NREL's S812 Airfoil (s812-nr) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: NREL's S812 Airfoil (s812-nr) Reynolds number: 500,000 Max Cl/Cd: 87.37 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s812-nr-500000-n5.txt Download as CSV file: xf-s812-nr-500000-n5.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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.000 -0.5253 0.12038 0.11799 -0.0576 1.0000 0.0061
-15.750 -0.5868 0.10406 0.10149 -0.0645 1.0000 0.0059
-15.500 -0.6138 0.09668 0.09401 -0.0670 1.0000 0.0060
-15.250 -0.6506 0.08828 0.08544 -0.0691 0.9999 0.0059
-14.750 -0.6903 0.07574 0.07257 -0.0734 0.9907 0.0060
-14.500 -0.7108 0.06920 0.06580 -0.0753 0.9858 0.0061
-14.250 -0.7170 0.06459 0.06101 -0.0772 0.9793 0.0062
-14.000 -0.7244 0.05841 0.05452 -0.0790 0.9709 0.0064
-13.750 -0.7215 0.04958 0.04456 -0.0735 0.9664 0.0076
-13.500 -0.6312 0.04636 0.04093 -0.0902 0.8904 0.0081
-13.250 -0.6112 0.04550 0.03948 -0.0914 0.7786 0.0083
-13.000 -0.5985 0.04474 0.03853 -0.0904 0.7524 0.0085
-12.750 -0.5839 0.04397 0.03761 -0.0898 0.7366 0.0087
-12.500 -0.5672 0.04337 0.03688 -0.0891 0.7249 0.0089
-12.250 -0.5517 0.04262 0.03602 -0.0887 0.7157 0.0093
-12.000 -0.5330 0.04219 0.03547 -0.0880 0.7085 0.0097
-11.750 -0.5145 0.04179 0.03494 -0.0872 0.7018 0.0102
-11.500 -0.4973 0.04124 0.03427 -0.0866 0.6963 0.0106
-11.250 -0.4810 0.04065 0.03364 -0.0860 0.6914 0.0110
-11.000 -0.4653 0.03993 0.03288 -0.0856 0.6868 0.0113
-10.750 -0.4499 0.03923 0.03215 -0.0851 0.6826 0.0117
-10.500 -0.4342 0.03851 0.03139 -0.0848 0.6790 0.0122
-10.250 -0.4185 0.03786 0.03070 -0.0842 0.6752 0.0126
-10.000 -0.4035 0.03718 0.02996 -0.0835 0.6716 0.0130
-9.750 -0.3894 0.03646 0.02916 -0.0828 0.6683 0.0136
-9.500 -0.3750 0.03571 0.02834 -0.0822 0.6654 0.0141
-9.250 -0.3635 0.03479 0.02741 -0.0814 0.6629 0.0146
-9.000 -0.3526 0.03381 0.02642 -0.0806 0.6604 0.0153
-8.750 -0.3404 0.03288 0.02548 -0.0800 0.6579 0.0157
-8.500 -0.3295 0.03189 0.02445 -0.0792 0.6555 0.0164
-8.250 -0.3186 0.03092 0.02345 -0.0784 0.6532 0.0171
-8.000 -0.3095 0.02987 0.02235 -0.0774 0.6512 0.0175
-7.750 -0.3010 0.02879 0.02122 -0.0764 0.6493 0.0180
-7.500 -0.2922 0.02776 0.02015 -0.0753 0.6475 0.0185
-7.250 -0.2849 0.02665 0.01902 -0.0741 0.6456 0.0190
-7.000 -0.2830 0.02526 0.01760 -0.0725 0.6435 0.0199
-6.750 -0.2778 0.02408 0.01639 -0.0710 0.6415 0.0206
-6.500 -0.2713 0.02297 0.01525 -0.0696 0.6395 0.0213
-6.250 -0.2648 0.02190 0.01414 -0.0681 0.6376 0.0220
-6.000 -0.2579 0.02086 0.01304 -0.0666 0.6359 0.0226
-5.500 -0.2433 0.01884 0.01094 -0.0635 0.6328 0.0239
-5.250 -0.2367 0.01786 0.00993 -0.0617 0.6313 0.0249
-5.000 -0.2368 0.01683 0.00887 -0.0590 0.6297 0.0266
-4.750 -0.2259 0.01590 0.00791 -0.0583 0.6281 0.0283
-4.500 -0.2089 0.01519 0.00715 -0.0582 0.6265 0.0307
-4.250 -0.1896 0.01467 0.00661 -0.0580 0.6250 0.0373
-4.000 -0.1698 0.01411 0.00609 -0.0579 0.6235 0.0613
-3.750 -0.1719 0.01097 0.00381 -0.0572 0.6220 0.3545
-3.500 -0.1481 0.01012 0.00334 -0.0579 0.6205 0.4507
-3.250 -0.1196 0.01002 0.00328 -0.0586 0.6190 0.4735
-3.000 -0.0904 0.00999 0.00324 -0.0592 0.6178 0.4843
-2.750 -0.0611 0.00999 0.00323 -0.0599 0.6165 0.4954
-2.500 -0.0318 0.01001 0.00328 -0.0606 0.6153 0.5037
-2.250 -0.0023 0.01005 0.00328 -0.0612 0.6139 0.5116
-2.000 0.0270 0.01009 0.00334 -0.0618 0.6126 0.5163
-1.750 0.0564 0.01009 0.00331 -0.0625 0.6114 0.5182
-1.500 0.0857 0.01009 0.00328 -0.0632 0.6101 0.5202
-1.250 0.1151 0.01010 0.00325 -0.0638 0.6087 0.5223
-1.000 0.1445 0.01011 0.00322 -0.0645 0.6073 0.5243
-0.750 0.1739 0.01011 0.00321 -0.0651 0.6061 0.5260
-0.500 0.2032 0.01014 0.00323 -0.0658 0.6049 0.5276
-0.250 0.2327 0.01017 0.00326 -0.0664 0.6038 0.5293
0.000 0.2621 0.01021 0.00329 -0.0671 0.6027 0.5310
0.250 0.2914 0.01023 0.00333 -0.0678 0.6017 0.5328
0.500 0.3207 0.01025 0.00337 -0.0684 0.6005 0.5347
0.750 0.3500 0.01027 0.00340 -0.0690 0.5992 0.5365
1.000 0.3793 0.01030 0.00343 -0.0697 0.5977 0.5383
1.250 0.4085 0.01033 0.00347 -0.0703 0.5963 0.5399
1.500 0.4376 0.01035 0.00354 -0.0709 0.5951 0.5414
1.750 0.4668 0.01039 0.00362 -0.0715 0.5939 0.5431
2.000 0.4960 0.01044 0.00370 -0.0721 0.5927 0.5449
2.250 0.5252 0.01048 0.00377 -0.0727 0.5915 0.5467
2.500 0.5544 0.01054 0.00385 -0.0734 0.5902 0.5486
2.750 0.5839 0.01061 0.00393 -0.0740 0.5890 0.5505
3.000 0.6134 0.01069 0.00403 -0.0747 0.5878 0.5522
3.250 0.6420 0.01074 0.00412 -0.0752 0.5864 0.5538
3.500 0.6705 0.01077 0.00424 -0.0757 0.5848 0.5552
3.750 0.6987 0.01080 0.00435 -0.0761 0.5824 0.5567
4.000 0.7265 0.01079 0.00440 -0.0764 0.5788 0.5582
4.250 0.7542 0.01076 0.00440 -0.0766 0.5742 0.5598
4.500 0.7806 0.01074 0.00445 -0.0766 0.5679 0.5615
4.750 0.8071 0.01070 0.00446 -0.0766 0.5611 0.5634
5.000 0.8338 0.01070 0.00451 -0.0766 0.5546 0.5652
5.250 0.8600 0.01070 0.00456 -0.0766 0.5464 0.5670
5.500 0.8862 0.01072 0.00462 -0.0766 0.5381 0.5685
5.750 0.9117 0.01075 0.00469 -0.0764 0.5291 0.5699
6.000 0.9357 0.01078 0.00477 -0.0759 0.5134 0.5713
6.250 0.9550 0.01093 0.00486 -0.0745 0.4791 0.5727
6.500 0.9624 0.01153 0.00518 -0.0711 0.4190 0.5742
6.750 0.9657 0.01237 0.00577 -0.0671 0.3656 0.5757
7.000 0.9673 0.01311 0.00633 -0.0627 0.3234 0.5773
7.250 0.9689 0.01389 0.00695 -0.0585 0.2859 0.5789
7.500 0.9710 0.01477 0.00767 -0.0546 0.2502 0.5804
7.750 0.9734 0.01568 0.00845 -0.0510 0.2186 0.5819
8.000 0.9748 0.01668 0.00931 -0.0474 0.1887 0.5833
8.250 0.9795 0.01761 0.01016 -0.0446 0.1665 0.5845
8.500 0.9837 0.01863 0.01113 -0.0419 0.1464 0.5860
8.750 0.9882 0.01973 0.01221 -0.0395 0.1290 0.5875
9.000 0.9931 0.02093 0.01337 -0.0374 0.1125 0.5891
9.250 0.9964 0.02233 0.01472 -0.0354 0.0951 0.5906
9.500 1.0012 0.02375 0.01609 -0.0337 0.0806 0.5923
9.750 1.0092 0.02503 0.01737 -0.0325 0.0709 0.5939
10.000 1.0169 0.02639 0.01872 -0.0313 0.0618 0.5956
10.250 1.0241 0.02781 0.02011 -0.0302 0.0532 0.5971
10.500 1.0334 0.02913 0.02143 -0.0292 0.0468 0.5985
10.750 1.0428 0.03045 0.02276 -0.0284 0.0420 0.5999
11.000 1.0523 0.03177 0.02411 -0.0276 0.0375 0.6015
11.250 1.0621 0.03309 0.02548 -0.0268 0.0343 0.6031
11.500 1.0730 0.03435 0.02680 -0.0262 0.0317 0.6046
11.750 1.0824 0.03575 0.02822 -0.0255 0.0288 0.6061
12.000 1.0924 0.03711 0.02964 -0.0249 0.0262 0.6076
12.250 1.1027 0.03850 0.03107 -0.0244 0.0241 0.6093
12.500 1.1117 0.04000 0.03260 -0.0239 0.0216 0.6108
12.750 1.1218 0.04146 0.03411 -0.0235 0.0194 0.6127
13.000 1.1310 0.04301 0.03569 -0.0230 0.0172 0.6144
13.250 1.1400 0.04461 0.03733 -0.0226 0.0149 0.6159
13.500 1.1479 0.04634 0.03910 -0.0223 0.0125 0.6175
13.750 1.1561 0.04808 0.04090 -0.0220 0.0105 0.6191
14.000 1.1638 0.04991 0.04279 -0.0217 0.0095 0.6208
14.250 1.1722 0.05172 0.04467 -0.0215 0.0087 0.6225
14.500 1.1789 0.05373 0.04676 -0.0213 0.0079 0.6243
14.750 1.1848 0.05587 0.04895 -0.0212 0.0072 0.6260
15.000 1.1924 0.05788 0.05105 -0.0212 0.0070 0.6278
15.250 1.1992 0.06002 0.05328 -0.0213 0.0066 0.6296
15.500 1.2059 0.06220 0.05554 -0.0214 0.0064 0.6313
15.750 1.2112 0.06460 0.05805 -0.0216 0.0060 0.6332
16.000 1.2164 0.06705 0.06059 -0.0218 0.0057 0.6353
16.250 1.2202 0.06971 0.06335 -0.0222 0.0055 0.6375
16.500 1.2231 0.07254 0.06628 -0.0226 0.0053 0.6398
16.750 1.2233 0.07579 0.06962 -0.0232 0.0050 0.6419
17.000 1.2256 0.07887 0.07283 -0.0239 0.0050 0.6440
17.250 1.2278 0.08199 0.07606 -0.0246 0.0049 0.6460
17.500 1.2287 0.08535 0.07955 -0.0256 0.0048 0.6480
17.750 1.2289 0.08888 0.08320 -0.0266 0.0047 0.6501
18.000 1.2279 0.09267 0.08713 -0.0279 0.0046 0.6524
18.250 1.2267 0.09656 0.09114 -0.0292 0.0045 0.6547
18.500 1.2246 0.10067 0.09538 -0.0308 0.0045 0.6571
18.750 1.2217 0.10497 0.09980 -0.0325 0.0044 0.6594
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