NREL's S812 Airfoil (s812-nr) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: NREL's S812 Airfoil (s812-nr) Reynolds number: 1,000,000 Max Cl/Cd: 116.54 at α=6.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s812-nr-1000000.txt Download as CSV file: xf-s812-nr-1000000.csv |
XFOIL Version 6.96
Calculated polar for: NREL's S812 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
------ -------- --------- --------- -------- -------- --------
-14.250 -0.6881 0.06981 0.06728 -0.0752 0.9957 0.0076
-14.000 -0.7078 0.06469 0.06202 -0.0766 0.9897 0.0074
-13.750 -0.7650 0.05030 0.04687 -0.0737 0.9877 0.0074
-13.500 -0.7575 0.04473 0.04067 -0.0721 0.9843 0.0077
-13.250 -0.7318 0.04297 0.03860 -0.0719 0.9755 0.0082
-13.000 -0.6544 0.04004 0.03557 -0.0878 0.9391 0.0086
-12.750 -0.6182 0.03875 0.03356 -0.0939 0.7774 0.0089
-12.500 -0.6006 0.03832 0.03291 -0.0925 0.7483 0.0091
-12.250 -0.5909 0.03733 0.03182 -0.0921 0.7312 0.0095
-12.000 -0.5690 0.03699 0.03133 -0.0912 0.7197 0.0099
-11.750 -0.5476 0.03674 0.03095 -0.0902 0.7108 0.0102
-11.500 -0.5294 0.03623 0.03034 -0.0897 0.7032 0.0104
-11.250 -0.5073 0.03635 0.03034 -0.0882 0.6970 0.0109
-11.000 -0.4895 0.03597 0.02993 -0.0874 0.6919 0.0112
-10.750 -0.4736 0.03540 0.02935 -0.0868 0.6872 0.0115
-10.500 -0.4589 0.03451 0.02842 -0.0866 0.6828 0.0121
-10.250 -0.4426 0.03395 0.02783 -0.0860 0.6792 0.0124
-10.000 -0.4265 0.03330 0.02716 -0.0855 0.6760 0.0129
-9.750 -0.4105 0.03267 0.02648 -0.0849 0.6728 0.0135
-9.500 -0.3946 0.03202 0.02578 -0.0844 0.6697 0.0139
-9.250 -0.3835 0.03131 0.02502 -0.0831 0.6667 0.0148
-9.000 -0.3737 0.03040 0.02411 -0.0820 0.6642 0.0154
-8.750 -0.3613 0.02954 0.02325 -0.0813 0.6621 0.0158
-8.500 -0.3508 0.02858 0.02227 -0.0803 0.6598 0.0163
-8.250 -0.3386 0.02771 0.02138 -0.0796 0.6574 0.0171
-8.000 -0.3290 0.02676 0.02040 -0.0785 0.6551 0.0175
-7.750 -0.3201 0.02581 0.01940 -0.0773 0.6527 0.0181
-7.500 -0.3051 0.02518 0.01873 -0.0766 0.6500 0.0187
-7.250 -0.3001 0.02401 0.01754 -0.0751 0.6485 0.0188
-7.000 -0.3109 0.02202 0.01550 -0.0722 0.6469 0.0199
-6.750 -0.3085 0.02072 0.01417 -0.0703 0.6452 0.0204
-6.500 -0.3041 0.01953 0.01296 -0.0686 0.6435 0.0212
-6.250 -0.2987 0.01840 0.01180 -0.0669 0.6418 0.0218
-6.000 -0.2932 0.01730 0.01066 -0.0651 0.6401 0.0223
-5.750 -0.2884 0.01623 0.00955 -0.0631 0.6383 0.0230
-5.500 -0.2853 0.01534 0.00861 -0.0607 0.6365 0.0237
-5.250 -0.2756 0.01447 0.00767 -0.0597 0.6343 0.0243
-5.000 -0.2614 0.01351 0.00664 -0.0595 0.6330 0.0253
-4.750 -0.2423 0.01293 0.00602 -0.0592 0.6317 0.0271
-4.500 -0.2198 0.01253 0.00560 -0.0592 0.6303 0.0290
-4.250 -0.1954 0.01223 0.00528 -0.0594 0.6288 0.0313
-4.000 -0.1712 0.01186 0.00493 -0.0596 0.6274 0.0419
-3.750 -0.1674 0.00857 0.00283 -0.0596 0.6260 0.3941
-3.500 -0.1403 0.00799 0.00253 -0.0604 0.6247 0.4651
-3.250 -0.1109 0.00794 0.00248 -0.0611 0.6234 0.4820
-3.000 -0.0813 0.00792 0.00247 -0.0618 0.6220 0.4936
-2.750 -0.0516 0.00795 0.00249 -0.0626 0.6206 0.5018
-2.500 -0.0215 0.00805 0.00255 -0.0634 0.6188 0.5082
-2.250 0.0083 0.00806 0.00254 -0.0641 0.6178 0.5124
-2.000 0.0379 0.00806 0.00256 -0.0648 0.6167 0.5166
-1.750 0.0679 0.00812 0.00262 -0.0655 0.6156 0.5218
-1.500 0.0979 0.00819 0.00265 -0.0662 0.6144 0.5250
-1.250 0.1275 0.00816 0.00263 -0.0669 0.6133 0.5278
-1.000 0.1572 0.00816 0.00264 -0.0676 0.6121 0.5297
-0.750 0.1869 0.00817 0.00266 -0.0683 0.6109 0.5314
-0.500 0.2167 0.00820 0.00267 -0.0690 0.6097 0.5333
-0.250 0.2465 0.00822 0.00269 -0.0697 0.6085 0.5351
0.000 0.2763 0.00826 0.00271 -0.0705 0.6072 0.5369
0.250 0.3062 0.00831 0.00274 -0.0712 0.6059 0.5386
0.500 0.3362 0.00838 0.00279 -0.0720 0.6046 0.5402
0.750 0.3661 0.00844 0.00287 -0.0728 0.6031 0.5424
1.000 0.3956 0.00845 0.00291 -0.0734 0.6023 0.5442
1.250 0.4251 0.00847 0.00296 -0.0741 0.6014 0.5459
1.500 0.4547 0.00849 0.00302 -0.0748 0.6003 0.5476
1.750 0.4842 0.00852 0.00307 -0.0754 0.5991 0.5493
2.000 0.5138 0.00856 0.00313 -0.0761 0.5979 0.5510
2.250 0.5434 0.00860 0.00319 -0.0768 0.5966 0.5525
2.500 0.5730 0.00865 0.00325 -0.0775 0.5953 0.5538
2.750 0.6025 0.00866 0.00328 -0.0781 0.5939 0.5555
3.000 0.6318 0.00864 0.00331 -0.0787 0.5920 0.5575
3.250 0.6610 0.00870 0.00337 -0.0793 0.5888 0.5592
3.500 0.6891 0.00867 0.00340 -0.0796 0.5855 0.5609
3.750 0.7170 0.00860 0.00338 -0.0799 0.5812 0.5626
4.000 0.7452 0.00856 0.00336 -0.0802 0.5772 0.5643
4.250 0.7739 0.00863 0.00341 -0.0807 0.5727 0.5659
4.500 0.8015 0.00857 0.00342 -0.0809 0.5688 0.5673
4.750 0.8293 0.00854 0.00343 -0.0812 0.5641 0.5685
5.000 0.8572 0.00856 0.00345 -0.0814 0.5596 0.5698
5.250 0.8848 0.00851 0.00348 -0.0817 0.5544 0.5718
5.500 0.9116 0.00847 0.00349 -0.0817 0.5458 0.5735
5.750 0.9389 0.00849 0.00356 -0.0819 0.5383 0.5750
6.000 0.9657 0.00853 0.00364 -0.0820 0.5302 0.5766
6.250 0.9922 0.00859 0.00373 -0.0820 0.5181 0.5783
6.500 1.0162 0.00872 0.00383 -0.0816 0.4985 0.5800
6.750 1.0329 0.00915 0.00407 -0.0798 0.4489 0.5815
7.000 1.0394 0.01005 0.00463 -0.0763 0.3815 0.5827
7.250 1.0423 0.01103 0.00528 -0.0722 0.3173 0.5837
7.500 1.0402 0.01189 0.00587 -0.0671 0.2641 0.5846
7.750 1.0394 0.01269 0.00648 -0.0624 0.2212 0.5864
8.250 1.0449 0.01433 0.00785 -0.0549 0.1591 0.5896
8.500 1.0498 0.01515 0.00857 -0.0517 0.1353 0.5911
8.750 1.0546 0.01602 0.00936 -0.0487 0.1162 0.5925
9.000 1.0603 0.01692 0.01021 -0.0460 0.0995 0.5941
9.250 1.0647 0.01796 0.01119 -0.0434 0.0837 0.5955
9.500 1.0709 0.01901 0.01220 -0.0412 0.0721 0.5969
9.750 1.0773 0.02015 0.01331 -0.0393 0.0617 0.5981
10.000 1.0841 0.02137 0.01450 -0.0376 0.0531 0.5993
10.250 1.0931 0.02252 0.01565 -0.0363 0.0473 0.6009
10.500 1.1029 0.02366 0.01682 -0.0351 0.0424 0.6029
10.750 1.1126 0.02485 0.01804 -0.0341 0.0385 0.6048
11.000 1.1220 0.02610 0.01930 -0.0330 0.0347 0.6064
11.250 1.1335 0.02723 0.02047 -0.0323 0.0322 0.6080
11.500 1.1429 0.02853 0.02179 -0.0313 0.0295 0.6095
11.750 1.1531 0.02979 0.02308 -0.0305 0.0269 0.6110
12.000 1.1641 0.03101 0.02433 -0.0298 0.0247 0.6127
12.250 1.1720 0.03248 0.02580 -0.0290 0.0217 0.6140
12.500 1.1824 0.03379 0.02713 -0.0283 0.0188 0.6152
12.750 1.1889 0.03540 0.02874 -0.0275 0.0145 0.6172
13.000 1.1955 0.03704 0.03040 -0.0267 0.0116 0.6190
13.250 1.2010 0.03883 0.03221 -0.0259 0.0095 0.6206
13.500 1.2087 0.04046 0.03389 -0.0253 0.0083 0.6223
13.750 1.2140 0.04236 0.03583 -0.0247 0.0074 0.6240
14.000 1.2216 0.04410 0.03765 -0.0242 0.0072 0.6258
14.250 1.2310 0.04573 0.03934 -0.0239 0.0069 0.6276
14.500 1.2390 0.04750 0.04118 -0.0236 0.0066 0.6293
14.750 1.2464 0.04938 0.04311 -0.0233 0.0063 0.6306
15.000 1.2543 0.05122 0.04504 -0.0231 0.0062 0.6329
15.250 1.2603 0.05333 0.04723 -0.0230 0.0059 0.6350
15.500 1.2673 0.05535 0.04933 -0.0229 0.0058 0.6371
15.750 1.2707 0.05782 0.05188 -0.0229 0.0056 0.6391
16.000 1.2724 0.06052 0.05466 -0.0229 0.0054 0.6410
16.250 1.2714 0.06362 0.05786 -0.0230 0.0052 0.6428
16.500 1.2705 0.06680 0.06115 -0.0232 0.0051 0.6445
16.750 1.2739 0.06954 0.06398 -0.0235 0.0050 0.6463
17.000 1.2750 0.07262 0.06716 -0.0241 0.0050 0.6488
17.250 1.2785 0.07545 0.07010 -0.0246 0.0049 0.6514
17.500 1.2791 0.07876 0.07351 -0.0254 0.0048 0.6539
17.750 1.2802 0.08205 0.07690 -0.0262 0.0048 0.6566
18.000 1.2793 0.08565 0.08061 -0.0271 0.0047 0.6590
18.250 1.2784 0.08936 0.08442 -0.0283 0.0046 0.6613
18.500 1.2778 0.09310 0.08828 -0.0296 0.0046 0.6643
18.750 1.2744 0.09736 0.09266 -0.0311 0.0045 0.6671
19.000 1.2729 0.10139 0.09680 -0.0326 0.0044 0.6701
19.250 1.2689 0.10586 0.10138 -0.0345 0.0043 0.6730
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