NREL's S809 Airfoil (s809-nr) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: NREL's S809 Airfoil (s809-nr) Reynolds number: 1,000,000 Max Cl/Cd: 100.59 at α=6.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s809-nr-1000000.txt Download as CSV file: xf-s809-nr-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.500 -0.7676 0.04840 0.04261 -0.0644 0.6364 0.0051
-13.250 -0.7384 0.04793 0.04204 -0.0631 0.6334 0.0048
-13.000 -0.7122 0.04800 0.04188 -0.0611 0.6302 0.0053
-12.750 -0.7018 0.04646 0.04030 -0.0617 0.6275 0.0049
-12.500 -0.6760 0.04702 0.04077 -0.0596 0.6257 0.0053
-12.250 -0.6585 0.04648 0.04017 -0.0589 0.6238 0.0052
-12.000 -0.6431 0.04583 0.03950 -0.0583 0.6221 0.0054
-11.750 -0.6291 0.04481 0.03846 -0.0582 0.6203 0.0056
-11.500 -0.6152 0.04420 0.03779 -0.0571 0.6186 0.0054
-11.250 -0.6007 0.04318 0.03676 -0.0571 0.6170 0.0058
-11.000 -0.5887 0.04223 0.03577 -0.0564 0.6154 0.0060
-10.750 -0.5748 0.04126 0.03476 -0.0561 0.6137 0.0061
-10.500 -0.5658 0.04011 0.03355 -0.0552 0.6119 0.0061
-10.250 -0.5549 0.03897 0.03239 -0.0547 0.6112 0.0063
-10.000 -0.5426 0.03790 0.03131 -0.0543 0.6103 0.0064
-9.750 -0.5386 0.03634 0.02971 -0.0532 0.6095 0.0064
-9.500 -0.5294 0.03507 0.02842 -0.0525 0.6085 0.0066
-9.250 -0.5185 0.03394 0.02726 -0.0520 0.6075 0.0067
-9.000 -0.5108 0.03264 0.02593 -0.0511 0.6065 0.0067
-8.750 -0.4959 0.03180 0.02507 -0.0508 0.6054 0.0070
-8.500 -0.4964 0.03003 0.02325 -0.0493 0.6045 0.0069
-8.250 -0.4934 0.02858 0.02177 -0.0480 0.6035 0.0074
-8.000 -0.4932 0.02698 0.02013 -0.0464 0.6027 0.0077
-7.750 -0.4851 0.02587 0.01899 -0.0454 0.6018 0.0077
-7.500 -0.4794 0.02462 0.01772 -0.0441 0.6010 0.0080
-7.250 -0.4743 0.02335 0.01641 -0.0427 0.6000 0.0085
-7.000 -0.4688 0.02212 0.01514 -0.0414 0.5991 0.0088
-6.750 -0.4633 0.02089 0.01387 -0.0399 0.5981 0.0093
-6.500 -0.4617 0.01943 0.01237 -0.0381 0.5971 0.0104
-6.250 -0.4631 0.01782 0.01073 -0.0360 0.5961 0.0139
-6.000 -0.4761 0.01576 0.00869 -0.0330 0.5957 0.0269
-5.750 -0.4775 0.01371 0.00679 -0.0322 0.5953 0.0806
-5.500 -0.5003 0.00889 0.00331 -0.0295 0.5948 0.4056
-5.250 -0.4735 0.00852 0.00316 -0.0300 0.5943 0.4647
-5.000 -0.4436 0.00858 0.00320 -0.0307 0.5937 0.4776
-4.750 -0.4134 0.00871 0.00330 -0.0314 0.5931 0.4858
-4.500 -0.3832 0.00891 0.00349 -0.0321 0.5925 0.4939
-4.250 -0.3522 0.00941 0.00395 -0.0327 0.5919 0.5019
-4.000 -0.3226 0.00940 0.00392 -0.0334 0.5914 0.5048
-3.750 -0.2930 0.00935 0.00384 -0.0340 0.5908 0.5059
-3.500 -0.2633 0.00932 0.00379 -0.0347 0.5902 0.5067
-3.250 -0.2336 0.00930 0.00375 -0.0354 0.5896 0.5076
-3.000 -0.2038 0.00929 0.00372 -0.0361 0.5891 0.5085
-2.750 -0.1740 0.00929 0.00370 -0.0367 0.5885 0.5094
-2.500 -0.1442 0.00929 0.00368 -0.0374 0.5880 0.5103
-2.250 -0.1144 0.00928 0.00365 -0.0381 0.5873 0.5112
-2.000 -0.0846 0.00928 0.00362 -0.0388 0.5866 0.5121
-1.750 -0.0548 0.00928 0.00360 -0.0395 0.5861 0.5130
-1.500 -0.0249 0.00928 0.00359 -0.0402 0.5856 0.5139
-1.250 0.0050 0.00929 0.00358 -0.0409 0.5851 0.5147
-1.000 0.0349 0.00931 0.00358 -0.0416 0.5846 0.5155
-0.750 0.0648 0.00934 0.00359 -0.0423 0.5841 0.5162
-0.500 0.0948 0.00937 0.00361 -0.0430 0.5836 0.5169
-0.250 0.1247 0.00942 0.00365 -0.0438 0.5830 0.5174
0.000 0.1545 0.00940 0.00363 -0.0445 0.5825 0.5185
0.250 0.1841 0.00939 0.00363 -0.0452 0.5820 0.5199
0.500 0.2139 0.00943 0.00370 -0.0459 0.5814 0.5209
0.750 0.2436 0.00952 0.00381 -0.0466 0.5807 0.5219
1.000 0.2733 0.00958 0.00390 -0.0472 0.5801 0.5227
1.250 0.3031 0.00959 0.00393 -0.0479 0.5797 0.5236
1.500 0.3329 0.00960 0.00398 -0.0486 0.5792 0.5244
1.750 0.3626 0.00960 0.00401 -0.0492 0.5785 0.5253
2.000 0.3923 0.00960 0.00405 -0.0498 0.5776 0.5262
2.250 0.4219 0.00961 0.00410 -0.0505 0.5767 0.5272
2.500 0.4516 0.00963 0.00415 -0.0511 0.5756 0.5282
2.750 0.4811 0.00961 0.00416 -0.0517 0.5738 0.5292
3.000 0.5107 0.00956 0.00413 -0.0522 0.5713 0.5302
3.250 0.5404 0.00951 0.00407 -0.0528 0.5686 0.5309
3.500 0.5700 0.00960 0.00414 -0.0534 0.5651 0.5316
3.750 0.5989 0.00951 0.00411 -0.0538 0.5625 0.5322
4.000 0.6279 0.00940 0.00404 -0.0542 0.5591 0.5327
4.250 0.6569 0.00921 0.00390 -0.0547 0.5552 0.5341
4.500 0.6858 0.00909 0.00379 -0.0550 0.5507 0.5355
4.750 0.7145 0.00903 0.00380 -0.0554 0.5471 0.5367
5.000 0.7433 0.00895 0.00380 -0.0558 0.5433 0.5378
5.250 0.7719 0.00882 0.00373 -0.0561 0.5375 0.5388
5.500 0.8003 0.00875 0.00370 -0.0564 0.5305 0.5398
5.750 0.8289 0.00867 0.00368 -0.0568 0.5216 0.5407
6.000 0.8575 0.00863 0.00370 -0.0571 0.5100 0.5417
6.250 0.8812 0.00876 0.00367 -0.0566 0.4576 0.5427
6.500 0.8901 0.00993 0.00434 -0.0538 0.3599 0.5436
6.750 0.9002 0.01099 0.00503 -0.0512 0.2829 0.5445
7.000 0.9127 0.01180 0.00559 -0.0491 0.2282 0.5453
7.250 0.9249 0.01255 0.00613 -0.0469 0.1841 0.5462
7.500 0.9356 0.01329 0.00667 -0.0444 0.1470 0.5469
7.750 0.9456 0.01395 0.00719 -0.0418 0.1181 0.5476
8.000 0.9519 0.01448 0.00764 -0.0384 0.0980 0.5484
8.250 0.9584 0.01508 0.00817 -0.0353 0.0814 0.5498
8.500 0.9668 0.01572 0.00878 -0.0326 0.0681 0.5510
8.750 0.9755 0.01641 0.00944 -0.0302 0.0576 0.5521
9.000 0.9844 0.01714 0.01016 -0.0280 0.0491 0.5532
9.250 0.9931 0.01795 0.01097 -0.0259 0.0420 0.5542
9.500 1.0004 0.01891 0.01193 -0.0239 0.0358 0.5552
9.750 1.0076 0.01999 0.01302 -0.0222 0.0311 0.5562
10.000 1.0172 0.02105 0.01412 -0.0210 0.0279 0.5572
10.250 1.0250 0.02231 0.01537 -0.0197 0.0247 0.5583
10.500 1.0346 0.02352 0.01663 -0.0188 0.0227 0.5593
10.750 1.0456 0.02469 0.01782 -0.0180 0.0208 0.5604
11.000 1.0522 0.02618 0.01933 -0.0169 0.0189 0.5614
11.250 1.0623 0.02746 0.02066 -0.0162 0.0178 0.5623
11.500 1.0758 0.02849 0.02171 -0.0158 0.0162 0.5631
11.750 1.0838 0.02992 0.02318 -0.0150 0.0153 0.5645
12.000 1.0907 0.03146 0.02477 -0.0141 0.0141 0.5662
12.250 1.1032 0.03259 0.02596 -0.0137 0.0135 0.5676
12.500 1.1128 0.03395 0.02739 -0.0131 0.0131 0.5690
12.750 1.1248 0.03513 0.02858 -0.0128 0.0120 0.5704
13.000 1.1319 0.03674 0.03024 -0.0122 0.0116 0.5716
13.250 1.1372 0.03852 0.03207 -0.0115 0.0108 0.5730
13.500 1.1481 0.03987 0.03349 -0.0112 0.0105 0.5743
13.750 1.1577 0.04136 0.03505 -0.0109 0.0102 0.5757
14.000 1.1677 0.04286 0.03659 -0.0107 0.0097 0.5769
14.250 1.1773 0.04442 0.03819 -0.0105 0.0094 0.5781
14.500 1.1865 0.04604 0.03985 -0.0103 0.0089 0.5795
14.750 1.1922 0.04803 0.04191 -0.0101 0.0087 0.5814
15.000 1.1930 0.05056 0.04453 -0.0099 0.0082 0.5831
15.250 1.2026 0.05228 0.04632 -0.0099 0.0080 0.5850
15.500 1.2116 0.05408 0.04820 -0.0100 0.0078 0.5869
15.750 1.2191 0.05607 0.05027 -0.0101 0.0076 0.5889
16.000 1.2266 0.05812 0.05239 -0.0103 0.0073 0.5908
16.250 1.2336 0.06024 0.05457 -0.0106 0.0071 0.5928
16.500 1.2407 0.06239 0.05677 -0.0109 0.0067 0.5947
16.750 1.2456 0.06484 0.05930 -0.0113 0.0065 0.5973
17.000 1.2471 0.06777 0.06232 -0.0119 0.0062 0.5998
17.250 1.2450 0.07123 0.06588 -0.0126 0.0059 0.6019
17.500 1.2500 0.07387 0.06861 -0.0133 0.0058 0.6046
17.750 1.2559 0.07644 0.07126 -0.0140 0.0056 0.6072
18.000 1.2592 0.07941 0.07432 -0.0149 0.0055 0.6096
18.250 1.2604 0.08272 0.07774 -0.0160 0.0053 0.6127
18.500 1.2616 0.08614 0.08127 -0.0172 0.0051 0.6161
18.750 1.2640 0.08942 0.08464 -0.0185 0.0050 0.6195
19.000 1.2625 0.09335 0.08867 -0.0201 0.0048 0.6228
19.250 1.2639 0.09689 0.09228 -0.0216 0.0046 0.6264
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