RAE(NPL) 5212 AIRFOIL (rae5212-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: RAE(NPL) 5212 AIRFOIL (rae5212-il) Reynolds number: 1,000,000 Max Cl/Cd: 76.45 at α=8.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-rae5212-il-1000000.txt Download as CSV file: xf-rae5212-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: RAE(NPL) 5212 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
------ -------- --------- --------- -------- -------- --------
-14.750 -0.8784 0.06195 0.05937 -0.0655 1.0000 0.0109
-14.500 -0.9111 0.05398 0.05119 -0.0701 1.0000 0.0108
-14.250 -0.9252 0.04945 0.04652 -0.0720 1.0000 0.0108
-14.000 -0.9448 0.04468 0.04158 -0.0734 1.0000 0.0109
-13.750 -0.9525 0.04167 0.03847 -0.0738 1.0000 0.0109
-13.500 -0.9586 0.03906 0.03577 -0.0736 1.0000 0.0110
-13.250 -0.9697 0.03619 0.03276 -0.0728 1.0000 0.0110
-13.000 -0.9759 0.03411 0.03058 -0.0716 1.0000 0.0111
-12.750 -0.9832 0.03225 0.02861 -0.0697 1.0000 0.0112
-12.500 -0.9912 0.03092 0.02720 -0.0668 1.0000 0.0113
-12.250 -1.0096 0.02976 0.02594 -0.0614 1.0000 0.0113
-12.000 -1.0138 0.02859 0.02467 -0.0576 1.0000 0.0114
-11.750 -1.0111 0.02758 0.02357 -0.0547 1.0000 0.0116
-11.500 -1.0068 0.02645 0.02233 -0.0519 1.0000 0.0117
-11.250 -0.9807 0.02505 0.02079 -0.0534 0.9984 0.0120
-11.000 -0.9539 0.02376 0.01935 -0.0548 0.9967 0.0123
-10.750 -0.9257 0.02263 0.01808 -0.0563 0.9952 0.0125
-10.500 -0.8952 0.02177 0.01710 -0.0579 0.9941 0.0128
-10.250 -0.8685 0.02099 0.01621 -0.0585 0.9920 0.0130
-10.000 -0.8456 0.01904 0.01411 -0.0592 0.9895 0.0134
-9.750 -0.8153 0.01839 0.01344 -0.0605 0.9878 0.0139
-9.500 -0.7841 0.01771 0.01271 -0.0618 0.9864 0.0142
-9.250 -0.7524 0.01704 0.01199 -0.0633 0.9853 0.0146
-9.000 -0.7198 0.01646 0.01135 -0.0648 0.9844 0.0151
-8.750 -0.6906 0.01584 0.01066 -0.0656 0.9825 0.0155
-8.500 -0.6635 0.01531 0.01007 -0.0658 0.9791 0.0158
-8.250 -0.6342 0.01442 0.00911 -0.0667 0.9769 0.0163
-8.000 -0.6028 0.01370 0.00838 -0.0680 0.9753 0.0170
-7.750 -0.5695 0.01325 0.00792 -0.0695 0.9742 0.0175
-7.500 -0.5353 0.01285 0.00750 -0.0711 0.9733 0.0184
-7.250 -0.5006 0.01247 0.00709 -0.0728 0.9726 0.0191
-7.000 -0.4756 0.01192 0.00650 -0.0725 0.9682 0.0198
-6.750 -0.4459 0.01135 0.00592 -0.0732 0.9651 0.0208
-6.500 -0.4139 0.01096 0.00553 -0.0743 0.9628 0.0219
-6.250 -0.3811 0.01061 0.00516 -0.0755 0.9609 0.0230
-6.000 -0.3517 0.01016 0.00468 -0.0760 0.9578 0.0244
-5.750 -0.3271 0.00983 0.00436 -0.0754 0.9515 0.0259
-5.500 -0.2969 0.00954 0.00406 -0.0759 0.9476 0.0276
-5.250 -0.2685 0.00918 0.00367 -0.0760 0.9426 0.0295
-5.000 -0.2421 0.00891 0.00341 -0.0757 0.9352 0.0318
-4.750 -0.2115 0.00865 0.00312 -0.0763 0.9303 0.0345
-4.500 -0.1858 0.00840 0.00288 -0.0758 0.9211 0.0387
-4.250 -0.1571 0.00814 0.00263 -0.0760 0.9139 0.0456
-4.000 -0.1299 0.00791 0.00242 -0.0759 0.9050 0.0565
-3.750 -0.1027 0.00763 0.00221 -0.0758 0.8968 0.0781
-3.500 -0.0769 0.00723 0.00199 -0.0755 0.8879 0.1329
-3.250 -0.0525 0.00669 0.00176 -0.0751 0.8793 0.2254
-3.000 -0.0304 0.00583 0.00146 -0.0745 0.8706 0.3934
-2.750 -0.0055 0.00544 0.00136 -0.0741 0.8626 0.4857
-2.500 0.0217 0.00535 0.00134 -0.0739 0.8550 0.5276
-2.250 0.0496 0.00534 0.00133 -0.0737 0.8479 0.5489
-2.000 0.0774 0.00533 0.00132 -0.0736 0.8403 0.5626
-1.750 0.1052 0.00535 0.00132 -0.0734 0.8324 0.5768
-1.500 0.1327 0.00537 0.00133 -0.0732 0.8231 0.5910
-1.250 0.1601 0.00543 0.00135 -0.0728 0.8116 0.6029
-1.000 0.1866 0.00548 0.00137 -0.0723 0.7962 0.6130
-0.750 0.2135 0.00555 0.00137 -0.0719 0.7815 0.6199
-0.500 0.2405 0.00558 0.00137 -0.0716 0.7686 0.6249
-0.250 0.2676 0.00564 0.00137 -0.0713 0.7553 0.6286
0.000 0.2946 0.00569 0.00136 -0.0709 0.7397 0.6318
0.250 0.3214 0.00577 0.00136 -0.0706 0.7234 0.6344
0.500 0.3485 0.00579 0.00136 -0.0703 0.7097 0.6377
0.750 0.3751 0.00585 0.00138 -0.0699 0.6925 0.6406
1.000 0.4015 0.00593 0.00140 -0.0694 0.6741 0.6436
1.250 0.4279 0.00603 0.00143 -0.0690 0.6528 0.6467
1.500 0.4533 0.00618 0.00147 -0.0684 0.6232 0.6496
1.750 0.4768 0.00641 0.00152 -0.0674 0.5756 0.6524
2.000 0.4978 0.00679 0.00165 -0.0661 0.5051 0.6557
2.250 0.5178 0.00733 0.00184 -0.0646 0.4209 0.6587
2.500 0.5388 0.00785 0.00204 -0.0633 0.3457 0.6619
2.750 0.5603 0.00834 0.00224 -0.0622 0.2782 0.6651
3.000 0.5824 0.00881 0.00244 -0.0611 0.2210 0.6680
3.250 0.6044 0.00923 0.00265 -0.0601 0.1678 0.6716
3.500 0.6270 0.00963 0.00287 -0.0591 0.1269 0.6751
3.750 0.6508 0.00996 0.00308 -0.0584 0.1032 0.6788
4.000 0.6755 0.01022 0.00326 -0.0578 0.0913 0.6824
4.250 0.7008 0.01041 0.00343 -0.0573 0.0852 0.6860
4.500 0.7259 0.01059 0.00362 -0.0567 0.0817 0.6898
4.750 0.7506 0.01082 0.00384 -0.0561 0.0780 0.6936
5.000 0.7754 0.01106 0.00408 -0.0555 0.0752 0.6975
5.250 0.8008 0.01122 0.00427 -0.0550 0.0740 0.7014
5.500 0.8257 0.01138 0.00448 -0.0545 0.0725 0.7057
5.750 0.8503 0.01159 0.00471 -0.0539 0.0709 0.7101
6.000 0.8746 0.01182 0.00495 -0.0532 0.0693 0.7144
6.250 0.8982 0.01209 0.00523 -0.0524 0.0675 0.7190
6.500 0.9202 0.01245 0.00564 -0.0514 0.0653 0.7241
6.750 0.9425 0.01280 0.00603 -0.0504 0.0640 0.7298
7.000 0.9666 0.01298 0.00627 -0.0497 0.0634 0.7359
7.250 0.9903 0.01318 0.00652 -0.0489 0.0625 0.7431
7.500 1.0138 0.01339 0.00677 -0.0482 0.0613 0.7506
7.750 1.0365 0.01362 0.00707 -0.0473 0.0602 0.7600
8.000 1.0587 0.01387 0.00737 -0.0463 0.0591 0.7711
8.250 1.0802 0.01413 0.00770 -0.0452 0.0579 0.7863
8.500 1.0997 0.01445 0.00811 -0.0437 0.0566 0.8110
8.750 1.1113 0.01475 0.00877 -0.0406 0.0549 0.9182
9.000 1.1441 0.01522 0.00933 -0.0422 0.0539 1.0000
9.250 1.1661 0.01542 0.00955 -0.0412 0.0533 1.0000
9.500 1.1873 0.01564 0.00980 -0.0400 0.0524 1.0000
9.750 1.2071 0.01595 0.01013 -0.0387 0.0515 1.0000
10.000 1.2273 0.01621 0.01041 -0.0374 0.0504 1.0000
10.250 1.2478 0.01645 0.01065 -0.0362 0.0493 1.0000
10.500 1.2672 0.01676 0.01095 -0.0349 0.0481 1.0000
10.750 1.2818 0.01739 0.01160 -0.0329 0.0468 1.0000
11.000 1.2964 0.01802 0.01228 -0.0309 0.0458 1.0000
11.250 1.3160 0.01833 0.01263 -0.0297 0.0454 1.0000
11.500 1.3351 0.01865 0.01301 -0.0284 0.0447 1.0000
11.750 1.3536 0.01902 0.01341 -0.0271 0.0439 1.0000
12.000 1.3719 0.01940 0.01382 -0.0258 0.0431 1.0000
12.250 1.3898 0.01979 0.01424 -0.0245 0.0422 1.0000
12.500 1.4076 0.02020 0.01466 -0.0232 0.0413 1.0000
12.750 1.4229 0.02075 0.01523 -0.0216 0.0401 1.0000
13.000 1.4334 0.02164 0.01617 -0.0195 0.0389 1.0000
13.250 1.4519 0.02202 0.01660 -0.0184 0.0383 1.0000
13.500 1.4686 0.02252 0.01716 -0.0172 0.0376 1.0000
13.750 1.4852 0.02302 0.01770 -0.0160 0.0366 1.0000
14.000 1.5006 0.02361 0.01833 -0.0147 0.0356 1.0000
14.250 1.5151 0.02428 0.01899 -0.0134 0.0341 1.0000
14.500 1.5236 0.02536 0.02012 -0.0115 0.0329 1.0000
14.750 1.5398 0.02595 0.02078 -0.0105 0.0321 1.0000
15.000 1.5537 0.02670 0.02160 -0.0093 0.0310 1.0000
15.250 1.5661 0.02758 0.02249 -0.0081 0.0296 1.0000
15.500 1.5740 0.02881 0.02376 -0.0066 0.0280 1.0000
15.750 1.5857 0.02979 0.02481 -0.0054 0.0269 1.0000
16.000 1.5960 0.03091 0.02598 -0.0043 0.0255 1.0000
16.250 1.6024 0.03236 0.02747 -0.0030 0.0242 1.0000
16.500 1.6073 0.03399 0.02916 -0.0017 0.0230 1.0000
16.750 1.6135 0.03555 0.03080 -0.0007 0.0219 1.0000
17.000 1.6171 0.03740 0.03272 0.0003 0.0211 1.0000
17.250 1.6173 0.03963 0.03501 0.0012 0.0200 1.0000
17.500 1.6156 0.04215 0.03762 0.0019 0.0194 1.0000
17.750 1.6168 0.04447 0.04005 0.0023 0.0188 1.0000
18.000 1.6158 0.04712 0.04280 0.0026 0.0183 1.0000
18.250 1.6121 0.05021 0.04597 0.0026 0.0177 1.0000
18.500 1.6063 0.05369 0.04956 0.0022 0.0174 1.0000
18.750 1.5973 0.05777 0.05375 0.0014 0.0170 1.0000
19.000 1.5846 0.06262 0.05872 0.0000 0.0167 1.0000
19.250 1.5671 0.06848 0.06471 -0.0023 0.0163 1.0000
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