NACA 64(1)-212 (n64212-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 64(1)-212 (n64212-il) Reynolds number: 50,000 Max Cl/Cd: 31.75 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-n64212-il-50000-n5.txt Download as CSV file: xf-n64212-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 64(1)-212
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.5635 0.09582 0.08852 -0.0309 1.0000 0.0572
-10.500 -0.5796 0.08754 0.08027 -0.0367 1.0000 0.0560
-10.250 -0.6070 0.07940 0.07212 -0.0430 1.0000 0.0546
-10.000 -0.6397 0.07290 0.06552 -0.0470 1.0000 0.0536
-9.750 -0.6742 0.06829 0.06069 -0.0476 1.0000 0.0526
-9.500 -0.6898 0.06444 0.05659 -0.0472 1.0000 0.0523
-9.250 -0.6958 0.06080 0.05270 -0.0464 1.0000 0.0523
-9.000 -0.6973 0.05729 0.04892 -0.0455 1.0000 0.0523
-8.750 -0.6951 0.05390 0.04526 -0.0444 1.0000 0.0525
-8.500 -0.6896 0.05073 0.04183 -0.0432 1.0000 0.0529
-8.250 -0.6816 0.04783 0.03867 -0.0420 1.0000 0.0535
-8.000 -0.6706 0.04539 0.03605 -0.0408 1.0000 0.0548
-7.750 -0.6592 0.04321 0.03366 -0.0394 1.0000 0.0568
-7.500 -0.6473 0.04102 0.03115 -0.0378 1.0000 0.0588
-7.250 -0.6339 0.03882 0.02861 -0.0360 1.0000 0.0605
-7.000 -0.6183 0.03674 0.02618 -0.0343 1.0000 0.0619
-6.750 -0.6013 0.03494 0.02403 -0.0326 1.0000 0.0634
-6.500 -0.5845 0.03328 0.02241 -0.0311 1.0000 0.0663
-6.250 -0.5682 0.03205 0.02111 -0.0294 1.0000 0.0701
-6.000 -0.5506 0.03086 0.01975 -0.0276 1.0000 0.0739
-5.750 -0.5330 0.02978 0.01853 -0.0255 1.0000 0.0770
-5.500 -0.5195 0.02876 0.01760 -0.0234 1.0000 0.0820
-5.250 -0.5059 0.02796 0.01667 -0.0213 1.0000 0.0886
-5.000 -0.4940 0.02704 0.01574 -0.0191 1.0000 0.0943
-4.750 -0.4817 0.02622 0.01485 -0.0171 1.0000 0.1027
-4.500 -0.4533 0.02500 0.01371 -0.0185 0.9927 0.1216
-4.250 -0.4226 0.02328 0.01236 -0.0208 0.9839 0.1696
-4.000 -0.4033 0.02093 0.01198 -0.0209 0.9748 0.4708
-3.750 -0.3762 0.02128 0.01250 -0.0198 0.9648 0.5954
-3.500 -0.3521 0.02211 0.01339 -0.0171 0.9551 0.6678
-3.250 -0.3299 0.02337 0.01468 -0.0126 0.9465 0.7268
-3.000 -0.3042 0.02401 0.01517 -0.0102 0.9376 0.7581
-2.750 -0.2716 0.02403 0.01496 -0.0110 0.9295 0.7727
-2.500 -0.2377 0.02395 0.01465 -0.0124 0.9215 0.7845
-2.250 -0.2040 0.02391 0.01440 -0.0135 0.9137 0.7941
-2.000 -0.1706 0.02380 0.01411 -0.0150 0.9058 0.8043
-1.750 -0.1411 0.02370 0.01385 -0.0157 0.8972 0.8141
-1.500 -0.1068 0.02361 0.01362 -0.0172 0.8900 0.8224
-1.250 -0.0803 0.02352 0.01341 -0.0175 0.8808 0.8325
-1.000 -0.0455 0.02346 0.01325 -0.0189 0.8742 0.8406
-0.750 -0.0198 0.02342 0.01312 -0.0190 0.8652 0.8503
-0.500 0.0133 0.02335 0.01298 -0.0203 0.8586 0.8600
-0.250 0.0400 0.02337 0.01296 -0.0205 0.8499 0.8695
0.000 0.0729 0.02334 0.01288 -0.0217 0.8435 0.8795
0.250 0.0991 0.02339 0.01291 -0.0219 0.8349 0.8908
0.500 0.1356 0.02340 0.01291 -0.0238 0.8289 0.9001
0.750 0.1659 0.02348 0.01300 -0.0249 0.8211 0.9113
1.000 0.1999 0.02353 0.01307 -0.0265 0.8144 0.9229
1.250 0.2383 0.02361 0.01319 -0.0290 0.8083 0.9332
1.500 0.2752 0.02374 0.01339 -0.0314 0.8008 0.9442
1.750 0.3191 0.02376 0.01347 -0.0348 0.7960 0.9540
2.000 0.3561 0.02402 0.01384 -0.0377 0.7876 0.9661
2.250 0.4012 0.02408 0.01401 -0.0415 0.7820 0.9761
2.500 0.4412 0.02431 0.01439 -0.0449 0.7738 0.9888
2.750 0.4782 0.02442 0.01464 -0.0472 0.7669 1.0000
3.000 0.4830 0.02484 0.01512 -0.0442 0.7564 1.0000
3.250 0.5043 0.02492 0.01529 -0.0432 0.7495 1.0000
3.750 0.5263 0.02583 0.01636 -0.0388 0.7287 1.0000
4.000 0.5517 0.02600 0.01666 -0.0384 0.7204 1.0000
4.250 0.5698 0.02642 0.01721 -0.0371 0.7087 1.0000
4.500 0.5936 0.02656 0.01754 -0.0362 0.6963 1.0000
4.750 0.6204 0.02634 0.01749 -0.0351 0.6806 1.0000
5.000 0.6535 0.02517 0.01647 -0.0332 0.6565 1.0000
5.250 0.6761 0.02405 0.01543 -0.0298 0.6184 1.0000
5.500 0.6962 0.02311 0.01452 -0.0263 0.5700 1.0000
5.750 0.7123 0.02277 0.01417 -0.0231 0.5082 1.0000
6.000 0.7256 0.02285 0.01380 -0.0196 0.3764 1.0000
6.250 0.7241 0.02484 0.01447 -0.0156 0.2211 1.0000
6.500 0.7253 0.02711 0.01609 -0.0131 0.1524 1.0000
6.750 0.7320 0.02897 0.01767 -0.0111 0.1230 1.0000
7.000 0.7416 0.03062 0.01918 -0.0094 0.1076 1.0000
7.250 0.7542 0.03210 0.02064 -0.0078 0.0952 1.0000
7.500 0.7704 0.03349 0.02211 -0.0065 0.0862 1.0000
7.750 0.7905 0.03501 0.02356 -0.0056 0.0796 1.0000
8.000 0.8176 0.03637 0.02514 -0.0052 0.0719 1.0000
8.250 0.8514 0.03816 0.02686 -0.0056 0.0670 1.0000
8.500 0.8829 0.04000 0.02904 -0.0057 0.0622 1.0000
8.750 0.9081 0.04192 0.03108 -0.0056 0.0581 1.0000
9.000 0.9366 0.04458 0.03377 -0.0060 0.0557 1.0000
9.250 0.9568 0.04730 0.03697 -0.0053 0.0544 1.0000
9.500 0.9711 0.05019 0.04032 -0.0042 0.0529 1.0000
9.750 0.9805 0.05312 0.04366 -0.0030 0.0512 1.0000
10.000 0.9862 0.05603 0.04690 -0.0016 0.0497 1.0000
10.250 0.9891 0.05902 0.05019 -0.0003 0.0486 1.0000
10.500 0.9875 0.06219 0.05365 0.0012 0.0479 1.0000
10.750 0.9794 0.06552 0.05725 0.0030 0.0476 1.0000
11.000 0.9663 0.06915 0.06115 0.0043 0.0477 1.0000
11.250 0.9492 0.07325 0.06550 0.0048 0.0477 1.0000
11.500 0.9277 0.07807 0.07056 0.0042 0.0479 1.0000
11.750 0.9020 0.08386 0.07657 0.0021 0.0483 1.0000
12.000 0.8727 0.09102 0.08391 -0.0016 0.0488 1.0000
12.250 0.8418 0.09983 0.09285 -0.0073 0.0496 1.0000
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Polar data table (+)
Polar graphs
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