NREL's S819 Airfoil (s819-nr) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: NREL's S819 Airfoil (s819-nr) Reynolds number: 1,000,000 Max Cl/Cd: 93.38 at α=7.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s819-nr-1000000.txt Download as CSV file: xf-s819-nr-1000000.csv |
XFOIL Version 6.96
Calculated polar for: NREL's S819 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
------ -------- --------- --------- -------- -------- --------
-18.750 -0.6659 0.15136 0.14928 -0.0295 1.0000 0.0063
-18.500 -0.6827 0.14402 0.14186 -0.0331 1.0000 0.0062
-18.250 -0.7008 0.13689 0.13463 -0.0366 1.0000 0.0062
-18.000 -0.7177 0.13033 0.12798 -0.0398 1.0000 0.0061
-17.750 -0.7339 0.12417 0.12173 -0.0427 1.0000 0.0061
-17.500 -0.7504 0.11821 0.11566 -0.0453 1.0000 0.0061
-17.250 -0.7649 0.11287 0.11023 -0.0476 1.0000 0.0061
-17.000 -0.7807 0.10751 0.10477 -0.0498 1.0000 0.0061
-16.750 -0.7945 0.10262 0.09978 -0.0517 1.0000 0.0061
-16.500 -0.8077 0.09800 0.09506 -0.0533 1.0000 0.0061
-16.250 -0.8205 0.09364 0.09060 -0.0547 1.0000 0.0061
-16.000 -0.8333 0.08942 0.08627 -0.0559 1.0000 0.0062
-15.750 -0.8442 0.08560 0.08236 -0.0569 1.0000 0.0062
-15.500 -0.8548 0.08192 0.07857 -0.0576 1.0000 0.0062
-15.250 -0.8636 0.07859 0.07515 -0.0580 1.0000 0.0062
-15.000 -0.8710 0.07554 0.07200 -0.0583 1.0000 0.0062
-14.750 -0.8776 0.07258 0.06895 -0.0583 1.0000 0.0063
-14.500 -0.8823 0.06981 0.06608 -0.0582 1.0000 0.0064
-14.250 -0.8855 0.06718 0.06336 -0.0578 1.0000 0.0064
-14.000 -0.8862 0.06480 0.06089 -0.0573 1.0000 0.0066
-13.750 -0.8870 0.06249 0.05850 -0.0567 1.0000 0.0066
-13.500 -0.8864 0.06044 0.05635 -0.0560 1.0000 0.0067
-13.250 -0.8843 0.05861 0.05442 -0.0550 1.0000 0.0069
-13.000 -0.8816 0.05687 0.05259 -0.0540 1.0000 0.0069
-12.750 -0.8908 0.05531 0.05090 -0.0528 1.0000 0.0071
-12.500 -0.8853 0.05359 0.04911 -0.0517 1.0000 0.0071
-12.250 -0.8865 0.05200 0.04742 -0.0504 1.0000 0.0071
-12.000 -0.8858 0.05053 0.04587 -0.0490 1.0000 0.0071
-11.750 -0.8833 0.04904 0.04429 -0.0475 1.0000 0.0072
-11.500 -0.8728 0.04762 0.04282 -0.0462 1.0000 0.0072
-11.250 -0.8662 0.04623 0.04135 -0.0446 1.0000 0.0072
-11.000 -0.8526 0.04495 0.04003 -0.0433 1.0000 0.0072
-10.750 -0.7241 0.04648 0.04179 -0.0414 1.0000 0.0076
-10.500 -0.7008 0.04642 0.04178 -0.0395 1.0000 0.0078
-10.250 -0.6813 0.04626 0.04165 -0.0376 1.0000 0.0079
-10.000 -0.6634 0.04612 0.04153 -0.0356 1.0000 0.0082
-9.750 -0.6454 0.04582 0.04124 -0.0341 0.9999 0.0084
-9.500 -0.6138 0.04553 0.04095 -0.0348 0.9990 0.0089
-9.250 -0.5897 0.04373 0.03906 -0.0376 0.9975 0.0096
-9.000 -0.5681 0.04156 0.03679 -0.0412 0.9958 0.0098
-8.750 -0.5200 0.04485 0.04027 -0.0372 0.9953 0.0104
-8.500 -0.4902 0.04446 0.03995 -0.0387 0.9940 0.0107
-8.250 -0.4677 0.04358 0.03910 -0.0397 0.9916 0.0111
-8.000 -0.4452 0.04218 0.03772 -0.0418 0.9891 0.0118
-7.750 -0.4193 0.04015 0.03560 -0.0452 0.9869 0.0129
-7.500 -0.3996 0.03845 0.03394 -0.0479 0.9847 0.0138
-7.250 -0.3921 0.03568 0.03118 -0.0502 0.9802 0.0143
-7.000 -0.3809 0.03256 0.02804 -0.0537 0.9753 0.0148
-6.750 -0.3517 0.03066 0.02608 -0.0577 0.9726 0.0175
-6.500 -0.3592 0.02537 0.02069 -0.0623 0.9607 0.0181
-6.250 -0.3622 0.02106 0.01627 -0.0654 0.9410 0.0187
-6.000 -0.3625 0.01793 0.01296 -0.0667 0.9013 0.0192
-5.750 -0.3637 0.01587 0.01058 -0.0666 0.8502 0.0201
-5.250 -0.3428 0.01383 0.00798 -0.0637 0.7927 0.0086
-5.000 -0.3250 0.01313 0.00706 -0.0629 0.7717 0.0076
-4.750 -0.3037 0.01262 0.00641 -0.0625 0.7529 0.0075
-4.500 -0.2807 0.01220 0.00586 -0.0622 0.7354 0.0076
-4.250 -0.2565 0.01185 0.00542 -0.0620 0.7196 0.0084
-4.000 -0.2312 0.01161 0.00509 -0.0620 0.7044 0.0093
-3.500 -0.1791 0.01117 0.00448 -0.0620 0.6760 0.0114
-3.250 -0.1521 0.01102 0.00426 -0.0622 0.6633 0.0140
-3.000 -0.1347 0.00879 0.00272 -0.0627 0.6518 0.2702
-2.750 -0.1073 0.00862 0.00268 -0.0630 0.6396 0.3016
-2.500 -0.0790 0.00865 0.00269 -0.0633 0.6269 0.3116
-2.250 -0.0503 0.00867 0.00271 -0.0636 0.6153 0.3165
-2.000 -0.0217 0.00871 0.00269 -0.0639 0.6045 0.3187
-1.500 0.0355 0.00873 0.00261 -0.0644 0.5829 0.3202
-1.250 0.0638 0.00869 0.00254 -0.0647 0.5723 0.3220
-0.750 0.1209 0.00864 0.00245 -0.0653 0.5511 0.3260
-0.500 0.1494 0.00865 0.00243 -0.0656 0.5416 0.3277
-0.250 0.1781 0.00865 0.00242 -0.0659 0.5317 0.3294
0.000 0.2068 0.00867 0.00241 -0.0662 0.5226 0.3312
0.500 0.2640 0.00873 0.00242 -0.0668 0.5034 0.3343
0.750 0.2924 0.00876 0.00242 -0.0670 0.4941 0.3363
1.000 0.3211 0.00875 0.00242 -0.0674 0.4851 0.3395
1.250 0.3496 0.00877 0.00245 -0.0676 0.4767 0.3422
1.500 0.3782 0.00881 0.00248 -0.0679 0.4680 0.3449
1.750 0.4067 0.00886 0.00252 -0.0682 0.4599 0.3476
2.000 0.4350 0.00893 0.00257 -0.0684 0.4511 0.3496
2.250 0.4636 0.00894 0.00260 -0.0687 0.4429 0.3536
2.500 0.4917 0.00899 0.00266 -0.0689 0.4346 0.3574
2.750 0.5203 0.00904 0.00272 -0.0691 0.4274 0.3608
3.000 0.5484 0.00912 0.00279 -0.0693 0.4197 0.3639
3.250 0.5768 0.00917 0.00286 -0.0695 0.4125 0.3678
3.500 0.6048 0.00923 0.00294 -0.0697 0.4043 0.3720
3.750 0.6329 0.00930 0.00303 -0.0698 0.3959 0.3761
4.000 0.6603 0.00943 0.00312 -0.0699 0.3865 0.3794
4.250 0.6885 0.00948 0.00321 -0.0701 0.3786 0.3842
4.750 0.7439 0.00966 0.00343 -0.0703 0.3628 0.3932
5.000 0.7709 0.00980 0.00356 -0.0702 0.3550 0.3970
5.250 0.7989 0.00986 0.00367 -0.0704 0.3478 0.4020
5.750 0.8533 0.01010 0.00394 -0.0704 0.3326 0.4106
6.000 0.8801 0.01023 0.00409 -0.0704 0.3253 0.4158
6.250 0.9074 0.01033 0.00425 -0.0704 0.3185 0.4210
6.500 0.9339 0.01049 0.00441 -0.0702 0.3106 0.4255
6.750 0.9607 0.01061 0.00457 -0.0702 0.3031 0.4309
7.000 0.9867 0.01078 0.00476 -0.0700 0.2946 0.4365
7.250 1.0129 0.01094 0.00494 -0.0698 0.2854 0.4415
7.500 1.0381 0.01114 0.00516 -0.0695 0.2742 0.4474
7.750 1.0627 0.01138 0.00539 -0.0691 0.2603 0.4534
8.000 1.0862 0.01167 0.00564 -0.0685 0.2416 0.4587
8.250 1.1062 0.01215 0.00601 -0.0674 0.2120 0.4652
8.500 1.1215 0.01288 0.00654 -0.0656 0.1757 0.4712
8.750 1.1391 0.01345 0.00702 -0.0641 0.1524 0.4772
9.000 1.1547 0.01403 0.00753 -0.0623 0.1319 0.4842
9.250 1.1682 0.01458 0.00800 -0.0600 0.1134 0.4901
9.500 1.1819 0.01513 0.00851 -0.0579 0.0986 0.4971
9.750 1.1966 0.01568 0.00904 -0.0559 0.0870 0.5039
10.000 1.2093 0.01632 0.00964 -0.0538 0.0743 0.5106
10.250 1.2240 0.01688 0.01020 -0.0520 0.0669 0.5180
10.500 1.2363 0.01755 0.01085 -0.0499 0.0583 0.5249
10.750 1.2498 0.01817 0.01149 -0.0481 0.0517 0.5329
11.000 1.2624 0.01884 0.01217 -0.0462 0.0462 0.5402
11.250 1.2752 0.01951 0.01289 -0.0444 0.0423 0.5488
11.500 1.2860 0.02031 0.01371 -0.0425 0.0375 0.5569
11.750 1.2956 0.02119 0.01462 -0.0406 0.0333 0.5657
12.000 1.3056 0.02209 0.01558 -0.0388 0.0299 0.5753
12.250 1.3134 0.02316 0.01669 -0.0370 0.0265 0.5860
12.500 1.3219 0.02426 0.01785 -0.0355 0.0239 0.5965
12.750 1.3288 0.02552 0.01918 -0.0339 0.0216 0.6084
13.000 1.3349 0.02692 0.02065 -0.0326 0.0194 0.6209
13.250 1.3400 0.02848 0.02228 -0.0314 0.0173 0.6327
13.500 1.3442 0.03020 0.02408 -0.0303 0.0158 0.6448
13.750 1.3501 0.03190 0.02587 -0.0295 0.0147 0.6573
14.000 1.3542 0.03382 0.02790 -0.0289 0.0137 0.6707
14.250 1.3552 0.03612 0.03028 -0.0283 0.0123 0.6855
14.500 1.3593 0.03825 0.03252 -0.0280 0.0116 0.7010
14.750 1.3616 0.04062 0.03502 -0.0279 0.0111 0.7188
15.000 1.3619 0.04328 0.03781 -0.0279 0.0104 0.7387
15.250 1.3605 0.04623 0.04088 -0.0281 0.0097 0.7608
15.500 1.3610 0.04905 0.04386 -0.0284 0.0092 0.7896
15.750 1.3607 0.05188 0.04692 -0.0286 0.0088 0.8398
16.000 1.3548 0.05467 0.05003 -0.0281 0.0084 1.0000
16.250 1.3518 0.05825 0.05368 -0.0290 0.0079 1.0000
16.500 1.3478 0.06206 0.05756 -0.0300 0.0075 1.0000
16.750 1.3440 0.06595 0.06153 -0.0312 0.0070 1.0000
17.000 1.3416 0.06977 0.06543 -0.0325 0.0068 1.0000
17.250 1.3390 0.07368 0.06943 -0.0338 0.0064 1.0000
17.500 1.3345 0.07794 0.07378 -0.0354 0.0062 1.0000
17.750 1.3292 0.08241 0.07832 -0.0372 0.0058 1.0000
18.000 1.3228 0.08712 0.08311 -0.0391 0.0056 1.0000
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