NACA 65(1)-212 (naca651212-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 65(1)-212 (naca651212-il) Reynolds number: 500,000 Max Cl/Cd: 66.05 at α=3° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca651212-il-500000-n5.txt Download as CSV file: xf-naca651212-il-500000-n5.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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.000 -0.8198 0.05598 0.05318 -0.0551 1.0000 0.0094
-12.750 -0.8437 0.05012 0.04713 -0.0577 1.0000 0.0094
-12.500 -0.8547 0.04653 0.04340 -0.0585 1.0000 0.0095
-12.250 -0.8528 0.04479 0.04160 -0.0586 1.0000 0.0096
-12.000 -0.8706 0.04093 0.03752 -0.0579 1.0000 0.0096
-11.750 -0.8793 0.03833 0.03475 -0.0565 1.0000 0.0097
-11.500 -0.8690 0.03798 0.03440 -0.0555 1.0000 0.0099
-11.250 -0.8779 0.03571 0.03194 -0.0528 1.0000 0.0100
-11.000 -0.8774 0.03433 0.03044 -0.0502 1.0000 0.0101
-10.750 -0.8735 0.03263 0.02855 -0.0482 1.0000 0.0104
-10.500 -0.8694 0.03067 0.02636 -0.0460 1.0000 0.0107
-10.250 -0.8598 0.02855 0.02399 -0.0446 0.9963 0.0110
-10.000 -0.8374 0.02614 0.02124 -0.0457 0.9813 0.0115
-9.750 -0.8112 0.02425 0.01906 -0.0470 0.9707 0.0119
-9.500 -0.7828 0.02304 0.01760 -0.0482 0.9610 0.0123
-9.250 -0.7582 0.02147 0.01586 -0.0489 0.9502 0.0129
-9.000 -0.7341 0.02073 0.01503 -0.0490 0.9388 0.0132
-8.750 -0.7114 0.02002 0.01421 -0.0487 0.9278 0.0136
-8.500 -0.6893 0.01928 0.01335 -0.0481 0.9174 0.0139
-8.250 -0.6675 0.01858 0.01253 -0.0474 0.9073 0.0144
-8.000 -0.6456 0.01781 0.01164 -0.0467 0.8980 0.0148
-7.750 -0.6233 0.01717 0.01085 -0.0460 0.8893 0.0153
-7.500 -0.6002 0.01663 0.01021 -0.0454 0.8804 0.0159
-7.250 -0.5770 0.01610 0.00956 -0.0448 0.8725 0.0163
-7.000 -0.5551 0.01533 0.00870 -0.0441 0.8643 0.0167
-6.750 -0.5335 0.01459 0.00788 -0.0433 0.8567 0.0172
-6.500 -0.5102 0.01409 0.00732 -0.0427 0.8488 0.0177
-6.250 -0.4864 0.01366 0.00684 -0.0423 0.8416 0.0183
-6.000 -0.4622 0.01325 0.00636 -0.0419 0.8343 0.0189
-5.750 -0.4377 0.01288 0.00592 -0.0415 0.8280 0.0199
-5.500 -0.4126 0.01254 0.00552 -0.0412 0.8209 0.0208
-5.000 -0.3629 0.01176 0.00461 -0.0405 0.8077 0.0225
-4.750 -0.3378 0.01139 0.00419 -0.0402 0.8014 0.0239
-4.500 -0.3117 0.01112 0.00388 -0.0401 0.7956 0.0254
-4.250 -0.2853 0.01088 0.00359 -0.0400 0.7894 0.0273
-4.000 -0.2587 0.01069 0.00333 -0.0399 0.7838 0.0289
-3.750 -0.2324 0.01040 0.00304 -0.0398 0.7776 0.0336
-3.500 -0.2056 0.01021 0.00281 -0.0398 0.7717 0.0380
-3.250 -0.1788 0.00998 0.00260 -0.0398 0.7664 0.0483
-3.000 -0.1530 0.00956 0.00236 -0.0397 0.7608 0.0961
-2.750 -0.1290 0.00884 0.00206 -0.0396 0.7555 0.2173
-2.500 -0.1059 0.00790 0.00173 -0.0396 0.7501 0.3831
-2.250 -0.0823 0.00718 0.00160 -0.0393 0.7445 0.5474
-1.750 -0.0283 0.00695 0.00164 -0.0391 0.7348 0.6472
-1.500 -0.0003 0.00695 0.00163 -0.0391 0.7296 0.6655
-1.250 0.0277 0.00695 0.00162 -0.0392 0.7250 0.6763
-1.000 0.0563 0.00695 0.00159 -0.0394 0.7202 0.6836
-0.750 0.0848 0.00694 0.00158 -0.0395 0.7153 0.6880
-0.500 0.1132 0.00696 0.00155 -0.0397 0.7107 0.6930
-0.250 0.1419 0.00697 0.00155 -0.0400 0.7062 0.6978
0.000 0.1703 0.00696 0.00156 -0.0402 0.7014 0.7022
0.250 0.1988 0.00698 0.00157 -0.0403 0.6969 0.7072
0.500 0.2274 0.00701 0.00158 -0.0406 0.6927 0.7122
0.750 0.2558 0.00701 0.00162 -0.0408 0.6879 0.7166
1.000 0.2842 0.00703 0.00166 -0.0409 0.6833 0.7217
1.250 0.3126 0.00708 0.00169 -0.0411 0.6793 0.7269
1.500 0.3410 0.00709 0.00176 -0.0413 0.6746 0.7316
1.750 0.3693 0.00711 0.00182 -0.0415 0.6695 0.7370
2.000 0.3973 0.00715 0.00186 -0.0415 0.6592 0.7424
2.250 0.4246 0.00719 0.00191 -0.0414 0.6451 0.7472
2.500 0.4516 0.00725 0.00195 -0.0413 0.6251 0.7529
2.750 0.4772 0.00739 0.00198 -0.0409 0.5877 0.7587
3.000 0.5020 0.00760 0.00206 -0.0403 0.5397 0.7642
3.250 0.5216 0.00829 0.00227 -0.0391 0.4253 0.7703
3.500 0.5384 0.00939 0.00277 -0.0377 0.2837 0.7761
3.750 0.5570 0.01032 0.00323 -0.0365 0.1704 0.7827
4.000 0.5772 0.01110 0.00365 -0.0356 0.0867 0.7894
4.250 0.5997 0.01161 0.00401 -0.0349 0.0476 0.7959
4.500 0.6240 0.01196 0.00433 -0.0345 0.0356 0.8028
4.750 0.6487 0.01223 0.00463 -0.0341 0.0306 0.8090
5.000 0.6730 0.01255 0.00496 -0.0336 0.0272 0.8163
5.250 0.6967 0.01289 0.00536 -0.0330 0.0245 0.8233
5.500 0.7208 0.01319 0.00572 -0.0325 0.0230 0.8312
5.750 0.7442 0.01352 0.00611 -0.0319 0.0214 0.8386
6.000 0.7669 0.01390 0.00654 -0.0311 0.0201 0.8467
6.250 0.7874 0.01444 0.00714 -0.0300 0.0188 0.8547
6.750 0.8300 0.01527 0.00813 -0.0280 0.0174 0.8733
7.000 0.8506 0.01568 0.00861 -0.0269 0.0167 0.8832
7.250 0.8702 0.01615 0.00915 -0.0257 0.0161 0.8939
7.500 0.8886 0.01663 0.00972 -0.0242 0.0156 0.9060
7.750 0.9061 0.01712 0.01027 -0.0226 0.0151 0.9199
8.000 0.9223 0.01765 0.01088 -0.0208 0.0148 0.9368
8.250 0.9407 0.01834 0.01165 -0.0195 0.0144 0.9593
8.500 0.9611 0.01943 0.01281 -0.0191 0.0139 1.0000
8.750 0.9790 0.02017 0.01362 -0.0179 0.0138 1.0000
9.000 0.9967 0.02093 0.01446 -0.0167 0.0136 1.0000
9.250 1.0140 0.02175 0.01537 -0.0155 0.0133 1.0000
9.500 1.0314 0.02252 0.01622 -0.0143 0.0129 1.0000
9.750 1.0482 0.02346 0.01725 -0.0131 0.0126 1.0000
10.000 1.0646 0.02432 0.01820 -0.0119 0.0122 1.0000
10.250 1.0804 0.02536 0.01935 -0.0107 0.0120 1.0000
10.500 1.0954 0.02632 0.02041 -0.0094 0.0117 1.0000
10.750 1.1096 0.02747 0.02166 -0.0081 0.0115 1.0000
11.000 1.1229 0.02856 0.02285 -0.0068 0.0113 1.0000
11.250 1.1350 0.02971 0.02410 -0.0055 0.0111 1.0000
11.500 1.1461 0.03090 0.02538 -0.0042 0.0109 1.0000
11.750 1.1554 0.03232 0.02690 -0.0028 0.0107 1.0000
12.000 1.1617 0.03416 0.02887 -0.0014 0.0105 1.0000
12.250 1.1661 0.03617 0.03109 0.0001 0.0103 1.0000
12.500 1.1707 0.03804 0.03315 0.0015 0.0101 1.0000
12.750 1.1729 0.04020 0.03551 0.0027 0.0100 1.0000
13.000 1.1716 0.04280 0.03832 0.0040 0.0098 1.0000
13.250 1.1696 0.04545 0.04119 0.0049 0.0096 1.0000
13.500 1.1619 0.04888 0.04485 0.0056 0.0095 1.0000
13.750 1.1494 0.05301 0.04923 0.0060 0.0094 1.0000
14.000 1.1363 0.05738 0.05381 0.0057 0.0093 1.0000
14.250 1.1204 0.06234 0.05900 0.0047 0.0092 1.0000
14.500 1.0968 0.06884 0.06574 0.0027 0.0092 1.0000
14.750 1.0756 0.07555 0.07265 -0.0002 0.0091 1.0000
15.000 1.0443 0.08501 0.08235 -0.0054 0.0092 1.0000
15.250 1.0041 0.09814 0.09573 -0.0137 0.0092 1.0000
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