NREL's S807 Airfoil (s807-nr) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: NREL's S807 Airfoil (s807-nr) Reynolds number: 50,000 Max Cl/Cd: 21.98 at α=7.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s807-nr-50000-n5.txt Download as CSV file: xf-s807-nr-50000-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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.750 -0.6082 0.13607 0.12796 -0.0304 1.0000 0.0598
-15.500 -0.6516 0.12135 0.11313 -0.0378 1.0000 0.0592
-15.250 -0.6897 0.10973 0.10128 -0.0435 1.0000 0.0588
-15.000 -0.7130 0.10189 0.09322 -0.0469 1.0000 0.0589
-14.750 -0.7284 0.09585 0.08695 -0.0492 1.0000 0.0595
-14.500 -0.7393 0.09076 0.08163 -0.0507 1.0000 0.0605
-14.250 -0.7455 0.08643 0.07706 -0.0516 1.0000 0.0615
-14.000 -0.7475 0.08274 0.07307 -0.0520 1.0000 0.0627
-13.750 -0.7325 0.08153 0.07193 -0.0508 1.0000 0.0647
-13.500 -0.7236 0.07967 0.07003 -0.0501 1.0000 0.0671
-13.250 -0.7172 0.07744 0.06766 -0.0496 1.0000 0.0702
-13.000 -0.7095 0.07538 0.06544 -0.0489 1.0000 0.0736
-12.750 -0.6988 0.07407 0.06423 -0.0479 1.0000 0.0773
-12.500 -0.6897 0.07244 0.06253 -0.0469 1.0000 0.0818
-12.250 -0.6811 0.07088 0.06098 -0.0458 1.0000 0.0869
-12.000 -0.6751 0.06911 0.05926 -0.0449 1.0000 0.0934
-11.750 -0.6706 0.06725 0.05748 -0.0440 1.0000 0.1012
-11.500 -0.6672 0.06529 0.05559 -0.0430 1.0000 0.1112
-11.250 -0.6664 0.06321 0.05366 -0.0421 1.0000 0.1229
-11.000 -0.6677 0.06103 0.05169 -0.0411 1.0000 0.1374
-10.750 -0.6708 0.05884 0.04978 -0.0400 1.0000 0.1553
-10.500 -0.6747 0.05688 0.04818 -0.0385 1.0000 0.1795
-10.250 -0.6743 0.05575 0.04750 -0.0365 1.0000 0.2150
-10.000 -0.6514 0.05775 0.04992 -0.0333 1.0000 0.2630
-9.750 -0.6333 0.05903 0.05120 -0.0308 1.0000 0.2942
-9.500 -0.6143 0.06043 0.05249 -0.0283 1.0000 0.3152
-9.250 -0.6067 0.06043 0.05239 -0.0263 1.0000 0.3349
-9.000 -0.6111 0.05925 0.05117 -0.0243 1.0000 0.3539
-8.750 -0.6055 0.05926 0.05109 -0.0219 1.0000 0.3703
-8.250 -0.5775 0.06054 0.05217 -0.0168 1.0000 0.3977
-8.000 -0.5581 0.06124 0.05276 -0.0145 1.0000 0.4088
-7.750 -0.5540 0.06079 0.05225 -0.0120 1.0000 0.4207
-7.500 -0.5634 0.05964 0.05109 -0.0089 1.0000 0.4333
-7.250 -0.5335 0.06036 0.05168 -0.0072 1.0000 0.4409
-7.000 -0.5380 0.05938 0.05069 -0.0042 1.0000 0.4512
-6.750 -0.5319 0.05885 0.05011 -0.0015 1.0000 0.4600
-6.500 -0.5273 0.05814 0.04935 0.0011 1.0000 0.4680
-6.000 -0.5199 0.05628 0.04743 0.0057 1.0000 0.4838
-5.750 -0.5084 0.05566 0.04676 0.0077 1.0000 0.4903
-5.500 -0.5165 0.05394 0.04504 0.0100 1.0000 0.4990
-5.250 -0.4995 0.05360 0.04465 0.0119 1.0000 0.5036
-5.000 -0.5157 0.05114 0.04218 0.0134 1.0000 0.5140
-4.750 -0.4974 0.05097 0.04198 0.0155 1.0000 0.5171
-4.500 -0.4863 0.05037 0.04136 0.0174 1.0000 0.5218
-4.250 -0.4961 0.04787 0.03882 0.0177 1.0000 0.5311
-4.000 -0.4461 0.04782 0.03865 0.0141 0.9891 0.5339
-3.750 -0.3971 0.04726 0.03798 0.0096 0.9752 0.5378
-3.500 -0.3555 0.04593 0.03651 0.0046 0.9582 0.5436
-3.250 -0.3210 0.04414 0.03461 0.0000 0.9386 0.5493
-3.000 -0.2858 0.04344 0.03388 -0.0013 0.9163 0.5520
-2.750 -0.2523 0.04248 0.03285 -0.0030 0.8916 0.5554
-2.500 -0.2193 0.04110 0.03141 -0.0054 0.8652 0.5597
-2.250 -0.1902 0.03910 0.02928 -0.0090 0.8354 0.5656
-2.000 -0.1490 0.03834 0.02845 -0.0108 0.8058 0.5678
-1.750 -0.0991 0.03745 0.02742 -0.0144 0.7727 0.5702
-1.500 -0.0423 0.03656 0.02627 -0.0197 0.7336 0.5732
-1.250 0.0057 0.03572 0.02509 -0.0240 0.6920 0.5771
-1.000 0.0390 0.03470 0.02371 -0.0273 0.6551 0.5819
-0.750 0.0688 0.03431 0.02306 -0.0282 0.6243 0.5842
-0.500 0.0955 0.03411 0.02267 -0.0282 0.5984 0.5863
-0.250 0.1212 0.03391 0.02229 -0.0283 0.5768 0.5891
0.000 0.1474 0.03365 0.02186 -0.0288 0.5584 0.5924
0.250 0.1745 0.03325 0.02130 -0.0301 0.5425 0.5962
0.500 0.2037 0.03270 0.02057 -0.0324 0.5284 0.6001
0.750 0.2312 0.03266 0.02042 -0.0325 0.5161 0.6020
1.000 0.2575 0.03261 0.02035 -0.0326 0.5039 0.6045
1.250 0.2856 0.03255 0.02024 -0.0331 0.4937 0.6076
1.500 0.3150 0.03244 0.02006 -0.0343 0.4843 0.6111
1.750 0.3456 0.03226 0.01983 -0.0361 0.4753 0.6151
2.000 0.3762 0.03215 0.01967 -0.0376 0.4671 0.6181
2.250 0.4030 0.03224 0.01978 -0.0377 0.4594 0.6204
2.500 0.4299 0.03234 0.01991 -0.0379 0.4520 0.6234
2.750 0.4600 0.03244 0.01995 -0.0388 0.4463 0.6269
3.000 0.4875 0.03255 0.02016 -0.0398 0.4395 0.6310
3.250 0.5178 0.03264 0.02025 -0.0412 0.4335 0.6349
3.500 0.5454 0.03286 0.02045 -0.0413 0.4285 0.6375
3.750 0.5688 0.03316 0.02092 -0.0411 0.4223 0.6404
4.000 0.5951 0.03343 0.02126 -0.0414 0.4170 0.6440
4.250 0.6253 0.03371 0.02152 -0.0426 0.4128 0.6484
4.500 0.6515 0.03413 0.02206 -0.0432 0.4081 0.6525
4.750 0.6735 0.03461 0.02272 -0.0426 0.4030 0.6557
5.000 0.6992 0.03502 0.02322 -0.0427 0.3984 0.6593
5.250 0.7290 0.03540 0.02358 -0.0435 0.3946 0.6635
5.500 0.7529 0.03612 0.02450 -0.0442 0.3898 0.6682
5.750 0.7728 0.03682 0.02543 -0.0434 0.3856 0.6715
6.000 0.7962 0.03743 0.02616 -0.0431 0.3815 0.6756
6.250 0.8248 0.03793 0.02669 -0.0437 0.3779 0.6806
6.500 0.8457 0.03891 0.02789 -0.0438 0.3733 0.6856
6.750 0.8610 0.03992 0.02917 -0.0426 0.3688 0.6892
7.000 0.8818 0.04076 0.03016 -0.0422 0.3648 0.6936
7.250 0.9095 0.04138 0.03083 -0.0427 0.3611 0.6991
7.500 0.9254 0.04260 0.03229 -0.0420 0.3567 0.7040
7.750 0.9333 0.04410 0.03409 -0.0403 0.3517 0.7085
8.000 0.9519 0.04514 0.03529 -0.0398 0.3473 0.7142
8.250 0.9817 0.04562 0.03583 -0.0404 0.3435 0.7203
8.500 0.9795 0.04773 0.03828 -0.0379 0.3382 0.7248
8.750 0.9814 0.04970 0.04050 -0.0362 0.3328 0.7303
9.000 1.0062 0.05032 0.04122 -0.0362 0.3282 0.7372
9.250 1.0190 0.05150 0.04257 -0.0350 0.3237 0.7434
9.500 0.9762 0.05609 0.04749 -0.0308 0.3171 0.7477
9.750 0.9942 0.05688 0.04840 -0.0301 0.3122 0.7552
10.000 1.0321 0.05646 0.04808 -0.0303 0.3080 0.7641
10.250 0.8842 0.07187 0.06370 -0.0290 0.2967 0.7617
10.500 0.9336 0.06905 0.06103 -0.0271 0.2939 0.7728
11.000 0.8780 0.08274 0.07493 -0.0321 0.2767 0.7831
11.500 0.8568 0.09249 0.08489 -0.0356 0.2605 0.7972
12.000 0.8455 0.10076 0.09340 -0.0383 0.2450 0.8155
12.250 0.8150 0.10900 0.10169 -0.0423 0.2342 0.8203
12.500 0.8365 0.10844 0.10133 -0.0405 0.2300 0.8403
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