NREL's S806A Airfoil (modified line 35) (s806a-nr) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: NREL's S806A Airfoil (modified line 35) (s806a-nr) Reynolds number: 200,000 Max Cl/Cd: 76.09 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s806a-nr-200000.txt Download as CSV file: xf-s806a-nr-200000.csv |
XFOIL Version 6.96
Calculated polar for: NREL's S806A 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
------ -------- --------- --------- -------- -------- --------
-7.250 -0.2613 0.09042 0.08679 -0.0549 0.8879 0.0285
-7.000 -0.2553 0.08680 0.08320 -0.0607 0.8840 0.0291
-6.750 -0.2514 0.08302 0.07940 -0.0676 0.8796 0.0294
-6.500 -0.2458 0.07974 0.07603 -0.0726 0.8755 0.0296
-6.250 -0.2384 0.07724 0.07337 -0.0763 0.8715 0.0299
-3.250 -0.0712 0.02743 0.02142 -0.0742 0.8351 0.1871
-2.750 0.0074 0.02037 0.01213 -0.0700 0.8302 0.0362
-2.500 0.0345 0.01942 0.01114 -0.0697 0.8276 0.0344
-2.250 0.0613 0.01869 0.01038 -0.0695 0.8249 0.0333
-2.000 0.0881 0.01817 0.00983 -0.0695 0.8222 0.0337
-1.750 0.1156 0.01781 0.00938 -0.0696 0.8196 0.0354
-1.500 0.1432 0.01746 0.00899 -0.0695 0.8170 0.0460
-1.250 0.1375 0.01496 0.00958 -0.0616 0.8141 0.8617
-1.000 0.2384 0.01546 0.01009 -0.0712 0.8156 0.9896
-0.750 0.2820 0.01554 0.01007 -0.0750 0.8136 0.9967
-0.500 0.3152 0.01564 0.01009 -0.0767 0.8112 1.0000
-0.250 0.3363 0.01578 0.01018 -0.0759 0.8076 1.0000
0.000 0.3555 0.01630 0.01064 -0.0748 0.8026 1.0000
0.250 0.3760 0.01694 0.01127 -0.0745 0.7990 1.0000
0.500 0.3982 0.01703 0.01124 -0.0743 0.7972 1.0000
0.750 0.4205 0.01720 0.01146 -0.0742 0.7948 1.0000
1.000 0.4419 0.01736 0.01161 -0.0738 0.7914 1.0000
1.250 0.4624 0.01750 0.01174 -0.0731 0.7867 1.0000
1.500 0.4819 0.01773 0.01196 -0.0723 0.7822 1.0000
1.750 0.5012 0.01794 0.01217 -0.0713 0.7777 1.0000
2.000 0.5213 0.01801 0.01224 -0.0701 0.7728 1.0000
2.250 0.5423 0.01803 0.01226 -0.0688 0.7681 1.0000
2.500 0.5655 0.01799 0.01220 -0.0678 0.7637 1.0000
2.750 0.5902 0.01781 0.01202 -0.0667 0.7592 1.0000
3.000 0.6150 0.01789 0.01209 -0.0657 0.7543 1.0000
3.250 0.6380 0.01845 0.01267 -0.0651 0.7479 1.0000
3.500 0.6655 0.01807 0.01234 -0.0652 0.7412 1.0000
3.750 0.6929 0.01769 0.01201 -0.0649 0.7324 1.0000
4.000 0.7206 0.01723 0.01158 -0.0643 0.7242 1.0000
4.250 0.7504 0.01658 0.01107 -0.0638 0.7172 1.0000
4.500 0.7798 0.01580 0.01029 -0.0629 0.7102 1.0000
4.750 0.8077 0.01541 0.00988 -0.0619 0.7016 1.0000
5.000 0.8346 0.01510 0.00969 -0.0616 0.6930 1.0000
5.250 0.8623 0.01453 0.00921 -0.0611 0.6793 1.0000
5.500 0.8921 0.01280 0.00731 -0.0590 0.6519 1.0000
5.750 0.9169 0.01205 0.00642 -0.0574 0.5923 1.0000
6.000 0.9314 0.01264 0.00607 -0.0546 0.4357 1.0000
6.250 0.9352 0.01473 0.00716 -0.0517 0.2781 1.0000
6.500 0.9477 0.01603 0.00804 -0.0499 0.2063 1.0000
6.750 0.9611 0.01717 0.00888 -0.0483 0.1521 1.0000
7.000 0.9741 0.01827 0.00972 -0.0465 0.1130 1.0000
7.250 0.9867 0.01934 0.01057 -0.0447 0.0846 1.0000
7.500 0.9996 0.02033 0.01142 -0.0429 0.0627 1.0000
7.750 1.0084 0.02153 0.01245 -0.0404 0.0417 1.0000
8.000 1.0660 0.02194 0.01335 -0.0482 0.0561 1.0000
8.250 1.0758 0.02321 0.01454 -0.0461 0.0448 1.0000
8.500 1.0807 0.02475 0.01604 -0.0434 0.0385 1.0000
8.750 1.0911 0.02604 0.01740 -0.0415 0.0344 1.0000
9.000 1.1004 0.02756 0.01895 -0.0397 0.0319 1.0000
9.250 1.1065 0.02962 0.02105 -0.0373 0.0303 1.0000
9.500 1.1211 0.03131 0.02282 -0.0356 0.0296 1.0000
9.750 1.1406 0.03278 0.02441 -0.0345 0.0293 1.0000
10.000 1.1642 0.03445 0.02622 -0.0339 0.0291 1.0000
10.250 1.1923 0.03652 0.02848 -0.0337 0.0291 1.0000
10.500 1.2231 0.03944 0.03172 -0.0342 0.0293 1.0000
10.750 1.2504 0.04355 0.03615 -0.0348 0.0297 1.0000
11.000 1.2678 0.04639 0.03926 -0.0341 0.0301 1.0000
11.250 1.2771 0.04771 0.04078 -0.0320 0.0306 1.0000
11.500 1.2794 0.04937 0.04274 -0.0291 0.0312 1.0000
11.750 1.2617 0.05448 0.04863 -0.0243 0.0336 1.0000
12.000 1.2379 0.06016 0.05483 -0.0204 0.0356 1.0000
12.250 1.2199 0.06482 0.05979 -0.0179 0.0368 1.0000
12.500 1.2022 0.06948 0.06468 -0.0162 0.0377 1.0000
12.750 1.1849 0.07447 0.06986 -0.0149 0.0386 1.0000
13.000 0.9504 0.12009 0.11675 -0.0331 0.0694 1.0000
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Polar data table (+)
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