NREL's S819 Airfoil (s819-nr) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: NREL's S819 Airfoil (s819-nr) Reynolds number: 500,000 Max Cl/Cd: 77.59 at α=8.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s819-nr-500000.txt Download as CSV file: xf-s819-nr-500000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-19.000 -0.6401 0.16163 0.15889 -0.0253 1.0000 0.0108
-18.750 -0.6577 0.15345 0.15062 -0.0295 1.0000 0.0107
-18.500 -0.6764 0.14565 0.14271 -0.0335 1.0000 0.0106
-18.250 -0.6924 0.13894 0.13590 -0.0369 1.0000 0.0106
-18.000 -0.7088 0.13248 0.12934 -0.0400 1.0000 0.0106
-17.750 -0.7251 0.12636 0.12310 -0.0429 1.0000 0.0106
-17.500 -0.7401 0.12070 0.11733 -0.0455 1.0000 0.0106
-17.250 -0.7560 0.11522 0.11173 -0.0479 1.0000 0.0105
-17.000 -0.7684 0.11040 0.10682 -0.0498 1.0000 0.0106
-16.750 -0.7810 0.10573 0.10204 -0.0516 1.0000 0.0106
-16.500 -0.7932 0.10123 0.09743 -0.0532 1.0000 0.0106
-16.250 -0.8042 0.09706 0.09315 -0.0546 1.0000 0.0106
-16.000 -0.8134 0.09315 0.08914 -0.0557 1.0000 0.0107
-15.750 -0.8222 0.08942 0.08531 -0.0567 1.0000 0.0107
-15.500 -0.8297 0.08589 0.08169 -0.0574 1.0000 0.0108
-15.250 -0.8364 0.08259 0.07829 -0.0580 1.0000 0.0108
-15.000 -0.8416 0.07952 0.07510 -0.0584 1.0000 0.0108
-14.750 -0.8457 0.07657 0.07206 -0.0586 1.0000 0.0110
-14.500 -0.8487 0.07377 0.06918 -0.0586 1.0000 0.0111
-14.250 -0.8496 0.07118 0.06649 -0.0585 1.0000 0.0112
-14.000 -0.8497 0.06865 0.06386 -0.0582 1.0000 0.0114
-13.750 -0.8474 0.06640 0.06153 -0.0578 1.0000 0.0115
-13.500 -0.8438 0.06426 0.05931 -0.0573 1.0000 0.0116
-13.250 -0.8404 0.06218 0.05713 -0.0566 1.0000 0.0120
-13.000 -0.8359 0.06031 0.05516 -0.0559 1.0000 0.0121
-12.750 -0.8391 0.05849 0.05321 -0.0551 1.0000 0.0125
-12.500 -0.8389 0.05686 0.05148 -0.0542 1.0000 0.0127
-12.250 -0.8549 0.05523 0.04969 -0.0531 1.0000 0.0129
-12.000 -0.8661 0.05374 0.04808 -0.0516 1.0000 0.0130
-11.750 -0.8818 0.05246 0.04666 -0.0495 1.0000 0.0130
-11.500 -0.7557 0.05167 0.04609 -0.0491 1.0000 0.0139
-11.250 -0.7204 0.05165 0.04615 -0.0473 1.0000 0.0145
-11.000 -0.7003 0.05111 0.04561 -0.0457 1.0000 0.0150
-10.750 -0.6863 0.05029 0.04476 -0.0444 1.0000 0.0158
-10.500 -0.6840 0.04881 0.04319 -0.0434 1.0000 0.0164
-10.250 -0.6959 0.04670 0.04093 -0.0427 1.0000 0.0167
-10.000 -0.7127 0.04473 0.03883 -0.0416 1.0000 0.0170
-9.250 -0.5792 0.04910 0.04362 -0.0323 1.0000 0.0231
-9.000 -0.5577 0.05019 0.04486 -0.0292 1.0000 0.0244
-8.750 -0.5531 0.04901 0.04367 -0.0276 1.0000 0.0265
-8.500 -0.5547 0.04703 0.04163 -0.0267 1.0000 0.0273
-8.250 -0.5372 0.04897 0.04383 -0.0220 1.0000 0.0320
-6.500 -0.4021 0.03250 0.02714 -0.0447 0.9734 0.0274
-6.250 -0.3977 0.02798 0.02246 -0.0491 0.9631 0.0205
-6.000 -0.3725 0.02441 0.01873 -0.0554 0.9578 0.0162
-5.750 -0.3825 0.02051 0.01466 -0.0564 0.9339 0.0157
-5.500 -0.3691 0.01771 0.01163 -0.0598 0.9141 0.0143
-5.250 -0.3420 0.01673 0.01052 -0.0612 0.8965 0.0134
-5.000 -0.3168 0.01553 0.00914 -0.0627 0.8742 0.0134
-4.750 -0.2933 0.01451 0.00790 -0.0633 0.8509 0.0137
-4.500 -0.2704 0.01392 0.00711 -0.0633 0.8276 0.0141
-4.250 -0.2465 0.01354 0.00654 -0.0631 0.8066 0.0154
-3.750 -0.1971 0.01305 0.00573 -0.0627 0.7691 0.0200
-3.500 -0.1717 0.01289 0.00543 -0.0625 0.7520 0.0243
-3.250 -0.1591 0.01053 0.00389 -0.0627 0.7361 0.3004
-3.000 -0.1310 0.01072 0.00407 -0.0630 0.7211 0.3226
-2.500 -0.0753 0.01103 0.00429 -0.0633 0.6924 0.3379
-2.250 -0.0480 0.01097 0.00419 -0.0634 0.6791 0.3394
-2.000 -0.0204 0.01094 0.00411 -0.0635 0.6666 0.3408
-1.750 0.0071 0.01092 0.00404 -0.0636 0.6543 0.3422
-1.250 0.0624 0.01089 0.00390 -0.0638 0.6295 0.3452
-1.000 0.0902 0.01088 0.00384 -0.0640 0.6181 0.3467
-0.750 0.1179 0.01089 0.00379 -0.0641 0.6073 0.3482
-0.500 0.1459 0.01090 0.00375 -0.0642 0.5960 0.3495
-0.250 0.1734 0.01082 0.00366 -0.0644 0.5851 0.3518
0.000 0.2009 0.01079 0.00363 -0.0645 0.5744 0.3539
0.250 0.2287 0.01079 0.00362 -0.0646 0.5636 0.3561
0.500 0.2566 0.01080 0.00362 -0.0648 0.5536 0.3583
0.750 0.2842 0.01085 0.00362 -0.0649 0.5440 0.3607
1.000 0.3124 0.01087 0.00363 -0.0651 0.5339 0.3631
1.250 0.3402 0.01091 0.00364 -0.0652 0.5243 0.3654
1.500 0.3676 0.01089 0.00365 -0.0653 0.5145 0.3686
1.750 0.3956 0.01090 0.00369 -0.0655 0.5050 0.3717
2.000 0.4229 0.01099 0.00375 -0.0656 0.4963 0.3748
2.250 0.4511 0.01103 0.00380 -0.0657 0.4872 0.3781
2.500 0.4786 0.01110 0.00385 -0.0658 0.4790 0.3815
2.750 0.5064 0.01110 0.00392 -0.0660 0.4700 0.3854
3.000 0.5338 0.01119 0.00402 -0.0660 0.4618 0.3895
3.250 0.5615 0.01127 0.00411 -0.0661 0.4534 0.3936
3.500 0.5889 0.01136 0.00421 -0.0662 0.4460 0.3978
3.750 0.6165 0.01141 0.00432 -0.0663 0.4381 0.4022
4.000 0.6436 0.01154 0.00445 -0.0663 0.4308 0.4067
4.250 0.6711 0.01163 0.00456 -0.0664 0.4225 0.4109
4.500 0.6978 0.01172 0.00469 -0.0663 0.4143 0.4157
4.750 0.7249 0.01180 0.00483 -0.0663 0.4058 0.4206
5.000 0.7515 0.01195 0.00497 -0.0662 0.3978 0.4254
5.250 0.7783 0.01203 0.00511 -0.0662 0.3896 0.4303
5.500 0.8048 0.01216 0.00529 -0.0661 0.3823 0.4355
5.750 0.8314 0.01229 0.00545 -0.0660 0.3745 0.4408
6.000 0.8574 0.01242 0.00563 -0.0658 0.3668 0.4459
6.250 0.8836 0.01254 0.00582 -0.0656 0.3586 0.4516
6.500 0.9093 0.01272 0.00601 -0.0653 0.3514 0.4572
6.750 0.9353 0.01283 0.00621 -0.0652 0.3435 0.4629
7.000 0.9604 0.01301 0.00644 -0.0648 0.3359 0.4693
7.250 0.9856 0.01316 0.00665 -0.0645 0.3272 0.4756
7.500 1.0104 0.01333 0.00690 -0.0641 0.3190 0.4822
7.750 1.0343 0.01355 0.00714 -0.0635 0.3096 0.4891
8.000 1.0585 0.01372 0.00740 -0.0630 0.2990 0.4958
8.250 1.0814 0.01396 0.00768 -0.0623 0.2874 0.5029
8.500 1.1033 0.01422 0.00798 -0.0615 0.2734 0.5097
8.750 1.1240 0.01453 0.00831 -0.0604 0.2557 0.5171
9.000 1.1397 0.01499 0.00869 -0.0586 0.2316 0.5240
9.250 1.1513 0.01560 0.00920 -0.0562 0.2011 0.5311
9.750 1.1709 0.01722 0.01063 -0.0511 0.1511 0.5455
10.250 1.1906 0.01889 0.01222 -0.0464 0.1170 0.5616
10.500 1.2002 0.01976 0.01307 -0.0442 0.1042 0.5703
11.000 1.2190 0.02154 0.01491 -0.0400 0.0842 0.5885
11.250 1.2274 0.02253 0.01595 -0.0380 0.0763 0.5987
11.500 1.2331 0.02373 0.01717 -0.0360 0.0691 0.6087
11.750 1.2418 0.02480 0.01832 -0.0344 0.0633 0.6202
12.000 1.2446 0.02632 0.01989 -0.0325 0.0574 0.6314
12.250 1.2531 0.02754 0.02123 -0.0312 0.0529 0.6434
12.500 1.2540 0.02940 0.02313 -0.0297 0.0480 0.6554
12.750 1.2610 0.03092 0.02476 -0.0288 0.0442 0.6686
13.000 1.2620 0.03300 0.02691 -0.0279 0.0403 0.6820
13.250 1.2646 0.03507 0.02911 -0.0272 0.0371 0.6967
13.500 1.2664 0.03729 0.03144 -0.0267 0.0341 0.7128
13.750 1.2611 0.04033 0.03457 -0.0263 0.0315 0.7294
14.000 1.2651 0.04255 0.03697 -0.0262 0.0293 0.7503
14.250 1.2642 0.04532 0.03984 -0.0262 0.0266 0.7743
14.500 1.2590 0.04861 0.04331 -0.0263 0.0248 0.8043
14.750 1.2531 0.05164 0.04663 -0.0259 0.0241 0.8613
15.000 1.2492 0.05437 0.04958 -0.0256 0.0226 1.0000
15.250 1.2453 0.05807 0.05333 -0.0266 0.0212 1.0000
15.500 1.2374 0.06243 0.05774 -0.0278 0.0198 1.0000
15.750 1.2380 0.06576 0.06117 -0.0289 0.0188 1.0000
16.000 1.2361 0.06952 0.06500 -0.0302 0.0176 1.0000
16.250 1.2302 0.07393 0.06947 -0.0317 0.0167 1.0000
16.500 1.2209 0.07891 0.07451 -0.0336 0.0158 1.0000
16.750 1.2222 0.08247 0.07816 -0.0350 0.0148 1.0000
17.000 1.2186 0.08683 0.08261 -0.0368 0.0141 1.0000
17.250 1.2148 0.09126 0.08711 -0.0387 0.0133 1.0000
17.500 1.2069 0.09643 0.09235 -0.0410 0.0128 1.0000
17.750 1.1996 0.10158 0.09759 -0.0433 0.0122 1.0000
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