NACA 65(1)-212 (naca651212-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 65(1)-212 (naca651212-il) Reynolds number: 1,000,000 Max Cl/Cd: 87.81 at α=3.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca651212-il-1000000.txt Download as CSV file: xf-naca651212-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 65(1)-212
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
------ -------- --------- --------- -------- -------- --------
-12.750 -0.7915 0.05582 0.05375 -0.0559 1.0000 0.0098
-12.500 -0.8174 0.04967 0.04741 -0.0586 1.0000 0.0098
-12.250 -0.8490 0.04389 0.04140 -0.0597 1.0000 0.0099
-12.000 -0.8733 0.03953 0.03681 -0.0588 1.0000 0.0099
-11.750 -0.8968 0.03575 0.03279 -0.0564 1.0000 0.0099
-11.500 -0.8853 0.03580 0.03288 -0.0552 1.0000 0.0102
-11.250 -0.9006 0.03331 0.03019 -0.0511 1.0000 0.0102
-11.000 -0.8984 0.03170 0.02844 -0.0488 1.0000 0.0103
-10.750 -0.8949 0.02988 0.02645 -0.0465 1.0000 0.0104
-10.500 -0.8782 0.02990 0.02647 -0.0454 1.0000 0.0107
-10.250 -0.8701 0.02881 0.02528 -0.0431 1.0000 0.0109
-10.000 -0.8468 0.02728 0.02359 -0.0441 0.9916 0.0112
-9.750 -0.8198 0.02532 0.02140 -0.0458 0.9853 0.0118
-9.500 -0.7923 0.02332 0.01914 -0.0473 0.9776 0.0123
-9.250 -0.7622 0.02202 0.01763 -0.0489 0.9698 0.0126
-9.000 -0.7351 0.02123 0.01666 -0.0495 0.9585 0.0129
-8.750 -0.7200 0.01790 0.01298 -0.0484 0.9453 0.0135
-8.500 -0.6986 0.01717 0.01218 -0.0476 0.9337 0.0138
-8.250 -0.6762 0.01677 0.01171 -0.0470 0.9234 0.0143
-8.000 -0.6540 0.01619 0.01103 -0.0462 0.9138 0.0147
-7.750 -0.6306 0.01574 0.01050 -0.0457 0.9047 0.0153
-7.500 -0.6074 0.01520 0.00987 -0.0451 0.8963 0.0158
-7.250 -0.5836 0.01465 0.00924 -0.0446 0.8875 0.0163
-7.000 -0.5598 0.01411 0.00860 -0.0440 0.8795 0.0166
-6.750 -0.5351 0.01374 0.00815 -0.0436 0.8716 0.0169
-6.500 -0.5158 0.01240 0.00670 -0.0424 0.8638 0.0177
-6.250 -0.4926 0.01183 0.00608 -0.0419 0.8560 0.0184
-6.000 -0.4675 0.01151 0.00573 -0.0416 0.8488 0.0192
-5.750 -0.4421 0.01121 0.00538 -0.0413 0.8414 0.0201
-5.500 -0.4168 0.01087 0.00498 -0.0410 0.8346 0.0209
-5.250 -0.3912 0.01055 0.00461 -0.0408 0.8276 0.0215
-5.000 -0.3650 0.01032 0.00433 -0.0406 0.8214 0.0221
-4.750 -0.3409 0.00969 0.00362 -0.0402 0.8145 0.0237
-4.250 -0.2878 0.00921 0.00307 -0.0400 0.8017 0.0273
-4.000 -0.2607 0.00905 0.00287 -0.0400 0.7954 0.0288
-3.750 -0.2342 0.00873 0.00250 -0.0399 0.7897 0.0328
-3.500 -0.2069 0.00853 0.00229 -0.0399 0.7835 0.0368
-3.250 -0.1800 0.00832 0.00208 -0.0399 0.7778 0.0474
-3.000 -0.1553 0.00759 0.00178 -0.0398 0.7718 0.1581
-2.750 -0.1333 0.00642 0.00139 -0.0397 0.7660 0.3770
-2.500 -0.1088 0.00570 0.00121 -0.0396 0.7607 0.5377
-2.250 -0.0811 0.00555 0.00117 -0.0397 0.7551 0.5827
-2.000 -0.0531 0.00549 0.00114 -0.0398 0.7497 0.6096
-1.750 -0.0246 0.00545 0.00113 -0.0400 0.7446 0.6322
-1.500 0.0035 0.00541 0.00114 -0.0401 0.7393 0.6549
-1.250 0.0317 0.00543 0.00115 -0.0402 0.7342 0.6728
-1.000 0.0602 0.00542 0.00117 -0.0404 0.7293 0.6868
-0.750 0.0888 0.00543 0.00118 -0.0406 0.7242 0.6958
-0.500 0.1173 0.00545 0.00117 -0.0408 0.7194 0.7007
-0.250 0.1463 0.00546 0.00117 -0.0411 0.7147 0.7056
0.000 0.1750 0.00545 0.00117 -0.0413 0.7099 0.7103
0.250 0.2035 0.00547 0.00118 -0.0415 0.7052 0.7153
0.500 0.2324 0.00549 0.00119 -0.0418 0.7008 0.7203
0.750 0.2611 0.00549 0.00121 -0.0420 0.6961 0.7252
1.000 0.2896 0.00551 0.00125 -0.0422 0.6915 0.7303
1.250 0.3183 0.00554 0.00128 -0.0425 0.6859 0.7357
1.500 0.3466 0.00554 0.00129 -0.0426 0.6778 0.7408
1.750 0.3747 0.00555 0.00132 -0.0427 0.6669 0.7462
2.000 0.4029 0.00560 0.00134 -0.0428 0.6541 0.7518
2.250 0.4303 0.00563 0.00136 -0.0428 0.6352 0.7572
2.500 0.4579 0.00569 0.00140 -0.0428 0.6183 0.7631
2.750 0.4853 0.00579 0.00146 -0.0428 0.5958 0.7688
3.000 0.5122 0.00591 0.00153 -0.0427 0.5697 0.7744
3.250 0.5383 0.00613 0.00163 -0.0424 0.5275 0.7808
3.500 0.5587 0.00686 0.00191 -0.0414 0.4079 0.7870
3.750 0.5746 0.00812 0.00245 -0.0398 0.2379 0.7940
4.000 0.5927 0.00915 0.00293 -0.0386 0.1086 0.8005
4.250 0.6139 0.00984 0.00333 -0.0377 0.0440 0.8075
4.500 0.6387 0.01019 0.00365 -0.0373 0.0327 0.8144
4.750 0.6643 0.01041 0.00392 -0.0370 0.0298 0.8215
5.000 0.6882 0.01083 0.00436 -0.0364 0.0252 0.8289
5.250 0.7135 0.01104 0.00462 -0.0361 0.0238 0.8361
5.500 0.7384 0.01132 0.00494 -0.0357 0.0223 0.8437
5.750 0.7623 0.01163 0.00529 -0.0351 0.0208 0.8515
6.000 0.7827 0.01229 0.00602 -0.0340 0.0192 0.8601
6.250 0.8056 0.01265 0.00646 -0.0332 0.0186 0.8690
6.500 0.8283 0.01301 0.00688 -0.0324 0.0181 0.8778
7.000 0.8713 0.01383 0.00784 -0.0304 0.0169 0.8974
7.250 0.8926 0.01418 0.00823 -0.0294 0.0162 0.9081
7.500 0.9126 0.01457 0.00867 -0.0282 0.0156 0.9200
7.750 0.9287 0.01518 0.00935 -0.0263 0.0150 0.9345
8.000 0.9368 0.01648 0.01079 -0.0230 0.0144 0.9571
8.250 0.9635 0.01720 0.01161 -0.0234 0.0142 1.0000
8.500 0.9857 0.01781 0.01227 -0.0229 0.0140 1.0000
8.750 1.0069 0.01856 0.01308 -0.0221 0.0137 1.0000
9.000 1.0275 0.01940 0.01398 -0.0214 0.0134 1.0000
9.250 1.0479 0.02022 0.01487 -0.0206 0.0131 1.0000
9.500 1.0679 0.02108 0.01580 -0.0197 0.0128 1.0000
9.750 1.0866 0.02170 0.01647 -0.0187 0.0124 1.0000
10.000 1.1032 0.02229 0.01712 -0.0173 0.0120 1.0000
10.250 1.1192 0.02311 0.01801 -0.0159 0.0118 1.0000
10.500 1.1341 0.02394 0.01889 -0.0144 0.0116 1.0000
10.750 1.1482 0.02500 0.02001 -0.0128 0.0113 1.0000
11.000 1.1607 0.02712 0.02227 -0.0115 0.0110 1.0000
11.250 1.1655 0.03087 0.02638 -0.0094 0.0107 1.0000
11.500 1.1721 0.03200 0.02765 -0.0071 0.0106 1.0000
11.750 1.1779 0.03323 0.02902 -0.0050 0.0105 1.0000
12.000 1.1813 0.03482 0.03078 -0.0028 0.0103 1.0000
12.250 1.1811 0.03692 0.03307 -0.0007 0.0102 1.0000
12.500 1.1786 0.03922 0.03555 0.0014 0.0100 1.0000
12.750 1.1715 0.04209 0.03864 0.0033 0.0099 1.0000
13.000 1.1710 0.04408 0.04075 0.0045 0.0096 1.0000
13.250 1.1632 0.04708 0.04393 0.0056 0.0095 1.0000
13.500 1.1362 0.05269 0.04983 0.0066 0.0095 1.0000
13.750 1.1143 0.05790 0.05527 0.0064 0.0095 1.0000
14.000 1.0954 0.06306 0.06060 0.0054 0.0094 1.0000
14.250 1.0588 0.07148 0.06928 0.0025 0.0094 1.0000
14.500 1.0198 0.08152 0.07955 -0.0025 0.0095 1.0000
14.750 0.9678 0.09670 0.09497 -0.0122 0.0098 1.0000
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Polar data table (+)
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