NREL's S801 Airfoil (s801-nr) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: NREL's S801 Airfoil (s801-nr) Reynolds number: 200,000 Max Cl/Cd: 85.24 at α=7.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s801-nr-200000.txt Download as CSV file: xf-s801-nr-200000.csv |
XFOIL Version 6.96
Calculated polar for: NREL's S801 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.2923 0.09120 0.08788 -0.0723 0.9785 0.0639
-9.000 -0.3179 0.07834 0.07499 -0.0968 0.9626 0.0667
-8.750 -0.3340 0.07015 0.06660 -0.1076 0.9487 0.0673
-8.500 -0.2769 0.07141 0.06813 -0.0962 0.9540 0.0700
-8.250 -0.2632 0.06631 0.06299 -0.1030 0.9482 0.0721
-8.000 -0.2638 0.05985 0.05641 -0.1117 0.9363 0.0749
-7.750 -0.2782 0.05150 0.04738 -0.1226 0.9229 0.0812
-7.500 -0.2458 0.04811 0.04412 -0.1250 0.9208 0.0836
-7.250 -0.2506 0.03589 0.03054 -0.1280 0.9087 0.0568
-7.000 -0.2197 0.03045 0.02410 -0.1297 0.9048 0.0451
-6.750 -0.1988 0.02698 0.02038 -0.1298 0.8973 0.0440
-6.500 -0.1682 0.02452 0.01754 -0.1310 0.8926 0.0438
-6.250 -0.1332 0.02264 0.01532 -0.1328 0.8892 0.0442
-6.000 -0.1105 0.02142 0.01386 -0.1321 0.8819 0.0456
-5.750 -0.0808 0.01986 0.01224 -0.1328 0.8773 0.0472
-5.500 -0.0477 0.01874 0.01105 -0.1339 0.8738 0.0488
-5.250 -0.0260 0.01809 0.01036 -0.1328 0.8669 0.0504
-5.000 0.0022 0.01737 0.00956 -0.1330 0.8620 0.0528
-4.750 0.0327 0.01655 0.00869 -0.1338 0.8584 0.0569
-4.500 0.0540 0.01609 0.00827 -0.1329 0.8526 0.0620
-4.250 0.0796 0.01548 0.00765 -0.1329 0.8479 0.0705
-4.000 0.1082 0.01444 0.00690 -0.1337 0.8443 0.1257
-3.750 0.1347 0.01341 0.00658 -0.1348 0.8406 0.2831
-3.500 0.1575 0.01274 0.00650 -0.1349 0.8354 0.4296
-3.250 0.1798 0.01243 0.00690 -0.1335 0.8314 0.5975
-3.000 0.2055 0.01293 0.00749 -0.1321 0.8284 0.6851
-2.750 0.2312 0.01351 0.00798 -0.1310 0.8254 0.7218
-2.500 0.2495 0.01404 0.00851 -0.1285 0.8209 0.7396
-2.250 0.2712 0.01447 0.00889 -0.1266 0.8172 0.7555
-2.000 0.2946 0.01483 0.00918 -0.1250 0.8141 0.7706
-1.750 0.3205 0.01511 0.00938 -0.1240 0.8117 0.7840
-1.500 0.3353 0.01548 0.00976 -0.1208 0.8079 0.7936
-1.250 0.3527 0.01577 0.01004 -0.1185 0.8039 0.8049
-1.000 0.3758 0.01595 0.01017 -0.1173 0.8006 0.8163
-0.750 0.3978 0.01608 0.01025 -0.1156 0.7980 0.8258
-0.500 0.4220 0.01617 0.01030 -0.1145 0.7959 0.8352
-0.250 0.4389 0.01647 0.01059 -0.1127 0.7916 0.8454
0.000 0.4529 0.01661 0.01075 -0.1097 0.7875 0.8534
0.250 0.4768 0.01668 0.01079 -0.1090 0.7844 0.8620
0.500 0.5010 0.01668 0.01076 -0.1080 0.7819 0.8696
0.750 0.5306 0.01670 0.01072 -0.1084 0.7799 0.8765
1.000 0.5380 0.01703 0.01112 -0.1048 0.7742 0.8833
1.250 0.5649 0.01716 0.01124 -0.1051 0.7705 0.8888
1.500 0.5899 0.01709 0.01116 -0.1045 0.7675 0.8931
1.750 0.6211 0.01704 0.01108 -0.1052 0.7652 0.8972
2.000 0.6388 0.01740 0.01149 -0.1039 0.7600 0.9020
2.250 0.6608 0.01751 0.01162 -0.1032 0.7554 0.9057
2.500 0.6909 0.01741 0.01153 -0.1036 0.7520 0.9088
2.750 0.7267 0.01726 0.01134 -0.1051 0.7493 0.9117
3.000 0.7425 0.01761 0.01177 -0.1035 0.7424 0.9155
3.250 0.7745 0.01748 0.01165 -0.1043 0.7376 0.9181
3.500 0.8112 0.01716 0.01132 -0.1058 0.7341 0.9202
3.750 0.8288 0.01732 0.01155 -0.1041 0.7266 0.9236
4.000 0.8628 0.01699 0.01124 -0.1051 0.7208 0.9263
4.250 0.8953 0.01678 0.01104 -0.1059 0.7146 0.9288
4.500 0.9237 0.01660 0.01090 -0.1060 0.7065 0.9313
4.750 0.9562 0.01623 0.01055 -0.1065 0.6998 0.9339
5.000 0.9797 0.01603 0.01042 -0.1056 0.6908 0.9376
5.250 1.0102 0.01579 0.01020 -0.1059 0.6832 0.9404
5.500 1.0386 0.01554 0.01000 -0.1059 0.6740 0.9435
5.750 1.0627 0.01534 0.00988 -0.1051 0.6639 0.9473
6.000 1.0932 0.01497 0.00952 -0.1053 0.6541 0.9513
6.250 1.1162 0.01474 0.00937 -0.1043 0.6419 0.9565
6.500 1.1379 0.01455 0.00929 -0.1030 0.6281 0.9622
6.750 1.1613 0.01435 0.00916 -0.1021 0.6119 0.9698
7.000 1.1856 0.01422 0.00912 -0.1016 0.5911 0.9854
7.250 1.2052 0.01419 0.00913 -0.1002 0.5634 1.0000
7.500 1.2206 0.01432 0.00917 -0.0980 0.5209 1.0000
7.750 1.2284 0.01487 0.00938 -0.0946 0.4623 1.0000
8.000 1.2299 0.01598 0.01011 -0.0906 0.4033 1.0000
8.250 1.2293 0.01733 0.01114 -0.0867 0.3504 1.0000
8.500 1.2286 0.01881 0.01235 -0.0831 0.3031 1.0000
8.750 1.2283 0.02041 0.01371 -0.0799 0.2615 1.0000
9.000 1.2299 0.02205 0.01515 -0.0772 0.2247 1.0000
9.250 1.2327 0.02374 0.01666 -0.0749 0.1947 1.0000
9.500 1.2360 0.02549 0.01824 -0.0728 0.1713 1.0000
9.750 1.2429 0.02709 0.01976 -0.0712 0.1512 1.0000
10.000 1.2496 0.02875 0.02134 -0.0696 0.1356 1.0000
10.250 1.2569 0.03041 0.02294 -0.0681 0.1233 1.0000
10.500 1.2634 0.03217 0.02464 -0.0666 0.1133 1.0000
10.750 1.2732 0.03372 0.02619 -0.0655 0.1042 1.0000
11.000 1.2828 0.03533 0.02782 -0.0643 0.0969 1.0000
11.250 1.2921 0.03696 0.02943 -0.0632 0.0907 1.0000
11.500 1.3029 0.03857 0.03108 -0.0621 0.0853 1.0000
11.750 1.3143 0.04007 0.03263 -0.0612 0.0802 1.0000
12.000 1.3257 0.04180 0.03428 -0.0601 0.0756 1.0000
12.250 1.3385 0.04324 0.03589 -0.0593 0.0720 1.0000
12.500 1.3505 0.04478 0.03749 -0.0585 0.0684 1.0000
12.750 1.3686 0.04635 0.03893 -0.0578 0.0643 1.0000
13.000 1.3791 0.04797 0.04076 -0.0570 0.0621 1.0000
13.250 1.3909 0.04963 0.04258 -0.0563 0.0594 1.0000
13.500 1.4017 0.05134 0.04433 -0.0556 0.0568 1.0000
13.750 1.4235 0.05305 0.04600 -0.0552 0.0534 1.0000
14.000 1.4293 0.05510 0.04828 -0.0543 0.0519 1.0000
14.250 1.4357 0.05723 0.05060 -0.0536 0.0498 1.0000
14.500 1.4410 0.05938 0.05287 -0.0530 0.0477 1.0000
14.750 1.4488 0.06141 0.05489 -0.0526 0.0457 1.0000
15.000 1.3158 0.06855 0.06311 -0.0443 0.0466 1.0000
15.250 1.3246 0.07129 0.06584 -0.0438 0.0441 1.0000
15.500 1.3096 0.07543 0.07029 -0.0436 0.0433 1.0000
15.750 1.2900 0.07954 0.07471 -0.0434 0.0424 1.0000
16.000 1.2728 0.08357 0.07901 -0.0437 0.0414 1.0000
16.250 1.2583 0.08759 0.08326 -0.0444 0.0403 1.0000
16.500 1.2454 0.09158 0.08743 -0.0456 0.0390 1.0000
16.750 1.2374 0.09510 0.09105 -0.0468 0.0379 1.0000
17.000 1.2361 0.09767 0.09363 -0.0474 0.0361 1.0000
17.250 1.2137 0.10335 0.09957 -0.0497 0.0358 1.0000
17.500 1.1882 0.10977 0.10628 -0.0530 0.0355 1.0000
17.750 1.1616 0.11672 0.11350 -0.0569 0.0354 1.0000
18.000 1.1309 0.12475 0.12180 -0.0618 0.0354 1.0000
18.250 1.0983 0.13359 0.13088 -0.0675 0.0356 1.0000
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