NREL's S809 Airfoil (s809-nr) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: NREL's S809 Airfoil (s809-nr) Reynolds number: 200,000 Max Cl/Cd: 53.87 at α=7.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s809-nr-200000-n5.txt Download as CSV file: xf-s809-nr-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NREL's S809 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.250 -0.6557 0.11087 0.10674 -0.0467 1.0000 0.0085
-16.000 -0.6733 0.10435 0.10007 -0.0493 1.0000 0.0081
-15.750 -0.6944 0.09770 0.09323 -0.0515 1.0000 0.0084
-15.500 -0.7112 0.09201 0.08736 -0.0532 1.0000 0.0083
-15.250 -0.7272 0.08659 0.08175 -0.0543 1.0000 0.0081
-15.000 -0.7389 0.08206 0.07704 -0.0551 1.0000 0.0081
-14.750 -0.7509 0.07754 0.07231 -0.0556 1.0000 0.0082
-14.500 -0.7582 0.07358 0.06816 -0.0557 1.0000 0.0081
-14.250 -0.7624 0.07006 0.06444 -0.0557 1.0000 0.0080
-14.000 -0.7644 0.06657 0.06073 -0.0553 1.0000 0.0080
-13.750 -0.7641 0.06391 0.05789 -0.0551 1.0000 0.0085
-13.500 -0.7258 0.05935 0.05273 -0.0631 0.8505 0.0090
-13.250 -0.7064 0.05715 0.04983 -0.0633 0.7647 0.0092
-13.000 -0.6913 0.05550 0.04775 -0.0627 0.7393 0.0095
-12.500 -0.6434 0.05376 0.04556 -0.0615 0.7118 0.0096
-12.250 -0.6185 0.05338 0.04504 -0.0607 0.7030 0.0097
-12.000 -0.5953 0.05308 0.04466 -0.0599 0.6955 0.0100
-11.750 -0.5740 0.05275 0.04422 -0.0592 0.6896 0.0100
-11.500 -0.5541 0.05233 0.04375 -0.0585 0.6843 0.0103
-11.250 -0.5354 0.05189 0.04324 -0.0577 0.6798 0.0104
-11.000 -0.5191 0.05128 0.04256 -0.0570 0.6762 0.0110
-10.750 -0.5040 0.05050 0.04172 -0.0564 0.6730 0.0110
-10.500 -0.4908 0.04954 0.04072 -0.0558 0.6699 0.0115
-10.250 -0.4795 0.04844 0.03956 -0.0552 0.6671 0.0119
-10.000 -0.4685 0.04725 0.03830 -0.0547 0.6645 0.0121
-9.750 -0.4621 0.04572 0.03673 -0.0540 0.6623 0.0132
-9.500 -0.4538 0.04432 0.03526 -0.0535 0.6603 0.0137
-9.250 -0.4453 0.04294 0.03381 -0.0530 0.6584 0.0141
-9.000 -0.4351 0.04167 0.03249 -0.0525 0.6564 0.0152
-8.750 -0.4280 0.04021 0.03097 -0.0519 0.6545 0.0167
-8.500 -0.4194 0.03891 0.02964 -0.0513 0.6527 0.0196
-8.250 -0.4132 0.03746 0.02816 -0.0505 0.6509 0.0227
-8.000 -0.4079 0.03601 0.02668 -0.0496 0.6494 0.0286
-7.750 -0.4041 0.03454 0.02521 -0.0486 0.6479 0.0386
-7.500 -0.4119 0.03246 0.02331 -0.0468 0.6466 0.0738
-7.250 -0.4374 0.02934 0.02053 -0.0439 0.6454 0.1459
-7.000 -0.4654 0.02607 0.01750 -0.0406 0.6442 0.2061
-6.750 -0.4886 0.02308 0.01464 -0.0376 0.6430 0.2426
-6.500 -0.5169 0.02025 0.01189 -0.0337 0.6416 0.2713
-6.250 -0.5447 0.01725 0.00926 -0.0303 0.6400 0.3567
-5.750 -0.4896 0.01980 0.01233 -0.0295 0.6368 0.4947
-5.500 -0.4366 0.02352 0.01612 -0.0299 0.6355 0.5073
-5.250 -0.4106 0.02345 0.01594 -0.0300 0.6343 0.5090
-5.000 -0.3903 0.02278 0.01514 -0.0300 0.6332 0.5114
-4.750 -0.3757 0.02150 0.01365 -0.0301 0.6321 0.5154
-4.500 -0.3560 0.02059 0.01252 -0.0304 0.6311 0.5181
-4.250 -0.3285 0.02044 0.01229 -0.0307 0.6302 0.5188
-4.000 -0.3011 0.02030 0.01208 -0.0311 0.6293 0.5195
-3.750 -0.2736 0.02020 0.01190 -0.0315 0.6285 0.5204
-3.500 -0.2460 0.02011 0.01174 -0.0319 0.6277 0.5214
-3.250 -0.2187 0.01999 0.01159 -0.0323 0.6268 0.5225
-3.000 -0.1917 0.01983 0.01138 -0.0328 0.6260 0.5237
-2.750 -0.1649 0.01963 0.01114 -0.0332 0.6251 0.5250
-2.500 -0.1381 0.01941 0.01087 -0.0337 0.6242 0.5265
-2.250 -0.1114 0.01917 0.01056 -0.0343 0.6233 0.5281
-2.000 -0.0847 0.01890 0.01022 -0.0349 0.6222 0.5299
-1.750 -0.0579 0.01861 0.00984 -0.0356 0.6211 0.5317
-1.500 -0.0304 0.01844 0.00961 -0.0362 0.6200 0.5331
-1.250 -0.0022 0.01843 0.00962 -0.0366 0.6192 0.5339
-1.000 0.0259 0.01843 0.00964 -0.0371 0.6183 0.5348
-0.750 0.0541 0.01843 0.00965 -0.0376 0.6176 0.5358
-0.500 0.0822 0.01843 0.00966 -0.0380 0.6168 0.5367
-0.250 0.1104 0.01841 0.00965 -0.0386 0.6161 0.5377
0.000 0.1385 0.01840 0.00965 -0.0391 0.6154 0.5388
0.250 0.1667 0.01839 0.00964 -0.0397 0.6147 0.5400
0.500 0.1950 0.01837 0.00962 -0.0402 0.6138 0.5412
0.750 0.2235 0.01835 0.00960 -0.0409 0.6129 0.5426
1.000 0.2520 0.01836 0.00960 -0.0415 0.6122 0.5442
1.250 0.2800 0.01837 0.00962 -0.0422 0.6115 0.5459
1.500 0.3076 0.01838 0.00965 -0.0428 0.6105 0.5476
1.750 0.3348 0.01842 0.00977 -0.0432 0.6091 0.5486
2.000 0.3619 0.01849 0.00994 -0.0435 0.6076 0.5494
2.250 0.3892 0.01857 0.01012 -0.0438 0.6059 0.5503
2.500 0.4165 0.01865 0.01029 -0.0441 0.6044 0.5512
2.750 0.4441 0.01874 0.01046 -0.0445 0.6029 0.5522
3.000 0.4719 0.01883 0.01063 -0.0449 0.6015 0.5533
3.250 0.4999 0.01892 0.01079 -0.0453 0.6000 0.5546
3.500 0.5282 0.01900 0.01093 -0.0458 0.5987 0.5560
3.750 0.5570 0.01907 0.01106 -0.0464 0.5973 0.5575
4.000 0.5849 0.01916 0.01122 -0.0468 0.5954 0.5590
4.250 0.6093 0.01928 0.01148 -0.0467 0.5918 0.5604
4.500 0.6358 0.01932 0.01161 -0.0469 0.5881 0.5618
4.750 0.6647 0.01922 0.01155 -0.0474 0.5845 0.5631
5.000 0.6960 0.01899 0.01133 -0.0480 0.5808 0.5641
5.250 0.7184 0.01897 0.01153 -0.0474 0.5738 0.5651
5.500 0.7473 0.01862 0.01125 -0.0475 0.5672 0.5662
5.750 0.7723 0.01843 0.01119 -0.0471 0.5592 0.5674
6.000 0.7999 0.01805 0.01089 -0.0469 0.5507 0.5688
6.250 0.8226 0.01793 0.01097 -0.0462 0.5410 0.5702
6.500 0.8479 0.01770 0.01086 -0.0458 0.5312 0.5717
6.750 0.8706 0.01756 0.01089 -0.0451 0.5165 0.5732
7.000 0.8920 0.01742 0.01092 -0.0442 0.4903 0.5746
7.250 0.9094 0.01688 0.00997 -0.0419 0.4208 0.5760
7.500 0.9075 0.01767 0.01031 -0.0372 0.3526 0.5772
7.750 0.9012 0.01872 0.01106 -0.0323 0.3010 0.5784
8.000 0.8917 0.01975 0.01191 -0.0269 0.2621 0.5794
8.250 0.8850 0.02105 0.01307 -0.0227 0.2269 0.5803
8.500 0.8790 0.02253 0.01443 -0.0192 0.1954 0.5813
8.750 0.8747 0.02416 0.01598 -0.0164 0.1677 0.5824
9.000 0.8727 0.02589 0.01763 -0.0144 0.1437 0.5836
9.250 0.8727 0.02767 0.01934 -0.0128 0.1221 0.5850
9.500 0.8753 0.02938 0.02098 -0.0116 0.1038 0.5865
9.750 0.8795 0.03102 0.02258 -0.0105 0.0879 0.5880
10.000 0.8849 0.03262 0.02415 -0.0096 0.0753 0.5895
10.250 0.8910 0.03420 0.02571 -0.0088 0.0649 0.5910
10.500 0.8972 0.03580 0.02728 -0.0081 0.0567 0.5924
10.750 0.9059 0.03726 0.02877 -0.0075 0.0500 0.5938
11.000 0.9127 0.03885 0.03040 -0.0068 0.0447 0.5951
11.250 0.9210 0.04035 0.03197 -0.0063 0.0402 0.5963
11.500 0.9267 0.04209 0.03374 -0.0057 0.0371 0.5975
11.750 0.9356 0.04361 0.03538 -0.0052 0.0342 0.5990
12.000 0.9431 0.04530 0.03713 -0.0048 0.0315 0.6005
12.250 0.9484 0.04721 0.03907 -0.0044 0.0294 0.6020
12.500 0.9571 0.04889 0.04088 -0.0041 0.0277 0.6038
12.750 0.9651 0.05067 0.04276 -0.0040 0.0260 0.6056
13.000 0.9716 0.05264 0.04480 -0.0038 0.0247 0.6075
13.250 0.9752 0.05495 0.04712 -0.0037 0.0235 0.6094
13.500 0.9832 0.05684 0.04916 -0.0036 0.0225 0.6111
13.750 0.9910 0.05879 0.05125 -0.0036 0.0213 0.6129
14.000 0.9980 0.06086 0.05344 -0.0037 0.0202 0.6148
14.250 1.0040 0.06312 0.05579 -0.0038 0.0195 0.6167
14.500 1.0084 0.06560 0.05832 -0.0041 0.0187 0.6187
14.750 1.0138 0.06800 0.06083 -0.0043 0.0181 0.6207
15.000 1.0204 0.07035 0.06335 -0.0046 0.0175 0.6229
15.250 1.0262 0.07287 0.06600 -0.0050 0.0167 0.6251
15.500 1.0313 0.07547 0.06876 -0.0055 0.0161 0.6269
15.750 1.0353 0.07828 0.07169 -0.0062 0.0155 0.6290
16.000 1.0386 0.08123 0.07476 -0.0070 0.0151 0.6312
16.250 1.0404 0.08442 0.07803 -0.0081 0.0145 0.6336
16.500 1.0417 0.08780 0.08154 -0.0091 0.0141 0.6360
16.750 1.0430 0.09130 0.08525 -0.0102 0.0137 0.6386
17.000 1.0427 0.09511 0.08925 -0.0115 0.0133 0.6410
17.250 1.0412 0.09919 0.09353 -0.0132 0.0128 0.6433
17.500 1.0389 0.10345 0.09798 -0.0150 0.0125 0.6459
17.750 1.0358 0.10798 0.10268 -0.0173 0.0121 0.6487
18.000 1.0324 0.11265 0.10749 -0.0197 0.0118 0.6518
18.250 1.0284 0.11749 0.11249 -0.0223 0.0116 0.6548
18.500 1.0246 0.12241 0.11752 -0.0251 0.0113 0.6577
18.750 1.0196 0.12758 0.12283 -0.0281 0.0111 0.6605
19.000 1.0120 0.13341 0.12881 -0.0316 0.0108 0.6634
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