NREL's S807 Airfoil (s807-nr) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: NREL's S807 Airfoil (s807-nr) Reynolds number: 100,000 Max Cl/Cd: 40.34 at α=10.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s807-nr-100000-n5.txt Download as CSV file: xf-s807-nr-100000-n5.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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-17.500 -0.7169 0.13211 0.12602 -0.0327 1.0000 0.0313
-17.250 -0.7597 0.11919 0.11283 -0.0397 1.0000 0.0310
-17.000 -0.7860 0.11061 0.10402 -0.0439 1.0000 0.0310
-16.750 -0.8052 0.10381 0.09700 -0.0470 1.0000 0.0311
-16.500 -0.8196 0.09809 0.09107 -0.0492 1.0000 0.0312
-16.250 -0.8301 0.09320 0.08598 -0.0509 1.0000 0.0314
-16.000 -0.8376 0.08889 0.08147 -0.0521 1.0000 0.0317
-15.750 -0.8422 0.08510 0.07749 -0.0528 1.0000 0.0321
-15.500 -0.8441 0.08177 0.07396 -0.0533 1.0000 0.0325
-15.250 -0.8425 0.07899 0.07103 -0.0533 1.0000 0.0330
-15.000 -0.8355 0.07714 0.06920 -0.0530 1.0000 0.0338
-14.750 -0.8296 0.07513 0.06717 -0.0528 1.0000 0.0345
-14.500 -0.8250 0.07299 0.06496 -0.0526 1.0000 0.0354
-14.250 -0.8193 0.07097 0.06284 -0.0523 1.0000 0.0365
-14.000 -0.8109 0.06930 0.06107 -0.0516 1.0000 0.0375
-13.750 -0.8011 0.06784 0.05948 -0.0507 1.0000 0.0385
-13.500 -0.7895 0.06675 0.05841 -0.0496 1.0000 0.0394
-13.250 -0.7800 0.06546 0.05715 -0.0487 1.0000 0.0406
-13.000 -0.7706 0.06417 0.05585 -0.0478 1.0000 0.0419
-12.750 -0.7617 0.06284 0.05448 -0.0468 1.0000 0.0437
-12.500 -0.7517 0.06166 0.05320 -0.0458 1.0000 0.0456
-12.250 -0.7450 0.06024 0.05186 -0.0449 1.0000 0.0475
-12.000 -0.7379 0.05883 0.05047 -0.0439 1.0000 0.0497
-11.750 -0.7302 0.05754 0.04914 -0.0428 1.0000 0.0527
-11.500 -0.7250 0.05606 0.04770 -0.0417 1.0000 0.0555
-11.250 -0.7207 0.05450 0.04616 -0.0406 1.0000 0.0588
-11.000 -0.7168 0.05293 0.04458 -0.0394 1.0000 0.0635
-10.750 -0.7164 0.05110 0.04282 -0.0383 1.0000 0.0687
-10.500 -0.7163 0.04935 0.04112 -0.0370 1.0000 0.0755
-10.250 -0.7178 0.04754 0.03936 -0.0355 1.0000 0.0841
-10.000 -0.7224 0.04557 0.03750 -0.0340 1.0000 0.0938
-9.750 -0.7282 0.04359 0.03561 -0.0322 1.0000 0.1049
-9.500 -0.7365 0.04154 0.03368 -0.0302 1.0000 0.1180
-9.250 -0.7479 0.03942 0.03168 -0.0278 1.0000 0.1324
-9.000 -0.7633 0.03723 0.02962 -0.0250 1.0000 0.1476
-8.750 -0.7836 0.03506 0.02756 -0.0214 1.0000 0.1612
-8.500 -0.8072 0.03287 0.02546 -0.0173 1.0000 0.1727
-8.250 -0.8245 0.02986 0.02258 -0.0158 1.0000 0.1939
-8.000 -0.8329 0.02619 0.01918 -0.0170 1.0000 0.2375
-7.750 -0.8224 0.02536 0.01911 -0.0160 1.0000 0.3190
-7.500 -0.8005 0.02584 0.01977 -0.0148 1.0000 0.3731
-7.250 -0.7794 0.02525 0.01905 -0.0156 1.0000 0.4034
-7.000 -0.7560 0.02580 0.01951 -0.0148 1.0000 0.4225
-6.750 -0.7334 0.02595 0.01953 -0.0143 1.0000 0.4355
-6.500 -0.7106 0.02567 0.01907 -0.0147 1.0000 0.4482
-6.250 -0.6884 0.02761 0.02111 -0.0108 1.0000 0.4538
-6.000 -0.6470 0.02871 0.02208 -0.0127 0.9942 0.4663
-5.750 -0.6029 0.03045 0.02381 -0.0132 0.9868 0.4710
-5.500 -0.5609 0.02921 0.02231 -0.0186 0.9792 0.4811
-5.250 -0.5199 0.02963 0.02267 -0.0201 0.9711 0.4832
-5.000 -0.4827 0.02964 0.02261 -0.0216 0.9623 0.4858
-4.750 -0.4425 0.02928 0.02214 -0.0242 0.9536 0.4894
-4.500 -0.4067 0.02736 0.01997 -0.0290 0.9417 0.4974
-3.750 -0.3154 0.02630 0.01879 -0.0299 0.8940 0.5033
-3.500 -0.2865 0.02562 0.01804 -0.0305 0.8718 0.5064
-3.250 -0.2484 0.02443 0.01667 -0.0337 0.8495 0.5111
-3.000 -0.2056 0.02351 0.01558 -0.0371 0.8212 0.5147
-2.750 -0.1473 0.02309 0.01499 -0.0422 0.7833 0.5162
-2.500 -0.0809 0.02279 0.01435 -0.0491 0.7253 0.5180
-2.250 -0.0376 0.02272 0.01392 -0.0519 0.6663 0.5202
-2.000 -0.0052 0.02265 0.01352 -0.0530 0.6199 0.5229
-1.750 0.0247 0.02240 0.01298 -0.0541 0.5834 0.5262
-1.500 0.0556 0.02193 0.01218 -0.0559 0.5533 0.5300
-1.250 0.0841 0.02184 0.01191 -0.0563 0.5287 0.5318
-1.000 0.1115 0.02188 0.01183 -0.0562 0.5083 0.5334
-0.750 0.1389 0.02192 0.01175 -0.0562 0.4912 0.5353
-0.500 0.1666 0.02193 0.01164 -0.0564 0.4769 0.5375
-0.250 0.1949 0.02189 0.01147 -0.0567 0.4647 0.5401
0.000 0.2238 0.02177 0.01125 -0.0574 0.4533 0.5428
0.250 0.2534 0.02164 0.01096 -0.0583 0.4434 0.5458
0.500 0.2828 0.02153 0.01074 -0.0592 0.4337 0.5485
0.750 0.3099 0.02162 0.01078 -0.0590 0.4256 0.5501
1.000 0.3372 0.02170 0.01086 -0.0590 0.4178 0.5521
1.250 0.3650 0.02183 0.01090 -0.0591 0.4117 0.5544
1.500 0.3934 0.02188 0.01096 -0.0594 0.4051 0.5570
1.750 0.4223 0.02192 0.01095 -0.0599 0.3990 0.5598
2.000 0.4520 0.02199 0.01089 -0.0606 0.3938 0.5628
2.250 0.4817 0.02201 0.01090 -0.0614 0.3877 0.5657
2.500 0.5089 0.02215 0.01108 -0.0613 0.3824 0.5674
2.750 0.5364 0.02234 0.01125 -0.0613 0.3780 0.5696
3.000 0.5643 0.02252 0.01147 -0.0614 0.3738 0.5722
3.250 0.5925 0.02269 0.01170 -0.0616 0.3693 0.5752
3.500 0.6214 0.02287 0.01187 -0.0621 0.3652 0.5785
3.750 0.6513 0.02305 0.01197 -0.0628 0.3614 0.5819
4.000 0.6790 0.02327 0.01225 -0.0629 0.3576 0.5842
4.250 0.7057 0.02350 0.01260 -0.0628 0.3534 0.5864
4.500 0.7329 0.02375 0.01293 -0.0628 0.3497 0.5890
4.750 0.7608 0.02403 0.01325 -0.0630 0.3465 0.5922
5.000 0.7897 0.02433 0.01354 -0.0634 0.3436 0.5959
5.250 0.8185 0.02466 0.01391 -0.0639 0.3404 0.6000
5.500 0.8437 0.02497 0.01441 -0.0635 0.3365 0.6024
5.750 0.8695 0.02530 0.01486 -0.0633 0.3330 0.6053
6.000 0.8963 0.02564 0.01529 -0.0632 0.3300 0.6084
6.250 0.9243 0.02600 0.01567 -0.0634 0.3273 0.6120
6.500 0.9520 0.02641 0.01612 -0.0637 0.3243 0.6162
6.750 0.9757 0.02684 0.01679 -0.0632 0.3205 0.6194
7.000 0.9998 0.02726 0.01739 -0.0627 0.3169 0.6228
7.250 1.0254 0.02765 0.01789 -0.0625 0.3135 0.6269
7.500 1.0528 0.02801 0.01827 -0.0626 0.3103 0.6315
7.750 1.0778 0.02847 0.01885 -0.0624 0.3068 0.6355
8.000 1.0985 0.02895 0.01960 -0.0614 0.3022 0.6389
8.250 1.1217 0.02932 0.02012 -0.0608 0.2978 0.6431
8.500 1.1480 0.02960 0.02043 -0.0607 0.2939 0.6482
8.750 1.1706 0.03006 0.02104 -0.0601 0.2898 0.6530
9.000 1.1890 0.03057 0.02183 -0.0588 0.2846 0.6574
9.250 1.2116 0.03085 0.02223 -0.0581 0.2798 0.6628
9.500 1.2379 0.03102 0.02237 -0.0580 0.2755 0.6687
9.750 1.2511 0.03163 0.02335 -0.0560 0.2694 0.6731
10.000 1.2707 0.03187 0.02372 -0.0548 0.2638 0.6788
10.250 1.2928 0.03205 0.02394 -0.0541 0.2587 0.6856
10.500 1.3040 0.03265 0.02487 -0.0518 0.2520 0.6911
10.750 1.3221 0.03280 0.02511 -0.0505 0.2461 0.6983
11.000 1.3340 0.03333 0.02586 -0.0484 0.2396 0.7052
11.250 1.3449 0.03374 0.02646 -0.0462 0.2327 0.7125
11.500 1.3542 0.03413 0.02699 -0.0437 0.2263 0.7206
11.750 1.3585 0.03486 0.02797 -0.0408 0.2185 0.7286
12.000 1.3650 0.03549 0.02873 -0.0383 0.2114 0.7382
12.250 1.3673 0.03647 0.02993 -0.0357 0.2028 0.7486
12.500 1.3685 0.03760 0.03124 -0.0332 0.1946 0.7598
12.750 1.3676 0.03889 0.03265 -0.0308 0.1862 0.7728
13.000 1.3620 0.04078 0.03476 -0.0287 0.1774 0.7877
13.250 1.3535 0.04292 0.03701 -0.0268 0.1698 0.8058
13.500 1.3389 0.04589 0.04020 -0.0254 0.1624 0.8301
13.750 1.3180 0.04926 0.04373 -0.0240 0.1571 0.8787
14.000 1.2916 0.05449 0.04916 -0.0250 0.1518 1.0000
14.250 1.2673 0.06096 0.05569 -0.0278 0.1462 1.0000
14.500 1.2415 0.06812 0.06294 -0.0312 0.1410 1.0000
14.750 1.2160 0.07548 0.07039 -0.0347 0.1352 1.0000
15.000 1.2015 0.08115 0.07601 -0.0373 0.1295 1.0000
15.250 1.1808 0.08810 0.08308 -0.0406 0.1237 1.0000
15.500 1.1743 0.09262 0.08752 -0.0427 0.1180 1.0000
15.750 1.1603 0.09880 0.09379 -0.0457 0.1126 1.0000
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