NREL's S812 Airfoil (s812-nr) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: NREL's S812 Airfoil (s812-nr) Reynolds number: 500,000 Max Cl/Cd: 92.39 at α=7.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s812-nr-500000.txt Download as CSV file: xf-s812-nr-500000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.250 -0.5380 0.09944 0.09697 -0.0683 1.0000 0.0168
-14.000 -0.5622 0.09368 0.09113 -0.0699 1.0000 0.0165
-13.750 -0.5868 0.08856 0.08592 -0.0707 1.0000 0.0169
-13.500 -0.6097 0.08406 0.08133 -0.0709 1.0000 0.0167
-13.250 -0.6320 0.07994 0.07713 -0.0707 1.0000 0.0166
-13.000 -0.6445 0.07481 0.07185 -0.0735 0.9977 0.0170
-12.750 -0.6536 0.06973 0.06655 -0.0765 0.9906 0.0178
-12.500 -0.6650 0.06645 0.06290 -0.0791 0.9803 0.0187
-12.250 -0.6683 0.06236 0.05856 -0.0825 0.9618 0.0187
-12.000 -0.6449 0.05642 0.05214 -0.0930 0.8912 0.0188
-11.750 -0.6501 0.04916 0.04424 -0.0931 0.8084 0.0195
-11.500 -0.6464 0.04735 0.04221 -0.0916 0.7780 0.0197
-11.250 -0.6436 0.04555 0.04022 -0.0900 0.7614 0.0199
-11.000 -0.6407 0.04447 0.03907 -0.0887 0.7496 0.0205
-10.750 -0.6375 0.04295 0.03740 -0.0870 0.7409 0.0211
-10.500 -0.6314 0.04113 0.03541 -0.0853 0.7334 0.0217
-10.250 -0.4903 0.02072 0.01453 -0.0847 0.7210 0.0178
-10.000 -0.4361 0.01927 0.01287 -0.0846 0.7162 0.0181
-9.750 -0.3912 0.01881 0.01223 -0.0840 0.7120 0.0195
-9.500 -0.3896 0.03282 0.02588 -0.0883 0.7159 0.0202
-9.250 -0.3672 0.03260 0.02563 -0.0877 0.7119 0.0212
-9.000 -0.3427 0.03256 0.02557 -0.0868 0.7082 0.0220
-8.750 -0.3215 0.03240 0.02538 -0.0858 0.7046 0.0228
-8.500 -0.3029 0.03212 0.02504 -0.0848 0.7012 0.0235
-8.250 -0.2862 0.03142 0.02423 -0.0846 0.6980 0.0246
-8.000 -0.2760 0.03101 0.02384 -0.0823 0.6953 0.0257
-7.750 -0.2677 0.03003 0.02288 -0.0810 0.6926 0.0266
-7.500 -0.2595 0.02900 0.02183 -0.0798 0.6896 0.0275
-7.250 -0.2525 0.02793 0.02073 -0.0785 0.6870 0.0283
-7.000 -0.2455 0.02687 0.01962 -0.0772 0.6844 0.0294
-6.750 -0.2388 0.02580 0.01849 -0.0759 0.6820 0.0303
-6.500 -0.2305 0.02480 0.01744 -0.0747 0.6800 0.0314
-6.250 -0.2277 0.02350 0.01611 -0.0730 0.6779 0.0320
-6.000 -0.2302 0.02192 0.01449 -0.0708 0.6758 0.0327
-5.750 -0.2309 0.02045 0.01298 -0.0686 0.6736 0.0341
-5.500 -0.2270 0.01925 0.01173 -0.0668 0.6716 0.0353
-5.250 -0.2221 0.01815 0.01059 -0.0650 0.6697 0.0369
-5.000 -0.2188 0.01723 0.00962 -0.0627 0.6678 0.0392
-4.750 -0.2132 0.01625 0.00854 -0.0613 0.6658 0.0417
-4.500 -0.2008 0.01528 0.00756 -0.0609 0.6640 0.0483
-4.250 -0.1951 0.01380 0.00632 -0.0597 0.6621 0.1415
-4.000 -0.1975 0.01047 0.00416 -0.0592 0.6603 0.4681
-3.750 -0.1685 0.01052 0.00424 -0.0598 0.6586 0.4971
-3.500 -0.1389 0.01068 0.00436 -0.0605 0.6570 0.5103
-3.250 -0.1093 0.01089 0.00459 -0.0610 0.6554 0.5188
-3.000 -0.0796 0.01102 0.00462 -0.0618 0.6540 0.5243
-2.750 -0.0500 0.01123 0.00484 -0.0623 0.6525 0.5298
-2.500 -0.0201 0.01151 0.00509 -0.0630 0.6511 0.5352
-2.250 0.0098 0.01175 0.00525 -0.0637 0.6495 0.5404
-2.000 0.0386 0.01182 0.00538 -0.0641 0.6481 0.5431
-1.750 0.0676 0.01183 0.00539 -0.0647 0.6467 0.5447
-1.500 0.0968 0.01184 0.00541 -0.0653 0.6453 0.5463
-1.250 0.1260 0.01187 0.00542 -0.0660 0.6438 0.5482
-1.000 0.1553 0.01189 0.00542 -0.0667 0.6424 0.5502
-0.750 0.1848 0.01191 0.00541 -0.0674 0.6410 0.5522
-0.500 0.2145 0.01196 0.00540 -0.0682 0.6397 0.5542
-0.250 0.2436 0.01192 0.00538 -0.0689 0.6383 0.5560
0.000 0.2731 0.01197 0.00544 -0.0695 0.6369 0.5576
0.250 0.3027 0.01206 0.00554 -0.0702 0.6356 0.5593
0.500 0.3323 0.01221 0.00569 -0.0710 0.6343 0.5610
0.750 0.3612 0.01227 0.00578 -0.0716 0.6332 0.5629
1.000 0.3900 0.01232 0.00586 -0.0722 0.6320 0.5649
1.250 0.4189 0.01237 0.00592 -0.0728 0.6306 0.5670
1.500 0.4479 0.01243 0.00599 -0.0734 0.6289 0.5688
1.750 0.4766 0.01243 0.00604 -0.0740 0.6274 0.5706
2.000 0.5053 0.01247 0.00614 -0.0746 0.6261 0.5722
2.250 0.5342 0.01254 0.00626 -0.0751 0.6246 0.5739
2.500 0.5633 0.01262 0.00639 -0.0757 0.6231 0.5757
2.750 0.5927 0.01271 0.00651 -0.0764 0.6218 0.5777
3.000 0.6224 0.01282 0.00663 -0.0771 0.6204 0.5798
3.250 0.6523 0.01302 0.00683 -0.0779 0.6187 0.5819
3.500 0.6800 0.01305 0.00692 -0.0783 0.6166 0.5837
3.750 0.7074 0.01300 0.00695 -0.0786 0.6136 0.5855
4.000 0.7352 0.01292 0.00694 -0.0789 0.6102 0.5871
4.250 0.7645 0.01281 0.00686 -0.0793 0.6064 0.5887
4.500 0.7936 0.01278 0.00684 -0.0798 0.6020 0.5904
4.750 0.8191 0.01264 0.00681 -0.0795 0.5966 0.5922
5.000 0.8475 0.01249 0.00668 -0.0798 0.5916 0.5942
5.250 0.8760 0.01243 0.00662 -0.0802 0.5868 0.5964
5.500 0.9014 0.01234 0.00662 -0.0799 0.5812 0.5984
5.750 0.9291 0.01223 0.00655 -0.0801 0.5761 0.6001
6.000 0.9542 0.01205 0.00645 -0.0798 0.5690 0.6019
6.250 0.9786 0.01187 0.00635 -0.0793 0.5604 0.6035
6.500 1.0033 0.01182 0.00640 -0.0789 0.5529 0.6052
6.750 1.0279 0.01176 0.00641 -0.0785 0.5444 0.6070
7.000 1.0514 0.01173 0.00648 -0.0779 0.5326 0.6089
7.250 1.0732 0.01173 0.00651 -0.0769 0.5157 0.6110
7.500 1.0920 0.01182 0.00658 -0.0754 0.4879 0.6130
7.750 1.0976 0.01231 0.00682 -0.0715 0.4336 0.6146
8.000 1.0878 0.01320 0.00740 -0.0650 0.3750 0.6161
8.250 1.0777 0.01424 0.00821 -0.0588 0.3258 0.6176
8.500 1.0686 0.01547 0.00922 -0.0532 0.2794 0.6190
8.750 1.0603 0.01679 0.01034 -0.0482 0.2381 0.6205
9.000 1.0540 0.01816 0.01157 -0.0439 0.2044 0.6222
9.250 1.0474 0.01974 0.01299 -0.0401 0.1732 0.6240
9.500 1.0436 0.02140 0.01453 -0.0370 0.1462 0.6258
9.750 1.0438 0.02301 0.01606 -0.0348 0.1251 0.6275
10.000 1.0442 0.02476 0.01770 -0.0329 0.1057 0.6292
10.250 1.0463 0.02648 0.01934 -0.0312 0.0894 0.6307
10.500 1.0505 0.02805 0.02090 -0.0299 0.0765 0.6326
10.750 1.0557 0.02963 0.02246 -0.0287 0.0665 0.6343
11.000 1.0637 0.03103 0.02390 -0.0277 0.0593 0.6360
11.250 1.0698 0.03261 0.02548 -0.0267 0.0531 0.6377
11.500 1.0789 0.03400 0.02691 -0.0259 0.0486 0.6396
11.750 1.0839 0.03573 0.02863 -0.0250 0.0439 0.6415
12.000 1.0957 0.03696 0.02992 -0.0245 0.0407 0.6436
12.250 1.1034 0.03854 0.03151 -0.0238 0.0374 0.6453
12.500 1.1113 0.04013 0.03315 -0.0232 0.0342 0.6470
12.750 1.1219 0.04151 0.03460 -0.0228 0.0312 0.6489
13.000 1.1269 0.04340 0.03651 -0.0222 0.0277 0.6506
13.250 1.1378 0.04484 0.03802 -0.0219 0.0242 0.6526
13.500 1.1426 0.04686 0.04005 -0.0213 0.0200 0.6546
13.750 1.1469 0.04900 0.04219 -0.0209 0.0168 0.6568
14.000 1.1530 0.05103 0.04430 -0.0206 0.0153 0.6589
14.250 1.1597 0.05305 0.04636 -0.0204 0.0139 0.6609
14.500 1.1595 0.05583 0.04921 -0.0201 0.0128 0.6627
14.750 1.1670 0.05783 0.05133 -0.0201 0.0120 0.6648
15.000 1.1724 0.06012 0.05371 -0.0201 0.0116 0.6669
15.250 1.1784 0.06238 0.05606 -0.0202 0.0109 0.6692
15.500 1.1827 0.06490 0.05865 -0.0204 0.0105 0.6715
15.750 1.1820 0.06808 0.06190 -0.0206 0.0101 0.6737
16.000 1.1796 0.07152 0.06542 -0.0210 0.0097 0.6757
16.250 1.1830 0.07435 0.06838 -0.0214 0.0095 0.6780
16.500 1.1859 0.07730 0.07146 -0.0220 0.0093 0.6805
16.750 1.1882 0.08039 0.07468 -0.0227 0.0090 0.6831
17.000 1.1890 0.08372 0.07813 -0.0234 0.0089 0.6860
17.250 1.1901 0.08709 0.08161 -0.0243 0.0086 0.6889
17.500 1.1903 0.09067 0.08529 -0.0254 0.0084 0.6917
17.750 1.1906 0.09428 0.08903 -0.0266 0.0083 0.6945
18.000 1.1900 0.09808 0.09295 -0.0279 0.0081 0.6974
18.250 1.1889 0.10200 0.09699 -0.0294 0.0079 0.7006
18.500 1.1875 0.10603 0.10114 -0.0310 0.0079 0.7039
19.000 1.1824 0.11463 0.10996 -0.0347 0.0076 0.7105
19.250 1.1795 0.11902 0.11448 -0.0367 0.0075 0.7141
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