NREL's S819 Airfoil (s819-nr) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: NREL's S819 Airfoil (s819-nr) Reynolds number: 1,000,000 Max Cl/Cd: 84.13 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s819-nr-1000000-n5.txt Download as CSV file: xf-s819-nr-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-17.500 -0.7546 0.11660 0.11383 -0.0458 1.0000 0.0049
-17.250 -0.7666 0.11183 0.10898 -0.0478 1.0000 0.0049
-17.000 -0.7816 0.10681 0.10385 -0.0498 1.0000 0.0049
-16.750 -0.7938 0.10233 0.09927 -0.0515 1.0000 0.0049
-16.500 -0.8059 0.09803 0.09488 -0.0529 1.0000 0.0049
-16.250 -0.8176 0.09397 0.09072 -0.0542 1.0000 0.0049
-16.000 -0.8293 0.08999 0.08664 -0.0552 1.0000 0.0049
-15.750 -0.8395 0.08636 0.08291 -0.0560 1.0000 0.0049
-15.500 -0.8496 0.08285 0.07930 -0.0566 1.0000 0.0049
-15.250 -0.8580 0.07968 0.07603 -0.0570 1.0000 0.0049
-15.000 -0.8643 0.07677 0.07304 -0.0572 1.0000 0.0049
-14.750 -0.8715 0.07380 0.06998 -0.0572 1.0000 0.0049
-14.500 -0.8772 0.07095 0.06703 -0.0571 1.0000 0.0049
-14.250 -0.8803 0.06845 0.06445 -0.0568 1.0000 0.0049
-14.000 -0.8839 0.06580 0.06170 -0.0562 1.0000 0.0049
-13.750 -0.8848 0.06356 0.05938 -0.0557 1.0000 0.0049
-13.500 -0.8844 0.06136 0.05710 -0.0549 1.0000 0.0049
-13.250 -0.8810 0.05916 0.05482 -0.0541 1.0000 0.0049
-13.000 -0.8761 0.05725 0.05284 -0.0532 1.0000 0.0049
-12.750 -0.8678 0.05532 0.05083 -0.0521 1.0000 0.0049
-12.500 -0.8478 0.05328 0.04872 -0.0531 0.9994 0.0049
-12.250 -0.8235 0.05139 0.04677 -0.0539 0.9987 0.0049
-12.000 -0.7993 0.04974 0.04504 -0.0546 0.9980 0.0050
-10.500 -0.5811 0.05063 0.04608 -0.0472 0.9943 0.0044
-10.250 -0.5529 0.05108 0.04655 -0.0462 0.9927 0.0042
-10.000 -0.5211 0.05232 0.04784 -0.0446 0.9911 0.0038
-9.750 -0.4860 0.05446 0.05003 -0.0425 0.9893 0.0033
-9.500 -0.4671 0.05350 0.04907 -0.0432 0.9873 0.0032
-9.250 -0.4519 0.05150 0.04706 -0.0450 0.9853 0.0032
-9.000 -0.4360 0.04928 0.04481 -0.0474 0.9834 0.0031
-8.750 -0.4375 0.04629 0.04178 -0.0481 0.9785 0.0032
-8.500 -0.4233 0.04397 0.03944 -0.0503 0.9742 0.0031
-8.250 -0.4197 0.04023 0.03564 -0.0536 0.9697 0.0031
-8.000 -0.4185 0.03614 0.03146 -0.0571 0.9611 0.0031
-7.750 -0.4185 0.03157 0.02677 -0.0614 0.9475 0.0031
-7.500 -0.4090 0.02676 0.02172 -0.0679 0.8972 0.0031
-7.250 -0.4229 0.02359 0.01815 -0.0670 0.8286 0.0031
-7.000 -0.4279 0.02154 0.01590 -0.0655 0.7942 0.0031
-6.750 -0.4488 0.01838 0.01249 -0.0635 0.7665 0.0032
-6.500 -0.4593 0.01635 0.01026 -0.0618 0.7445 0.0032
-6.250 -0.4507 0.01524 0.00898 -0.0609 0.7264 0.0033
-6.000 -0.4340 0.01455 0.00816 -0.0603 0.7104 0.0033
-5.750 -0.4144 0.01399 0.00748 -0.0599 0.6956 0.0034
-5.500 -0.3924 0.01356 0.00696 -0.0596 0.6811 0.0036
-5.250 -0.3694 0.01317 0.00647 -0.0595 0.6671 0.0037
-5.000 -0.3452 0.01285 0.00607 -0.0594 0.6532 0.0040
-4.750 -0.3204 0.01257 0.00571 -0.0594 0.6394 0.0044
-4.250 -0.2688 0.01210 0.00510 -0.0595 0.6134 0.0050
-4.000 -0.2425 0.01188 0.00481 -0.0597 0.6017 0.0055
-3.750 -0.2158 0.01172 0.00459 -0.0598 0.5907 0.0060
-3.500 -0.1887 0.01159 0.00442 -0.0600 0.5790 0.0072
-3.250 -0.1613 0.01144 0.00422 -0.0603 0.5693 0.0089
-3.000 -0.1339 0.01131 0.00404 -0.0605 0.5597 0.0128
-2.750 -0.1146 0.00915 0.00261 -0.0614 0.5505 0.2740
-2.500 -0.0864 0.00905 0.00256 -0.0617 0.5403 0.2905
-2.250 -0.0580 0.00899 0.00250 -0.0621 0.5301 0.2979
-2.000 -0.0292 0.00897 0.00246 -0.0625 0.5216 0.3017
-1.500 0.0284 0.00897 0.00239 -0.0631 0.5044 0.3036
-1.250 0.0570 0.00899 0.00236 -0.0634 0.4953 0.3044
-1.000 0.0859 0.00899 0.00234 -0.0638 0.4862 0.3051
-0.750 0.1145 0.00902 0.00232 -0.0641 0.4775 0.3058
-0.500 0.1434 0.00901 0.00230 -0.0644 0.4693 0.3072
-0.250 0.1721 0.00902 0.00229 -0.0648 0.4619 0.3090
0.000 0.2009 0.00902 0.00228 -0.0651 0.4542 0.3106
0.250 0.2296 0.00904 0.00229 -0.0654 0.4466 0.3123
0.500 0.2583 0.00906 0.00230 -0.0657 0.4383 0.3140
0.750 0.2869 0.00909 0.00231 -0.0660 0.4305 0.3156
1.000 0.3157 0.00912 0.00233 -0.0663 0.4231 0.3173
1.250 0.3441 0.00917 0.00237 -0.0666 0.4162 0.3189
1.500 0.3730 0.00920 0.00240 -0.0669 0.4098 0.3202
1.750 0.4014 0.00924 0.00243 -0.0672 0.4029 0.3227
2.000 0.4301 0.00926 0.00248 -0.0675 0.3966 0.3252
2.250 0.4585 0.00931 0.00253 -0.0677 0.3891 0.3278
2.500 0.4869 0.00936 0.00258 -0.0679 0.3831 0.3305
2.750 0.5155 0.00941 0.00264 -0.0682 0.3772 0.3329
3.000 0.5436 0.00948 0.00272 -0.0684 0.3713 0.3350
3.250 0.5721 0.00952 0.00279 -0.0686 0.3660 0.3382
3.500 0.6003 0.00958 0.00287 -0.0688 0.3592 0.3416
3.750 0.6281 0.00967 0.00296 -0.0690 0.3511 0.3450
4.000 0.6557 0.00977 0.00306 -0.0690 0.3417 0.3482
4.250 0.6834 0.00987 0.00316 -0.0692 0.3337 0.3516
4.500 0.7107 0.00998 0.00327 -0.0692 0.3244 0.3558
4.750 0.7385 0.01007 0.00339 -0.0693 0.3176 0.3598
5.000 0.7657 0.01019 0.00351 -0.0693 0.3099 0.3631
5.250 0.7930 0.01031 0.00365 -0.0694 0.3022 0.3662
5.750 0.8468 0.01057 0.00394 -0.0693 0.2845 0.3743
6.000 0.8732 0.01074 0.00410 -0.0692 0.2762 0.3779
6.250 0.8997 0.01088 0.00426 -0.0691 0.2665 0.3813
6.500 0.9257 0.01106 0.00445 -0.0689 0.2555 0.3856
6.750 0.9507 0.01130 0.00466 -0.0686 0.2408 0.3899
7.000 0.9747 0.01159 0.00490 -0.0681 0.2232 0.3937
7.250 0.9962 0.01203 0.00524 -0.0672 0.1973 0.3975
7.500 1.0163 0.01253 0.00564 -0.0661 0.1718 0.4020
7.750 1.0363 0.01301 0.00604 -0.0650 0.1498 0.4064
8.000 1.0563 0.01348 0.00644 -0.0639 0.1323 0.4103
8.250 1.0756 0.01395 0.00686 -0.0627 0.1146 0.4148
8.500 1.0931 0.01447 0.00731 -0.0612 0.0970 0.4201
8.750 1.1100 0.01489 0.00770 -0.0595 0.0856 0.4248
9.000 1.1261 0.01531 0.00811 -0.0577 0.0761 0.4304
9.250 1.1410 0.01583 0.00860 -0.0557 0.0653 0.4359
9.500 1.1562 0.01636 0.00911 -0.0539 0.0570 0.4410
9.750 1.1728 0.01683 0.00961 -0.0523 0.0513 0.4462
10.000 1.1858 0.01747 0.01022 -0.0503 0.0423 0.4517
10.250 1.2009 0.01801 0.01079 -0.0487 0.0386 0.4569
10.500 1.2138 0.01867 0.01145 -0.0468 0.0328 0.4621
10.750 1.2253 0.01940 0.01218 -0.0448 0.0270 0.4679
11.000 1.2370 0.02014 0.01294 -0.0429 0.0231 0.4732
11.250 1.2497 0.02084 0.01370 -0.0413 0.0212 0.4791
11.500 1.2597 0.02172 0.01460 -0.0394 0.0180 0.4855
11.750 1.2686 0.02270 0.01563 -0.0376 0.0155 0.4909
12.000 1.2781 0.02370 0.01669 -0.0360 0.0135 0.4988
12.250 1.2864 0.02482 0.01787 -0.0345 0.0119 0.5072
12.500 1.2953 0.02598 0.01909 -0.0332 0.0109 0.5150
12.750 1.3027 0.02731 0.02049 -0.0319 0.0099 0.5246
13.000 1.3100 0.02872 0.02199 -0.0309 0.0091 0.5355
13.250 1.3149 0.03039 0.02374 -0.0299 0.0078 0.5435
13.500 1.3206 0.03210 0.02552 -0.0291 0.0073 0.5524
13.750 1.3262 0.03392 0.02743 -0.0285 0.0067 0.5606
14.000 1.3316 0.03582 0.02942 -0.0280 0.0064 0.5687
14.250 1.3329 0.03820 0.03189 -0.0277 0.0054 0.5776
14.500 1.3362 0.04048 0.03425 -0.0275 0.0051 0.5854
14.750 1.3397 0.04282 0.03670 -0.0275 0.0051 0.5949
15.000 1.3416 0.04542 0.03939 -0.0277 0.0047 0.6044
15.250 1.3421 0.04826 0.04234 -0.0280 0.0043 0.6134
15.500 1.3417 0.05128 0.04545 -0.0285 0.0040 0.6220
15.750 1.3401 0.05454 0.04881 -0.0291 0.0036 0.6327
16.000 1.3394 0.05781 0.05219 -0.0299 0.0034 0.6417
16.250 1.3382 0.06124 0.05573 -0.0308 0.0032 0.6536
16.500 1.3356 0.06490 0.05950 -0.0319 0.0029 0.6662
16.750 1.3316 0.06887 0.06360 -0.0332 0.0026 0.6786
17.000 1.3287 0.07282 0.06766 -0.0345 0.0025 0.6905
17.250 1.3245 0.07700 0.07196 -0.0361 0.0023 0.7038
17.500 1.3211 0.08117 0.07626 -0.0377 0.0022 0.7180
17.750 1.3165 0.08560 0.08083 -0.0395 0.0020 0.7339
18.000 1.3131 0.08994 0.08531 -0.0414 0.0020 0.7535
18.250 1.3074 0.09469 0.09022 -0.0435 0.0018 0.7777
18.500 1.3018 0.09948 0.09519 -0.0457 0.0017 0.8120
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