NACA 64(1)-212 (n64212-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 64(1)-212 (n64212-il) Reynolds number: 50,000 Max Cl/Cd: 31.06 at α=6.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-n64212-il-50000.txt Download as CSV file: xf-n64212-il-50000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.4470 0.10120 0.09406 -0.0029 1.0000 0.3884
-8.750 -0.5415 0.08244 0.07565 -0.0288 1.0000 0.2004
-8.500 -0.6112 0.07267 0.06603 -0.0383 1.0000 0.1791
-8.250 -0.6327 0.06585 0.05900 -0.0410 1.0000 0.1591
-8.000 -0.6557 0.06033 0.05300 -0.0415 1.0000 0.1463
-7.750 -0.6484 0.05577 0.04835 -0.0408 1.0000 0.1400
-7.500 -0.6572 0.05171 0.04354 -0.0392 1.0000 0.1318
-7.250 -0.6477 0.04810 0.03976 -0.0377 1.0000 0.1293
-7.000 -0.6402 0.04501 0.03633 -0.0359 1.0000 0.1284
-6.750 -0.6313 0.04227 0.03320 -0.0339 1.0000 0.1288
-6.500 -0.6200 0.03974 0.03026 -0.0319 1.0000 0.1296
-6.250 -0.6057 0.03732 0.02747 -0.0301 1.0000 0.1300
-6.000 -0.5895 0.03510 0.02487 -0.0283 1.0000 0.1309
-5.750 -0.5722 0.03313 0.02254 -0.0265 1.0000 0.1337
-5.500 -0.5539 0.03128 0.02076 -0.0251 1.0000 0.1406
-5.250 -0.5341 0.02981 0.01899 -0.0234 1.0000 0.1467
-5.000 -0.5134 0.02820 0.01749 -0.0218 1.0000 0.1547
-4.750 -0.4945 0.02693 0.01628 -0.0200 1.0000 0.1686
-4.500 -0.4769 0.02571 0.01516 -0.0179 1.0000 0.1851
-4.250 -0.4621 0.02433 0.01401 -0.0159 1.0000 0.2141
-4.000 -0.4517 0.02162 0.01248 -0.0142 1.0000 0.3159
-3.750 -0.4663 0.02211 0.01481 -0.0015 1.0000 0.6655
-3.500 -0.4693 0.02360 0.01627 0.0083 1.0000 0.7301
-3.250 -0.4684 0.02465 0.01723 0.0167 1.0000 0.7735
-3.000 -0.3029 0.02990 0.02159 0.0116 1.0000 0.9143
-2.750 -0.2317 0.02928 0.02055 0.0028 1.0000 0.9366
-2.500 -0.1922 0.02869 0.01972 -0.0014 1.0000 0.9521
-2.250 -0.1548 0.02816 0.01900 -0.0055 1.0000 0.9657
-2.000 -0.1163 0.02769 0.01834 -0.0101 1.0000 0.9786
-1.750 -0.0758 0.02727 0.01778 -0.0152 1.0000 0.9911
-1.500 -0.0463 0.02703 0.01743 -0.0185 1.0000 1.0000
-1.250 -0.0535 0.02701 0.01739 -0.0154 1.0000 1.0000
-1.000 -0.0608 0.02693 0.01729 -0.0124 1.0000 1.0000
-0.750 -0.0682 0.02679 0.01713 -0.0093 1.0000 1.0000
-0.500 -0.0761 0.02658 0.01689 -0.0062 1.0000 1.0000
-0.250 -0.0845 0.02630 0.01658 -0.0030 1.0000 1.0000
0.000 -0.0937 0.02593 0.01618 0.0004 1.0000 1.0000
0.250 -0.1030 0.02549 0.01570 0.0038 1.0000 1.0000
0.500 -0.0834 0.02566 0.01580 0.0023 0.9934 1.0000
0.750 -0.0612 0.02596 0.01603 0.0004 0.9853 1.0000
1.000 -0.0387 0.02635 0.01632 -0.0012 0.9780 1.0000
1.250 -0.0071 0.02709 0.01697 -0.0043 0.9708 1.0000
1.500 0.0175 0.02762 0.01744 -0.0060 0.9633 1.0000
1.750 0.0543 0.02864 0.01839 -0.0096 0.9562 1.0000
2.000 0.0772 0.02923 0.01893 -0.0108 0.9485 1.0000
2.250 0.1135 0.03031 0.01999 -0.0142 0.9405 1.0000
2.500 0.1377 0.03105 0.02073 -0.0154 0.9322 1.0000
2.750 0.1701 0.03211 0.02179 -0.0179 0.9236 1.0000
3.000 0.1988 0.03308 0.02279 -0.0198 0.9147 1.0000
3.250 0.2247 0.03406 0.02381 -0.0212 0.9056 1.0000
3.500 0.2606 0.03530 0.02514 -0.0240 0.8953 1.0000
3.750 0.2854 0.03627 0.02618 -0.0251 0.8844 1.0000
4.000 0.3110 0.03734 0.02734 -0.0263 0.8727 1.0000
4.250 0.3409 0.03850 0.02863 -0.0279 0.8592 1.0000
4.500 0.3721 0.03963 0.02991 -0.0296 0.8438 1.0000
4.750 0.4046 0.04073 0.03118 -0.0313 0.8267 1.0000
5.000 0.4471 0.04175 0.03246 -0.0338 0.8067 1.0000
5.250 0.4778 0.04257 0.03349 -0.0345 0.7842 1.0000
5.500 0.5274 0.04280 0.03406 -0.0364 0.7561 1.0000
5.750 0.6074 0.04016 0.03202 -0.0375 0.7085 1.0000
6.000 0.7482 0.02598 0.01881 -0.0290 0.6005 1.0000
6.250 0.7421 0.02389 0.01503 -0.0161 0.3133 1.0000
6.500 0.7366 0.02714 0.01697 -0.0118 0.2226 1.0000
6.750 0.7538 0.02944 0.01882 -0.0101 0.1818 1.0000
7.000 0.7897 0.03162 0.02084 -0.0102 0.1565 1.0000
7.250 0.8265 0.03388 0.02299 -0.0107 0.1394 1.0000
7.500 0.8627 0.03661 0.02583 -0.0112 0.1307 1.0000
7.750 0.8918 0.03919 0.02849 -0.0113 0.1226 1.0000
8.000 0.9159 0.04226 0.03190 -0.0107 0.1188 1.0000
8.250 0.9363 0.04547 0.03559 -0.0096 0.1176 1.0000
8.500 0.9520 0.04885 0.03945 -0.0083 0.1167 1.0000
8.750 0.9629 0.05233 0.04340 -0.0068 0.1158 1.0000
9.000 0.9694 0.05600 0.04751 -0.0053 0.1152 1.0000
9.250 0.9711 0.05999 0.05192 -0.0037 0.1159 1.0000
9.500 0.9706 0.06438 0.05664 -0.0023 0.1177 1.0000
9.750 0.9764 0.06930 0.06176 -0.0017 0.1199 1.0000
10.000 0.9461 0.07338 0.06635 0.0004 0.1240 1.0000
10.250 0.9040 0.07814 0.07135 0.0016 0.1271 1.0000
10.500 0.8736 0.08388 0.07720 0.0004 0.1304 1.0000
10.750 0.8768 0.08979 0.08318 -0.0007 0.1361 1.0000
11.000 0.7905 0.10466 0.09804 -0.0137 0.1518 1.0000
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Polar data table (+)
Polar graphs
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