NREL's S807 Airfoil (s807-nr) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: NREL's S807 Airfoil (s807-nr) Reynolds number: 200,000 Max Cl/Cd: 56.44 at α=11.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s807-nr-200000.txt Download as CSV file: xf-s807-nr-200000.csv |
XFOIL Version 6.96
Calculated polar for: NREL's S807 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
------ -------- --------- --------- -------- -------- --------
-17.000 -0.8845 0.09579 0.09060 -0.0549 1.0000 0.0329
-16.750 -0.9042 0.09022 0.08484 -0.0571 1.0000 0.0329
-16.500 -0.9203 0.08522 0.07965 -0.0586 1.0000 0.0328
-16.250 -0.9373 0.08028 0.07454 -0.0599 1.0000 0.0331
-16.000 -0.9457 0.07624 0.07036 -0.0604 1.0000 0.0333
-15.750 -0.9475 0.07306 0.06709 -0.0604 1.0000 0.0337
-15.500 -0.9489 0.07017 0.06410 -0.0604 1.0000 0.0340
-15.250 -0.9512 0.06723 0.06102 -0.0603 1.0000 0.0342
-15.000 -0.9500 0.06478 0.05847 -0.0600 1.0000 0.0346
-14.750 -0.9473 0.06241 0.05599 -0.0596 1.0000 0.0349
-14.500 -0.9431 0.06023 0.05369 -0.0589 1.0000 0.0353
-14.250 -0.9375 0.05823 0.05157 -0.0582 1.0000 0.0358
-14.000 -0.9307 0.05637 0.04960 -0.0573 1.0000 0.0363
-13.750 -0.9240 0.05461 0.04772 -0.0565 1.0000 0.0370
-13.500 -0.9169 0.05294 0.04591 -0.0555 1.0000 0.0378
-13.250 -0.9114 0.05126 0.04407 -0.0546 1.0000 0.0385
-13.000 -0.8910 0.05044 0.04325 -0.0528 1.0000 0.0396
-12.750 -0.8741 0.04972 0.04260 -0.0513 1.0000 0.0407
-12.500 -0.8606 0.04882 0.04171 -0.0499 1.0000 0.0417
-12.250 -0.8467 0.04800 0.04087 -0.0484 1.0000 0.0427
-12.000 -0.8349 0.04708 0.03991 -0.0469 1.0000 0.0439
-11.750 -0.8248 0.04604 0.03879 -0.0455 1.0000 0.0453
-11.500 -0.8121 0.04540 0.03823 -0.0434 1.0000 0.0470
-11.250 -0.8047 0.04433 0.03722 -0.0418 1.0000 0.0486
-11.000 -0.7984 0.04318 0.03609 -0.0402 1.0000 0.0505
-10.750 -0.7927 0.04202 0.03491 -0.0386 1.0000 0.0524
-10.500 -0.7895 0.04076 0.03365 -0.0366 1.0000 0.0544
-10.250 -0.7921 0.03917 0.03213 -0.0345 1.0000 0.0564
-10.000 -0.7943 0.03761 0.03058 -0.0325 1.0000 0.0593
-9.750 -0.7967 0.03609 0.02904 -0.0303 1.0000 0.0622
-9.500 -0.8086 0.03412 0.02713 -0.0275 1.0000 0.0653
-9.250 -0.8207 0.03228 0.02534 -0.0245 1.0000 0.0694
-9.000 -0.8360 0.03056 0.02361 -0.0207 1.0000 0.0738
-8.750 -0.8600 0.02853 0.02162 -0.0162 1.0000 0.0768
-8.500 -0.8704 0.02583 0.01896 -0.0151 1.0000 0.0867
-8.250 -0.8710 0.02195 0.01530 -0.0179 1.0000 0.1188
-8.000 -0.8585 0.01714 0.01130 -0.0238 1.0000 0.2439
-7.750 -0.8317 0.01582 0.01078 -0.0263 1.0000 0.3795
-7.500 -0.8053 0.01607 0.01099 -0.0261 1.0000 0.4099
-7.250 -0.7793 0.01641 0.01125 -0.0257 1.0000 0.4280
-7.000 -0.7547 0.01697 0.01178 -0.0247 1.0000 0.4398
-6.750 -0.7294 0.01729 0.01198 -0.0243 1.0000 0.4501
-6.500 -0.7068 0.01814 0.01288 -0.0225 1.0000 0.4586
-6.250 -0.6843 0.01900 0.01375 -0.0209 1.0000 0.4677
-6.000 -0.6634 0.02009 0.01490 -0.0186 1.0000 0.4752
-5.750 -0.6403 0.02061 0.01539 -0.0175 0.9999 0.4826
-5.500 -0.5945 0.02334 0.01830 -0.0177 0.9921 0.4884
-5.250 -0.5483 0.02467 0.01960 -0.0200 0.9841 0.4990
-5.000 -0.5062 0.02617 0.02118 -0.0202 0.9764 0.5011
-4.750 -0.4589 0.02685 0.02185 -0.0226 0.9699 0.5037
-4.500 -0.4141 0.02463 0.01933 -0.0297 0.9610 0.5141
-4.000 -0.3309 0.02471 0.01943 -0.0331 0.9442 0.5169
-3.750 -0.2932 0.02452 0.01923 -0.0343 0.9333 0.5187
-3.500 -0.2543 0.02401 0.01869 -0.0361 0.9216 0.5211
-3.250 -0.2184 0.02300 0.01762 -0.0383 0.9063 0.5251
-3.000 -0.1808 0.02096 0.01534 -0.0428 0.8861 0.5315
-2.750 -0.1412 0.02043 0.01480 -0.0442 0.8634 0.5328
-2.500 -0.0728 0.01989 0.01415 -0.0511 0.8224 0.5342
-2.250 0.0195 0.01989 0.01361 -0.0629 0.7170 0.5360
-2.000 0.0452 0.02011 0.01337 -0.0624 0.6410 0.5382
-1.750 0.0678 0.02002 0.01293 -0.0619 0.5900 0.5409
-1.500 0.0929 0.01963 0.01219 -0.0625 0.5540 0.5442
-1.250 0.1213 0.01904 0.01126 -0.0642 0.5265 0.5482
-1.000 0.1459 0.01906 0.01115 -0.0635 0.5055 0.5497
-0.750 0.1715 0.01912 0.01111 -0.0631 0.4886 0.5513
-0.500 0.1980 0.01915 0.01104 -0.0629 0.4747 0.5529
-0.250 0.2252 0.01918 0.01093 -0.0629 0.4631 0.5547
0.000 0.2532 0.01909 0.01078 -0.0633 0.4521 0.5569
0.250 0.2822 0.01902 0.01058 -0.0639 0.4430 0.5594
0.500 0.3120 0.01886 0.01031 -0.0649 0.4340 0.5625
0.750 0.3430 0.01877 0.01005 -0.0661 0.4262 0.5657
1.000 0.3701 0.01874 0.01004 -0.0660 0.4187 0.5674
1.250 0.3983 0.01885 0.01007 -0.0661 0.4126 0.5691
1.500 0.4265 0.01890 0.01015 -0.0663 0.4067 0.5710
1.750 0.4550 0.01895 0.01019 -0.0665 0.4010 0.5732
2.000 0.4845 0.01905 0.01021 -0.0670 0.3961 0.5757
2.250 0.5145 0.01913 0.01026 -0.0677 0.3913 0.5784
2.500 0.5448 0.01914 0.01023 -0.0686 0.3861 0.5818
2.750 0.5734 0.01919 0.01027 -0.0689 0.3814 0.5842
3.000 0.6022 0.01944 0.01048 -0.0691 0.3775 0.5863
3.250 0.6302 0.01959 0.01071 -0.0692 0.3738 0.5885
3.500 0.6584 0.01972 0.01090 -0.0694 0.3699 0.5911
3.750 0.6875 0.01987 0.01107 -0.0697 0.3662 0.5939
4.000 0.7176 0.02006 0.01120 -0.0704 0.3628 0.5970
4.250 0.7492 0.02042 0.01146 -0.0715 0.3593 0.6001
4.500 0.7751 0.02051 0.01172 -0.0711 0.3558 0.6024
4.750 0.8022 0.02073 0.01206 -0.0710 0.3525 0.6051
5.000 0.8301 0.02098 0.01237 -0.0711 0.3494 0.6082
5.250 0.8591 0.02124 0.01264 -0.0715 0.3463 0.6116
5.500 0.8897 0.02164 0.01296 -0.0722 0.3432 0.6151
5.750 0.9174 0.02194 0.01338 -0.0724 0.3402 0.6181
6.000 0.9430 0.02219 0.01379 -0.0721 0.3369 0.6207
6.250 0.9694 0.02245 0.01417 -0.0719 0.3334 0.6237
6.500 0.9971 0.02271 0.01447 -0.0720 0.3301 0.6273
6.750 1.0267 0.02308 0.01480 -0.0725 0.3268 0.6316
7.000 1.0532 0.02347 0.01529 -0.0725 0.3232 0.6354
7.250 1.0769 0.02369 0.01571 -0.0718 0.3190 0.6385
7.500 1.1025 0.02390 0.01603 -0.0714 0.3150 0.6421
7.750 1.1307 0.02413 0.01624 -0.0716 0.3113 0.6463
8.000 1.1589 0.02461 0.01670 -0.0719 0.3075 0.6508
8.250 1.1805 0.02476 0.01712 -0.0709 0.3028 0.6542
8.500 1.2045 0.02486 0.01733 -0.0703 0.2980 0.6583
8.750 1.2327 0.02498 0.01739 -0.0704 0.2937 0.6635
9.000 1.2561 0.02531 0.01785 -0.0698 0.2889 0.6687
9.250 1.2768 0.02538 0.01813 -0.0686 0.2835 0.6728
9.500 1.3023 0.02533 0.01809 -0.0682 0.2785 0.6779
9.750 1.3258 0.02556 0.01838 -0.0676 0.2733 0.6836
10.000 1.3448 0.02557 0.01861 -0.0662 0.2672 0.6884
10.250 1.3680 0.02547 0.01851 -0.0653 0.2617 0.6942
10.500 1.3869 0.02565 0.01885 -0.0640 0.2556 0.7011
10.750 1.4047 0.02561 0.01897 -0.0623 0.2490 0.7070
11.000 1.4249 0.02565 0.01903 -0.0611 0.2431 0.7143
11.250 1.4387 0.02576 0.01938 -0.0589 0.2354 0.7213
11.500 1.4549 0.02578 0.01941 -0.0571 0.2285 0.7289
11.750 1.4653 0.02596 0.01987 -0.0544 0.2195 0.7374
12.000 1.4740 0.02616 0.02015 -0.0514 0.2110 0.7463
12.250 1.4817 0.02649 0.02061 -0.0485 0.2005 0.7566
12.500 1.4889 0.02706 0.02129 -0.0458 0.1878 0.7689
12.750 1.4925 0.02785 0.02218 -0.0428 0.1743 0.7813
13.000 1.4922 0.02901 0.02338 -0.0397 0.1608 0.7958
13.250 1.4880 0.03053 0.02495 -0.0365 0.1485 0.8138
13.500 1.4798 0.03235 0.02686 -0.0333 0.1383 0.8386
13.750 1.4622 0.03416 0.02883 -0.0288 0.1317 0.9036
14.000 1.4526 0.03674 0.03148 -0.0273 0.1235 1.0000
14.250 1.4382 0.04049 0.03519 -0.0269 0.1174 1.0000
14.500 1.4296 0.04417 0.03898 -0.0272 0.1106 1.0000
14.750 1.4134 0.04890 0.04371 -0.0283 0.1060 1.0000
15.000 1.4011 0.05360 0.04851 -0.0297 0.1011 1.0000
15.250 1.3876 0.05868 0.05367 -0.0316 0.0967 1.0000
15.500 1.3723 0.06395 0.05890 -0.0334 0.0930 1.0000
15.750 1.3613 0.06898 0.06408 -0.0354 0.0892 1.0000
16.000 1.3502 0.07412 0.06930 -0.0376 0.0856 1.0000
16.250 1.3408 0.07885 0.07398 -0.0394 0.0822 1.0000
16.500 1.3334 0.08354 0.07874 -0.0413 0.0789 1.0000
16.750 1.3255 0.08854 0.08384 -0.0436 0.0757 1.0000
17.000 1.3201 0.09309 0.08839 -0.0457 0.0728 1.0000
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