NREL's S822 Airfoil (s822-nr) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: NREL's S822 Airfoil (s822-nr) Reynolds number: 200,000 Max Cl/Cd: 68.56 at α=7° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s822-nr-200000.txt Download as CSV file: xf-s822-nr-200000.csv |
XFOIL Version 6.96
Calculated polar for: NREL's S822 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
------ -------- --------- --------- -------- -------- --------
-16.250 -0.5610 0.12087 0.11706 -0.0620 1.0000 0.0271
-16.000 -0.6131 0.10534 0.10143 -0.0699 1.0000 0.0259
-15.750 -0.6562 0.09300 0.08892 -0.0770 1.0000 0.0249
-15.500 -0.6937 0.08291 0.07862 -0.0828 1.0000 0.0244
-15.250 -0.7275 0.07441 0.06987 -0.0873 1.0000 0.0237
-15.000 -0.7462 0.06903 0.06434 -0.0897 1.0000 0.0239
-14.750 -0.7673 0.06367 0.05879 -0.0914 1.0000 0.0238
-14.500 -0.7794 0.06005 0.05504 -0.0922 1.0000 0.0242
-14.250 -0.7932 0.05646 0.05128 -0.0924 1.0000 0.0245
-14.000 -0.8076 0.05318 0.04785 -0.0919 1.0000 0.0251
-13.750 -0.8209 0.05044 0.04497 -0.0907 1.0000 0.0254
-13.500 -0.8360 0.04829 0.04270 -0.0882 1.0000 0.0258
-13.250 -0.8563 0.04690 0.04124 -0.0838 1.0000 0.0258
-13.000 -0.8812 0.04586 0.04012 -0.0786 1.0000 0.0261
-12.750 -0.9005 0.04463 0.03878 -0.0741 1.0000 0.0263
-12.500 -0.9158 0.04338 0.03743 -0.0701 1.0000 0.0264
-12.250 -0.9053 0.04113 0.03487 -0.0716 0.9964 0.0274
-12.000 -0.8915 0.03815 0.03187 -0.0726 0.9939 0.0297
-11.750 -0.8778 0.03668 0.03031 -0.0736 0.9895 0.0321
-11.500 -0.8621 0.03527 0.02869 -0.0745 0.9854 0.0347
-11.250 -0.8431 0.03307 0.02641 -0.0756 0.9829 0.0378
-11.000 -0.8314 0.03201 0.02532 -0.0752 0.9777 0.0408
-10.750 -0.8142 0.03099 0.02409 -0.0754 0.9732 0.0444
-10.500 -0.7937 0.02923 0.02233 -0.0763 0.9704 0.0490
-10.250 -0.7836 0.02847 0.02149 -0.0748 0.9648 0.0532
-10.000 -0.7702 0.02732 0.02027 -0.0739 0.9600 0.0583
-9.750 -0.7486 0.02643 0.01934 -0.0744 0.9568 0.0650
-9.500 -0.7431 0.02567 0.01853 -0.0715 0.9509 0.0705
-9.250 -0.7281 0.02497 0.01779 -0.0704 0.9460 0.0782
-9.000 -0.7048 0.02397 0.01681 -0.0709 0.9430 0.0892
-8.750 -0.6768 0.02305 0.01587 -0.0722 0.9410 0.1032
-8.500 -0.6825 0.02274 0.01555 -0.0666 0.9325 0.1106
-8.250 -0.6585 0.02198 0.01485 -0.0669 0.9294 0.1268
-8.000 -0.6289 0.02130 0.01417 -0.0682 0.9275 0.1471
-7.750 -0.6304 0.02108 0.01400 -0.0633 0.9200 0.1586
-7.500 -0.6078 0.02057 0.01351 -0.0631 0.9162 0.1797
-7.250 -0.5786 0.02000 0.01300 -0.0642 0.9139 0.2050
-7.000 -0.5462 0.01944 0.01253 -0.0658 0.9124 0.2329
-6.750 -0.5530 0.01946 0.01258 -0.0597 0.9037 0.2459
-6.500 -0.5257 0.01903 0.01222 -0.0602 0.9006 0.2737
-6.250 -0.4930 0.01858 0.01184 -0.0617 0.8988 0.3052
-6.000 -0.4574 0.01815 0.01147 -0.0638 0.8975 0.3382
-5.750 -0.4670 0.01832 0.01168 -0.0570 0.8880 0.3534
-5.500 -0.4371 0.01799 0.01143 -0.0578 0.8855 0.3850
-5.250 -0.4023 0.01765 0.01116 -0.0595 0.8838 0.4186
-5.000 -0.3658 0.01730 0.01091 -0.0615 0.8826 0.4528
-4.750 -0.3741 0.01756 0.01123 -0.0549 0.8728 0.4705
-4.500 -0.3431 0.01736 0.01112 -0.0557 0.8705 0.5031
-4.250 -0.3077 0.01717 0.01100 -0.0573 0.8690 0.5359
-4.000 -0.2709 0.01703 0.01090 -0.0590 0.8678 0.5671
-3.750 -0.2768 0.01743 0.01137 -0.0529 0.8578 0.5850
-3.500 -0.2441 0.01741 0.01137 -0.0538 0.8557 0.6112
-3.250 -0.2084 0.01740 0.01138 -0.0552 0.8543 0.6338
-3.000 -0.1721 0.01738 0.01135 -0.0567 0.8531 0.6552
-2.750 -0.1780 0.01792 0.01192 -0.0506 0.8430 0.6694
-2.500 -0.1445 0.01795 0.01193 -0.0516 0.8409 0.6876
-2.250 -0.1091 0.01799 0.01197 -0.0529 0.8395 0.7037
-2.000 -0.0733 0.01802 0.01199 -0.0541 0.8383 0.7185
-1.750 -0.0812 0.01870 0.01273 -0.0477 0.8279 0.7294
-1.500 -0.0478 0.01878 0.01281 -0.0485 0.8259 0.7417
-1.250 -0.0126 0.01885 0.01288 -0.0497 0.8246 0.7534
-1.000 -0.0141 0.01948 0.01352 -0.0446 0.8161 0.7651
-0.750 0.0117 0.01967 0.01371 -0.0441 0.8126 0.7757
-0.500 0.0447 0.01975 0.01381 -0.0447 0.8108 0.7849
-0.250 0.0813 0.01975 0.01380 -0.0461 0.8095 0.7952
0.000 0.1179 0.01975 0.01380 -0.0473 0.8085 0.8035
0.250 0.1030 0.02056 0.01465 -0.0400 0.7969 0.8137
0.500 0.1400 0.02046 0.01453 -0.0415 0.7955 0.8236
0.750 0.1771 0.02038 0.01448 -0.0426 0.7944 0.8301
1.000 0.2161 0.02019 0.01428 -0.0444 0.7934 0.8390
1.250 0.1995 0.02099 0.01513 -0.0366 0.7814 0.8491
1.500 0.2381 0.02075 0.01491 -0.0381 0.7802 0.8564
1.750 0.2783 0.02047 0.01465 -0.0399 0.7792 0.8634
2.000 0.3173 0.02014 0.01434 -0.0414 0.7780 0.8705
2.250 0.3055 0.02071 0.01495 -0.0346 0.7661 0.8829
2.500 0.3046 0.02115 0.01544 -0.0294 0.7571 0.8930
2.750 0.3365 0.02079 0.01511 -0.0296 0.7538 0.9008
3.000 0.3792 0.02023 0.01459 -0.0315 0.7524 0.9070
3.250 0.4257 0.01957 0.01396 -0.0343 0.7511 0.9132
3.500 0.4736 0.01888 0.01331 -0.0371 0.7498 0.9173
3.750 0.4732 0.01913 0.01363 -0.0320 0.7393 0.9299
4.000 0.5248 0.01836 0.01290 -0.0356 0.7373 0.9338
4.250 0.5795 0.01753 0.01211 -0.0398 0.7353 0.9373
4.500 0.5979 0.01749 0.01215 -0.0381 0.7257 0.9464
4.750 0.6553 0.01662 0.01133 -0.0429 0.7218 0.9483
5.000 0.6832 0.01632 0.01112 -0.0427 0.7125 0.9563
5.250 0.7410 0.01549 0.01031 -0.0477 0.7059 0.9573
5.500 0.7793 0.01514 0.01005 -0.0496 0.6933 0.9617
5.750 0.8136 0.01477 0.00974 -0.0507 0.6796 0.9680
6.000 0.8570 0.01440 0.00942 -0.0535 0.6631 0.9711
6.250 0.8948 0.01425 0.00933 -0.0556 0.6423 0.9756
6.500 0.9278 0.01412 0.00920 -0.0566 0.6171 0.9820
6.750 0.9612 0.01418 0.00926 -0.0580 0.5799 0.9877
7.000 0.9872 0.01440 0.00930 -0.0581 0.5235 0.9954
7.250 0.9805 0.01471 0.00933 -0.0522 0.4746 1.0000
7.500 0.9494 0.01476 0.00926 -0.0417 0.4554 1.0000
7.750 0.9303 0.01512 0.00942 -0.0337 0.4245 1.0000
8.000 0.9257 0.01595 0.00999 -0.0289 0.3812 1.0000
8.250 0.9254 0.01696 0.01075 -0.0252 0.3385 1.0000
8.500 0.9272 0.01805 0.01164 -0.0220 0.2989 1.0000
8.750 0.9296 0.01923 0.01260 -0.0190 0.2621 1.0000
9.000 0.9340 0.02041 0.01359 -0.0165 0.2275 1.0000
9.250 0.9393 0.02163 0.01464 -0.0141 0.1970 1.0000
9.500 0.9453 0.02289 0.01573 -0.0120 0.1707 1.0000
9.750 0.9522 0.02415 0.01685 -0.0100 0.1481 1.0000
10.000 0.9594 0.02544 0.01802 -0.0082 0.1302 1.0000
10.250 0.9684 0.02667 0.01919 -0.0065 0.1148 1.0000
10.500 0.9767 0.02799 0.02045 -0.0049 0.1022 1.0000
10.750 0.9853 0.02932 0.02173 -0.0034 0.0913 1.0000
11.000 0.9964 0.03052 0.02297 -0.0021 0.0818 1.0000
11.250 1.0047 0.03198 0.02441 -0.0006 0.0743 1.0000
11.500 1.0147 0.03331 0.02575 0.0007 0.0678 1.0000
11.750 1.0243 0.03483 0.02729 0.0020 0.0623 1.0000
12.000 1.0352 0.03615 0.02866 0.0030 0.0571 1.0000
12.250 1.0456 0.03785 0.03028 0.0042 0.0527 1.0000
12.500 1.0581 0.03916 0.03178 0.0052 0.0495 1.0000
12.750 1.0692 0.04059 0.03325 0.0061 0.0463 1.0000
13.000 1.0850 0.04241 0.03498 0.0068 0.0425 1.0000
13.250 1.0954 0.04387 0.03664 0.0078 0.0408 1.0000
13.500 1.1059 0.04551 0.03842 0.0086 0.0386 1.0000
13.750 1.1154 0.04718 0.04018 0.0094 0.0367 1.0000
14.000 1.1241 0.04897 0.04197 0.0100 0.0348 1.0000
14.250 1.1367 0.05147 0.04461 0.0107 0.0327 1.0000
14.500 1.1406 0.05366 0.04704 0.0115 0.0317 1.0000
14.750 1.1439 0.05606 0.04963 0.0122 0.0304 1.0000
15.000 1.1455 0.05852 0.05225 0.0127 0.0291 1.0000
15.250 1.1468 0.06099 0.05481 0.0130 0.0279 1.0000
15.500 1.1500 0.06340 0.05725 0.0132 0.0268 1.0000
15.750 1.1474 0.06796 0.06199 0.0135 0.0256 1.0000
16.000 1.1386 0.07169 0.06597 0.0134 0.0253 1.0000
16.250 1.1272 0.07599 0.07053 0.0129 0.0249 1.0000
16.500 1.1141 0.08088 0.07568 0.0120 0.0246 1.0000
16.750 1.0985 0.08629 0.08134 0.0105 0.0243 1.0000
17.000 1.0807 0.09237 0.08767 0.0083 0.0241 1.0000
17.250 1.0601 0.09927 0.09481 0.0053 0.0239 1.0000
17.500 1.0384 0.10679 0.10257 0.0015 0.0240 1.0000
17.750 1.0134 0.11545 0.11145 -0.0033 0.0241 1.0000
18.000 0.9853 0.12539 0.12160 -0.0093 0.0245 1.0000
18.250 0.9535 0.13694 0.13333 -0.0166 0.0250 1.0000
18.500 0.9173 0.15056 0.14710 -0.0252 0.0255 1.0000
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