6315
4.000 0.6373 0.00689 0.00203 -0.0474 0.5963 0.6324
4.250 0.6519 0.00757 0.00229 -0.0453 0.5005 0.6334
4.500 0.6628 0.00851 0.00282 -0.0428 0.4077 0.6342
4.750 0.6770 0.00922 0.00324 -0.0408 0.3417 0.6350
5.000 0.6920 0.00980 0.00361 -0.0390 0.2891 0.6360
5.250 0.7046 0.01043 0.00402 -0.0368 0.2363 0.6371
5.500 0.7162 0.01103 0.00442 -0.0343 0.1895 0.6383
5.750 0.7280 0.01153 0.00480 -0.0319 0.1563 0.6395
6.000 0.7343 0.01202 0.00517 -0.0284 0.1253 0.6407
6.250 0.7409 0.01265 0.00567 -0.0252 0.0941 0.6418
6.500 0.7520 0.01322 0.00616 -0.0229 0.0744 0.6429
6.750 0.7668 0.01369 0.00660 -0.0212 0.0640 0.6440
7.000 0.7801 0.01425 0.00711 -0.0195 0.0507 0.6451
7.250 0.7938 0.01482 0.00764 -0.0179 0.0400 0.6461
7.750 0.8244 0.01594 0.00874 -0.0154 0.0276 0.6482
8.000 0.8389 0.01658 0.00935 -0.0141 0.0211 0.6491
8.250 0.8566 0.01706 0.00987 -0.0133 0.0202 0.6504
8.500 0.8719 0.01768 0.01050 -0.0122 0.0162 0.6517
8.750 0.8867 0.01835 0.01117 -0.0111 0.0116 0.6529
9.000 0.8985 0.01921 0.01200 -0.0096 0.0057 0.6541
9.250 0.9146 0.01985 0.01267 -0.0087 0.0051 0.6552
9.500 0.9291 0.02060 0.01347 -0.0077 0.0037 0.6564
9.750 0.9448 0.02128 0.01420 -0.0068 0.0035 0.6577
10.000 0.9606 0.02197 0.01494 -0.0060 0.0034 0.6589
10.250 0.9745 0.02280 0.01582 -0.0049 0.0030 0.6600
10.500 0.9902 0.02351 0.01659 -0.0042 0.0030 0.6612
10.750 1.0045 0.02434 0.01745 -0.0033 0.0027 0.6622
11.250 1.0306 0.02618 0.01942 -0.0013 0.0024 0.6649
11.500 1.0445 0.02705 0.02037 -0.0005 0.0023 0.6664
11.750 1.0539 0.02828 0.02170 0.0008 0.0021 0.6677
12.000 1.0642 0.02947 0.02298 0.0019 0.0021 0.6691
12.250 1.0741 0.03071 0.02431 0.0029 0.0020 0.6704
12.500 1.0858 0.03182 0.02550 0.0037 0.0020 0.6718
12.750 1.0965 0.03304 0.02680 0.0046 0.0020 0.6732
13.000 1.1084 0.03418 0.02801 0.0052 0.0020 0.6746
13.250 1.1185 0.03551 0.02941 0.0060 0.0019 0.6759
13.500 1.1294 0.03677 0.03074 0.0066 0.0019 0.6770
13.750 1.1355 0.03849 0.03258 0.0075 0.0019 0.6784
14.000 1.1442 0.04000 0.03418 0.0082 0.0019 0.6800
14.250 1.1535 0.04151 0.03580 0.0087 0.0018 0.6816
14.500 1.1608 0.04322 0.03761 0.0092 0.0018 0.6832
14.750 1.1650 0.04528 0.03979 0.0099 0.0018 0.6849
15.000 1.1691 0.04741 0.04203 0.0104 0.0017 0.6866
15.250 1.1755 0.04936 0.04408 0.0106 0.0017 0.6886
15.500 1.1802 0.05155 0.04637 0.0108 0.0017 0.6902
16.000 1.1815 0.05700 0.05208 0.0111 0.0016 0.6934
16.250 1.1808 0.06004 0.05525 0.0110 0.0016 0.6951
16.500 1.1820 0.06296 0.05828 0.0106 0.0015 0.6969
16.750 1.1775 0.06669 0.06216 0.0101 0.0016 0.6986
17.000 1.1711 0.07085 0.06648 0.0092 0.0016 0.7003
17.250 1.1639 0.07534 0.07111 0.0080 0.0016 0.7019
17.500 1.1613 0.07933 0.07521 0.0066 0.0015 0.7036
17.750 1.1598 0.08327 0.07927 0.0050 0.0014 0.7052
18.000 1.1465 0.08927 0.08544 0.0026 0.0014 0.7066
18.250 1.1377 0.09479 0.09109 0.0001 0.0014 0.7082
18.500 1.1208 0.10198 0.09846 -0.0034 0.0014 0.7095
18.750 1.1106 0.10821 0.10482 -0.0068 0.0013 0.7112
19.000 1.0850 0.11775 0.11455 -0.0120 0.0014 0.7119
19.250 1.0705 0.12541 0.12234 -0.0164 0.0014 0.7133
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