NREL's S819 Airfoil (s819-nr) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: NREL's S819 Airfoil (s819-nr) Reynolds number: 500,000 Max Cl/Cd: 72.52 at α=7.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s819-nr-500000-n5.txt Download as CSV file: xf-s819-nr-500000-n5.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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-19.000 -0.6428 0.16047 0.15770 -0.0253 1.0000 0.0080
-18.750 -0.6601 0.15239 0.14953 -0.0294 1.0000 0.0079
-18.500 -0.6781 0.14473 0.14175 -0.0332 1.0000 0.0078
-18.250 -0.6935 0.13811 0.13503 -0.0365 1.0000 0.0078
-18.000 -0.7091 0.13174 0.12856 -0.0395 1.0000 0.0078
-17.750 -0.7247 0.12564 0.12233 -0.0423 1.0000 0.0077
-17.500 -0.7394 0.11997 0.11656 -0.0448 1.0000 0.0077
-17.250 -0.7538 0.11459 0.11105 -0.0471 1.0000 0.0077
-17.000 -0.7661 0.10973 0.10610 -0.0490 1.0000 0.0077
-16.750 -0.7774 0.10517 0.10143 -0.0507 1.0000 0.0077
-16.500 -0.7888 0.10067 0.09681 -0.0523 1.0000 0.0077
-16.250 -0.7986 0.09653 0.09256 -0.0536 1.0000 0.0077
-16.000 -0.8072 0.09265 0.08858 -0.0547 1.0000 0.0078
-15.750 -0.8146 0.08897 0.08480 -0.0556 1.0000 0.0078
-15.500 -0.8208 0.08553 0.08126 -0.0563 1.0000 0.0078
-15.250 -0.8256 0.08229 0.07792 -0.0569 1.0000 0.0078
-15.000 -0.8290 0.07928 0.07480 -0.0572 1.0000 0.0078
-14.750 -0.8313 0.07640 0.07182 -0.0574 1.0000 0.0079
-14.500 -0.8327 0.07368 0.06902 -0.0574 1.0000 0.0080
-14.250 -0.8321 0.07117 0.06641 -0.0572 1.0000 0.0080
-14.000 -0.8303 0.06872 0.06388 -0.0570 1.0000 0.0081
-13.750 -0.8264 0.06655 0.06163 -0.0566 1.0000 0.0082
-13.500 -0.8208 0.06450 0.05950 -0.0560 1.0000 0.0082
-13.250 -0.8136 0.06254 0.05746 -0.0553 1.0000 0.0084
-13.000 -0.8047 0.06082 0.05566 -0.0546 1.0000 0.0085
-12.750 -0.7925 0.05924 0.05402 -0.0536 1.0000 0.0087
-12.500 -0.7793 0.05788 0.05259 -0.0526 1.0000 0.0088
-12.250 -0.7654 0.05662 0.05126 -0.0515 1.0000 0.0091
-12.000 -0.7565 0.05528 0.04983 -0.0505 1.0000 0.0094
-11.750 -0.7757 0.05307 0.04743 -0.0501 1.0000 0.0097
-11.500 -0.7676 0.05174 0.04601 -0.0490 1.0000 0.0098
-11.250 -0.7675 0.05025 0.04442 -0.0479 1.0000 0.0098
-11.000 -0.7512 0.04924 0.04336 -0.0466 1.0000 0.0099
-10.750 -0.7337 0.04830 0.04238 -0.0452 1.0000 0.0099
-10.500 -0.5940 0.05666 0.05120 -0.0368 1.0000 0.0067
-10.250 -0.5725 0.05742 0.05200 -0.0342 1.0000 0.0065
-10.000 -0.5521 0.05819 0.05282 -0.0316 1.0000 0.0061
-9.750 -0.5350 0.05823 0.05288 -0.0299 0.9998 0.0060
-9.500 -0.5023 0.05885 0.05353 -0.0298 0.9985 0.0056
-9.250 -0.4747 0.05859 0.05327 -0.0306 0.9966 0.0053
-9.000 -0.4522 0.05726 0.05192 -0.0323 0.9944 0.0051
-8.750 -0.4371 0.05545 0.05012 -0.0338 0.9917 0.0052
-8.500 -0.4203 0.05340 0.04805 -0.0359 0.9887 0.0050
-8.250 -0.4081 0.05066 0.04530 -0.0385 0.9857 0.0051
-8.000 -0.4000 0.04749 0.04209 -0.0412 0.9820 0.0051
-7.750 -0.3985 0.04401 0.03856 -0.0434 0.9760 0.0051
-7.500 -0.3943 0.04000 0.03447 -0.0471 0.9715 0.0051
-7.250 -0.4006 0.03604 0.03043 -0.0489 0.9609 0.0051
-7.000 -0.3987 0.03243 0.02673 -0.0514 0.9488 0.0051
-6.500 -0.3918 0.02354 0.01751 -0.0603 0.8974 0.0053
-6.250 -0.3828 0.02035 0.01402 -0.0636 0.8543 0.0055
-6.000 -0.3877 0.01833 0.01172 -0.0626 0.8175 0.0054
-5.750 -0.3803 0.01709 0.01026 -0.0620 0.7911 0.0057
-5.500 -0.3664 0.01631 0.00930 -0.0613 0.7704 0.0060
-5.250 -0.3490 0.01566 0.00849 -0.0607 0.7523 0.0062
-5.000 -0.3293 0.01513 0.00783 -0.0602 0.7350 0.0066
-4.750 -0.3076 0.01470 0.00725 -0.0599 0.7190 0.0071
-4.500 -0.2849 0.01432 0.00673 -0.0596 0.7040 0.0074
-4.250 -0.2610 0.01404 0.00635 -0.0595 0.6895 0.0087
-4.000 -0.2361 0.01382 0.00603 -0.0594 0.6749 0.0099
-3.750 -0.2111 0.01357 0.00565 -0.0594 0.6610 0.0109
-3.500 -0.1854 0.01339 0.00537 -0.0593 0.6476 0.0124
-3.250 -0.1594 0.01321 0.00512 -0.0593 0.6351 0.0185
-3.000 -0.1443 0.01095 0.00360 -0.0599 0.6240 0.2899
-2.750 -0.1166 0.01090 0.00358 -0.0601 0.6121 0.3053
-2.500 -0.0889 0.01086 0.00356 -0.0604 0.6008 0.3144
-2.250 -0.0611 0.01085 0.00348 -0.0606 0.5899 0.3163
-2.000 -0.0331 0.01083 0.00340 -0.0608 0.5795 0.3174
-1.750 -0.0051 0.01081 0.00334 -0.0610 0.5696 0.3184
-1.500 0.0227 0.01082 0.00328 -0.0612 0.5590 0.3195
-1.250 0.0508 0.01081 0.00323 -0.0614 0.5485 0.3204
-1.000 0.0788 0.01078 0.00318 -0.0616 0.5392 0.3220
-0.750 0.1067 0.01077 0.00314 -0.0618 0.5299 0.3235
-0.500 0.1350 0.01075 0.00312 -0.0621 0.5211 0.3252
-0.250 0.1628 0.01077 0.00310 -0.0622 0.5120 0.3269
0.000 0.1910 0.01077 0.00310 -0.0625 0.5023 0.3287
0.250 0.2190 0.01079 0.00310 -0.0627 0.4934 0.3306
0.500 0.2471 0.01081 0.00310 -0.0629 0.4847 0.3324
0.750 0.2752 0.01085 0.00312 -0.0631 0.4770 0.3342
1.000 0.3033 0.01087 0.00313 -0.0633 0.4687 0.3361
1.250 0.3313 0.01089 0.00317 -0.0635 0.4609 0.3385
1.500 0.3592 0.01092 0.00320 -0.0637 0.4524 0.3410
1.750 0.3872 0.01097 0.00325 -0.0639 0.4445 0.3436
2.000 0.4151 0.01102 0.00331 -0.0640 0.4368 0.3463
2.250 0.4429 0.01108 0.00337 -0.0642 0.4300 0.3488
2.500 0.4710 0.01112 0.00343 -0.0644 0.4229 0.3517
2.750 0.4985 0.01119 0.00352 -0.0645 0.4160 0.3550
3.000 0.5265 0.01124 0.00360 -0.0646 0.4088 0.3586
3.250 0.5538 0.01133 0.00370 -0.0647 0.4019 0.3621
3.500 0.5817 0.01140 0.00380 -0.0648 0.3959 0.3651
3.750 0.6093 0.01147 0.00391 -0.0649 0.3896 0.3686
4.000 0.6365 0.01156 0.00404 -0.0650 0.3836 0.3723
4.250 0.6640 0.01164 0.00416 -0.0650 0.3764 0.3761
4.500 0.6906 0.01178 0.00429 -0.0650 0.3684 0.3794
4.750 0.7177 0.01188 0.00443 -0.0650 0.3594 0.3831
5.000 0.7441 0.01201 0.00459 -0.0649 0.3511 0.3872
5.250 0.7707 0.01214 0.00474 -0.0648 0.3425 0.3914
5.500 0.7970 0.01228 0.00491 -0.0646 0.3350 0.3952
5.750 0.8233 0.01242 0.00509 -0.0645 0.3267 0.3994
6.000 0.8492 0.01257 0.00528 -0.0643 0.3182 0.4039
6.250 0.8744 0.01276 0.00549 -0.0640 0.3088 0.4084
6.500 0.9003 0.01291 0.00569 -0.0638 0.3005 0.4126
6.750 0.9249 0.01312 0.00593 -0.0634 0.2916 0.4175
7.000 0.9502 0.01330 0.00616 -0.0631 0.2818 0.4230
7.250 0.9744 0.01352 0.00642 -0.0627 0.2706 0.4281
7.500 0.9978 0.01378 0.00669 -0.0621 0.2577 0.4338
7.750 1.0204 0.01407 0.00699 -0.0614 0.2423 0.4394
8.000 1.0403 0.01450 0.00736 -0.0603 0.2196 0.4445
8.250 1.0574 0.01504 0.00781 -0.0588 0.1931 0.4498
8.500 1.0712 0.01564 0.00832 -0.0567 0.1691 0.4550
8.750 1.0848 0.01622 0.00885 -0.0546 0.1501 0.4599
9.000 1.0978 0.01688 0.00946 -0.0525 0.1318 0.4654
9.250 1.1112 0.01755 0.01009 -0.0505 0.1155 0.4710
9.500 1.1241 0.01825 0.01075 -0.0485 0.1010 0.4763
9.750 1.1373 0.01892 0.01144 -0.0467 0.0901 0.4823
10.250 1.1631 0.02033 0.01288 -0.0431 0.0726 0.4952
10.500 1.1750 0.02109 0.01368 -0.0413 0.0663 0.5021
10.750 1.1863 0.02190 0.01453 -0.0395 0.0601 0.5092
11.000 1.1973 0.02276 0.01545 -0.0378 0.0555 0.5169
11.250 1.2073 0.02371 0.01646 -0.0362 0.0505 0.5247
11.500 1.2160 0.02477 0.01758 -0.0346 0.0462 0.5335
11.750 1.2245 0.02592 0.01880 -0.0331 0.0421 0.5424
12.000 1.2309 0.02727 0.02021 -0.0316 0.0383 0.5518
12.250 1.2383 0.02863 0.02166 -0.0305 0.0349 0.5604
12.500 1.2422 0.03033 0.02341 -0.0293 0.0316 0.5697
12.750 1.2485 0.03194 0.02513 -0.0284 0.0288 0.5781
13.000 1.2517 0.03391 0.02716 -0.0277 0.0261 0.5866
13.250 1.2554 0.03593 0.02929 -0.0271 0.0241 0.5959
13.500 1.2583 0.03812 0.03157 -0.0268 0.0219 0.6051
13.750 1.2592 0.04061 0.03415 -0.0265 0.0203 0.6150
14.000 1.2616 0.04304 0.03669 -0.0265 0.0189 0.6248
14.250 1.2596 0.04603 0.03975 -0.0267 0.0164 0.6344
14.500 1.2596 0.04892 0.04276 -0.0270 0.0152 0.6449
14.750 1.2606 0.05178 0.04577 -0.0274 0.0151 0.6565
15.000 1.2596 0.05497 0.04907 -0.0281 0.0139 0.6679
15.250 1.2566 0.05849 0.05271 -0.0289 0.0127 0.6804
15.500 1.2544 0.06204 0.05638 -0.0298 0.0118 0.6937
15.750 1.2525 0.06562 0.06010 -0.0309 0.0110 0.7090
16.000 1.2490 0.06952 0.06413 -0.0321 0.0102 0.7239
16.250 1.2447 0.07364 0.06839 -0.0336 0.0096 0.7409
16.500 1.2423 0.07753 0.07243 -0.0350 0.0088 0.7610
16.750 1.2383 0.08168 0.07675 -0.0365 0.0081 0.7869
17.000 1.2337 0.08586 0.08113 -0.0379 0.0077 0.8256
17.250 1.2233 0.08971 0.08527 -0.0383 0.0072 1.0000
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