NREL's S817 Airfoil (s817-nr) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: NREL's S817 Airfoil (s817-nr) Reynolds number: 50,000 Max Cl/Cd: 17.92 at α=10.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s817-nr-50000-n5.txt Download as CSV file: xf-s817-nr-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NREL's S817 Airfoil
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.750 -0.2673 0.12683 0.12019 -0.0838 0.9523 0.0948
-11.500 -0.2771 0.12395 0.11735 -0.0902 0.9471 0.0983
-11.250 -0.2868 0.12073 0.11417 -0.0957 0.9414 0.0989
-11.000 -0.2538 0.11519 0.10859 -0.0928 0.9390 0.1020
-10.750 -0.2443 0.11157 0.10494 -0.0945 0.9350 0.1048
-10.500 -0.2411 0.10769 0.10107 -0.0979 0.9316 0.1095
-10.250 -0.2795 0.10500 0.09846 -0.1050 0.9230 0.1135
-10.000 -0.2505 0.10040 0.09385 -0.1031 0.9212 0.1162
-9.750 -0.2397 0.09673 0.09015 -0.1042 0.9181 0.1210
-9.500 -0.2506 0.08941 0.08267 -0.1105 0.9116 0.0652
-9.250 -0.2612 0.08510 0.07827 -0.1120 0.9062 0.0520
-9.000 -0.2678 0.08158 0.07468 -0.1128 0.9024 0.0502
-8.750 -0.2883 0.08013 0.07322 -0.1097 0.8960 0.0490
-8.500 -0.3074 0.07820 0.07122 -0.1068 0.8909 0.0478
-8.250 -0.3265 0.07610 0.06898 -0.1037 0.8863 0.0459
-8.000 -0.3523 0.07571 0.06832 -0.0976 0.8796 0.0421
-7.750 -0.3559 0.07321 0.06573 -0.0954 0.8762 0.0415
-7.500 -0.3587 0.07066 0.06299 -0.0932 0.8736 0.0413
-7.250 -0.3780 0.06998 0.06225 -0.0872 0.8689 0.0411
-7.000 -0.3878 0.06847 0.06062 -0.0829 0.8650 0.0407
-6.750 -0.3900 0.06631 0.05825 -0.0798 0.8620 0.0405
-6.500 -0.3860 0.06395 0.05559 -0.0775 0.8596 0.0407
-6.250 -0.3963 0.06281 0.05429 -0.0723 0.8561 0.0407
-6.000 -0.4027 0.06142 0.05271 -0.0677 0.8530 0.0406
-5.750 -0.4000 0.05954 0.05056 -0.0645 0.8503 0.0406
-5.500 -0.3911 0.05739 0.04808 -0.0622 0.8479 0.0406
-5.250 -0.3771 0.05515 0.04546 -0.0605 0.8460 0.0402
-5.000 -0.3596 0.05284 0.04277 -0.0592 0.8446 0.0398
-4.750 -0.3561 0.05156 0.04122 -0.0555 0.8422 0.0396
-4.500 -0.3472 0.05014 0.03952 -0.0525 0.8398 0.0396
-4.250 -0.3310 0.04852 0.03756 -0.0505 0.8375 0.0398
-4.000 -0.3099 0.04711 0.03577 -0.0491 0.8356 0.0412
-3.750 -0.2864 0.04568 0.03401 -0.0481 0.8340 0.0441
-3.500 -0.2604 0.04439 0.03258 -0.0479 0.8328 0.0470
-3.250 -0.2228 0.04337 0.03137 -0.0483 0.8319 0.0505
-3.000 -0.1846 0.04281 0.03059 -0.0489 0.8309 0.0569
-2.750 -0.1594 0.04223 0.02995 -0.0479 0.8296 0.0630
-2.500 -0.1592 0.04209 0.02970 -0.0433 0.8265 0.0674
-2.250 -0.1545 0.04168 0.02925 -0.0398 0.8242 0.0744
-2.000 -0.1460 0.04129 0.02870 -0.0369 0.8219 0.0842
-1.750 -0.1358 0.04061 0.02804 -0.0346 0.8196 0.1014
-1.500 -0.1240 0.03963 0.02725 -0.0328 0.8176 0.1411
-1.250 -0.1375 0.03812 0.02826 -0.0239 0.8158 0.7049
-1.000 -0.0168 0.04446 0.03406 -0.0267 0.8170 0.9124
-0.750 -0.0107 0.04451 0.03392 -0.0237 0.8150 0.9163
-0.500 -0.0114 0.04458 0.03387 -0.0199 0.8113 0.9185
-0.250 -0.0028 0.04466 0.03380 -0.0177 0.8084 0.9206
0.000 0.0078 0.04474 0.03370 -0.0158 0.8058 0.9228
0.250 0.0207 0.04480 0.03360 -0.0141 0.8033 0.9246
0.500 0.0370 0.04490 0.03355 -0.0131 0.8011 0.9265
0.750 0.0297 0.04490 0.03349 -0.0081 0.7972 0.9306
1.000 0.0450 0.04511 0.03360 -0.0072 0.7938 0.9328
1.250 0.0640 0.04534 0.03372 -0.0069 0.7908 0.9349
1.500 0.0853 0.04559 0.03385 -0.0070 0.7882 0.9368
1.750 0.1052 0.04586 0.03402 -0.0067 0.7854 0.9392
2.000 0.1062 0.04600 0.03413 -0.0034 0.7807 0.9433
2.250 0.1263 0.04635 0.03443 -0.0035 0.7771 0.9459
2.500 0.1539 0.04678 0.03480 -0.0047 0.7740 0.9481
2.750 0.1827 0.04726 0.03523 -0.0061 0.7713 0.9506
3.000 0.1899 0.04761 0.03560 -0.0043 0.7659 0.9549
3.250 0.2106 0.04803 0.03600 -0.0045 0.7617 0.9584
3.500 0.2422 0.04859 0.03656 -0.0064 0.7585 0.9605
3.750 0.2608 0.04914 0.03714 -0.0066 0.7533 0.9639
4.000 0.2821 0.04969 0.03773 -0.0072 0.7482 0.9679
4.250 0.3122 0.05027 0.03837 -0.0089 0.7444 0.9716
4.500 0.3352 0.05096 0.03913 -0.0100 0.7389 0.9754
4.750 0.3592 0.05160 0.03984 -0.0111 0.7332 0.9799
5.000 0.3931 0.05223 0.04057 -0.0133 0.7292 0.9842
5.250 0.4097 0.05294 0.04138 -0.0136 0.7216 0.9900
5.500 0.4386 0.05356 0.04215 -0.0153 0.7164 0.9968
5.750 0.4438 0.05386 0.04252 -0.0128 0.7090 1.0000
6.000 0.4531 0.05401 0.04274 -0.0107 0.7024 1.0000
6.500 0.4788 0.05470 0.04360 -0.0081 0.6878 1.0000
6.750 0.4916 0.05525 0.04428 -0.0072 0.6792 1.0000
7.000 0.5182 0.05570 0.04488 -0.0079 0.6727 1.0000
7.250 0.5316 0.05632 0.04563 -0.0072 0.6627 1.0000
7.500 0.5666 0.05661 0.04614 -0.0087 0.6570 1.0000
7.750 0.5802 0.05718 0.04686 -0.0080 0.6454 1.0000
8.000 0.5984 0.05764 0.04751 -0.0077 0.6341 1.0000
8.250 0.6210 0.05785 0.04793 -0.0077 0.6227 1.0000
8.500 0.6459 0.05773 0.04806 -0.0076 0.6100 1.0000
8.750 0.6719 0.05700 0.04758 -0.0071 0.5937 1.0000
9.000 0.7099 0.05467 0.04554 -0.0065 0.5743 1.0000
9.250 0.7259 0.05368 0.04477 -0.0046 0.5490 1.0000
9.500 0.7435 0.05274 0.04412 -0.0028 0.5222 1.0000
9.750 0.7621 0.05175 0.04339 -0.0010 0.4917 1.0000
10.000 0.7782 0.05108 0.04296 0.0009 0.4494 1.0000
10.250 0.8278 0.04619 0.03738 0.0042 0.3043 1.0000
10.500 0.8266 0.04810 0.03851 0.0066 0.2198 1.0000
10.750 0.8252 0.05057 0.04053 0.0082 0.1761 1.0000
11.000 0.8282 0.05282 0.04252 0.0094 0.1483 1.0000
11.250 0.8363 0.05472 0.04430 0.0104 0.1295 1.0000
11.500 0.8480 0.05636 0.04590 0.0112 0.1146 1.0000
11.750 0.8627 0.05780 0.04735 0.0119 0.1019 1.0000
12.000 0.8856 0.05871 0.04822 0.0126 0.0924 1.0000
12.250 0.9116 0.05961 0.04938 0.0130 0.0822 1.0000
12.500 0.9594 0.05989 0.04993 0.0129 0.0731 1.0000
12.750 0.9943 0.06130 0.05140 0.0125 0.0656 1.0000
13.000 1.0235 0.06365 0.05426 0.0125 0.0606 1.0000
13.250 1.0421 0.06609 0.05687 0.0126 0.0564 1.0000
13.500 1.0505 0.06933 0.06042 0.0131 0.0532 1.0000
13.750 1.0492 0.07314 0.06475 0.0141 0.0512 1.0000
14.000 1.0442 0.07719 0.06919 0.0149 0.0498 1.0000
14.250 1.0356 0.08123 0.07354 0.0155 0.0484 1.0000
14.500 1.0260 0.08531 0.07787 0.0157 0.0470 1.0000
14.750 1.0176 0.08916 0.08189 0.0157 0.0455 1.0000
15.000 1.0125 0.09314 0.08598 0.0153 0.0441 1.0000
15.250 0.9969 0.09828 0.09129 0.0146 0.0435 1.0000
15.500 0.9761 0.10405 0.09731 0.0132 0.0435 1.0000
15.750 0.9544 0.11047 0.10394 0.0109 0.0435 1.0000
16.000 0.9338 0.11727 0.11091 0.0079 0.0436 1.0000
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