NACA 66(1)-212 (naca661212-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 66(1)-212 (naca661212-il) Reynolds number: 500,000 Max Cl/Cd: 62.81 at α=2.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca661212-il-500000-n5.txt Download as CSV file: xf-naca661212-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 66(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
------ -------- --------- --------- -------- -------- --------
-12.750 -0.5439 0.10670 0.10431 -0.0407 1.0000 0.0097
-12.500 -0.5490 0.10130 0.09893 -0.0433 1.0000 0.0098
-12.000 -0.8189 0.04237 0.03918 -0.0682 1.0000 0.0094
-11.500 -0.7949 0.04023 0.03691 -0.0693 0.9749 0.0097
-11.250 -0.7794 0.03834 0.03486 -0.0712 0.9615 0.0099
-11.000 -0.7712 0.03627 0.03257 -0.0711 0.9468 0.0101
-10.750 -0.7743 0.03393 0.02994 -0.0682 0.9316 0.0103
-10.500 -0.7710 0.03205 0.02781 -0.0657 0.9206 0.0106
-10.250 -0.7695 0.02942 0.02483 -0.0628 0.9106 0.0109
-10.000 -0.7624 0.02710 0.02217 -0.0605 0.9030 0.0113
-9.750 -0.7509 0.02507 0.01979 -0.0587 0.8962 0.0118
-9.500 -0.7348 0.02369 0.01812 -0.0573 0.8908 0.0123
-9.250 -0.7170 0.02242 0.01662 -0.0562 0.8853 0.0127
-9.000 -0.6989 0.02126 0.01531 -0.0552 0.8802 0.0131
-8.750 -0.6785 0.02061 0.01456 -0.0544 0.8758 0.0134
-8.500 -0.6572 0.01992 0.01378 -0.0537 0.8710 0.0138
-8.250 -0.6355 0.01922 0.01296 -0.0531 0.8665 0.0141
-8.000 -0.6132 0.01850 0.01212 -0.0524 0.8625 0.0146
-7.750 -0.5904 0.01781 0.01131 -0.0519 0.8588 0.0152
-7.500 -0.5672 0.01718 0.01058 -0.0514 0.8548 0.0158
-7.250 -0.5439 0.01658 0.00987 -0.0509 0.8512 0.0163
-7.000 -0.5206 0.01600 0.00917 -0.0504 0.8480 0.0166
-6.750 -0.4989 0.01517 0.00826 -0.0496 0.8448 0.0172
-6.500 -0.4764 0.01457 0.00763 -0.0490 0.8413 0.0177
-6.250 -0.4533 0.01412 0.00715 -0.0485 0.8380 0.0183
-6.000 -0.4298 0.01372 0.00670 -0.0480 0.8348 0.0189
-5.750 -0.4060 0.01336 0.00628 -0.0475 0.8321 0.0198
-5.500 -0.3817 0.01303 0.00592 -0.0471 0.8289 0.0208
-5.250 -0.3577 0.01267 0.00552 -0.0466 0.8258 0.0217
-5.000 -0.3332 0.01236 0.00514 -0.0462 0.8230 0.0223
-4.750 -0.3108 0.01183 0.00458 -0.0455 0.8203 0.0238
-4.500 -0.2862 0.01153 0.00425 -0.0452 0.8180 0.0251
-4.250 -0.2610 0.01127 0.00396 -0.0449 0.8157 0.0268
-4.000 -0.2353 0.01105 0.00371 -0.0447 0.8132 0.0286
-3.750 -0.2093 0.01087 0.00351 -0.0446 0.8107 0.0301
-3.500 -0.1841 0.01058 0.00321 -0.0443 0.8083 0.0338
-3.250 -0.1581 0.01038 0.00299 -0.0442 0.8059 0.0370
-3.000 -0.1317 0.01022 0.00280 -0.0441 0.8038 0.0416
-2.750 -0.1060 0.00998 0.00262 -0.0439 0.8018 0.0580
-2.500 -0.0832 0.00942 0.00241 -0.0434 0.7994 0.1498
-2.250 -0.0644 0.00845 0.00213 -0.0426 0.7969 0.3345
-2.000 -0.0519 0.00699 0.00186 -0.0405 0.7943 0.6375
-1.750 -0.0265 0.00691 0.00198 -0.0400 0.7923 0.7080
-1.500 0.0007 0.00695 0.00206 -0.0398 0.7905 0.7357
-1.250 0.0286 0.00699 0.00209 -0.0398 0.7889 0.7493
-1.000 0.0566 0.00705 0.00212 -0.0399 0.7872 0.7610
-0.750 0.0842 0.00710 0.00220 -0.0399 0.7850 0.7716
-0.500 0.1120 0.00714 0.00227 -0.0399 0.7830 0.7790
-0.250 0.1405 0.00716 0.00228 -0.0402 0.7811 0.7818
0.000 0.1692 0.00716 0.00228 -0.0405 0.7792 0.7838
0.250 0.1978 0.00718 0.00228 -0.0409 0.7774 0.7857
0.500 0.2266 0.00719 0.00228 -0.0412 0.7755 0.7877
0.750 0.2554 0.00720 0.00227 -0.0416 0.7728 0.7897
1.000 0.2832 0.00719 0.00230 -0.0417 0.7680 0.7915
1.250 0.3108 0.00715 0.00227 -0.0417 0.7605 0.7933
1.500 0.3384 0.00713 0.00226 -0.0417 0.7523 0.7952
1.750 0.3661 0.00712 0.00225 -0.0417 0.7443 0.7971
2.000 0.3932 0.00710 0.00224 -0.0416 0.7317 0.7992
2.250 0.4198 0.00709 0.00220 -0.0413 0.7145 0.8015
2.500 0.4455 0.00711 0.00216 -0.0409 0.6858 0.8037
2.750 0.4648 0.00740 0.00213 -0.0392 0.5917 0.8060
3.000 0.4710 0.00859 0.00256 -0.0353 0.4268 0.8088
3.250 0.4800 0.00976 0.00304 -0.0323 0.2680 0.8120
3.500 0.4943 0.01065 0.00344 -0.0303 0.1524 0.8151
3.750 0.5116 0.01137 0.00381 -0.0288 0.0713 0.8181
4.000 0.5333 0.01178 0.00409 -0.0279 0.0433 0.8206
4.250 0.5563 0.01206 0.00436 -0.0272 0.0356 0.8230
4.500 0.5799 0.01230 0.00463 -0.0266 0.0324 0.8257
4.750 0.6028 0.01259 0.00494 -0.0259 0.0293 0.8287
5.000 0.6248 0.01296 0.00533 -0.0251 0.0265 0.8319
5.250 0.6482 0.01322 0.00563 -0.0245 0.0254 0.8351
5.500 0.6703 0.01351 0.00598 -0.0236 0.0238 0.8382
5.750 0.6918 0.01384 0.00636 -0.0227 0.0223 0.8417
6.000 0.7125 0.01423 0.00677 -0.0216 0.0208 0.8455
6.250 0.7312 0.01477 0.00734 -0.0203 0.0195 0.8495
6.500 0.7513 0.01510 0.00773 -0.0191 0.0187 0.8529
6.750 0.7701 0.01546 0.00817 -0.0177 0.0177 0.8570
7.000 0.7881 0.01589 0.00865 -0.0161 0.0170 0.8617
7.250 0.8061 0.01635 0.00916 -0.0146 0.0164 0.8662
7.500 0.8238 0.01680 0.00967 -0.0131 0.0159 0.8710
7.750 0.8411 0.01733 0.01024 -0.0116 0.0154 0.8768
8.000 0.8567 0.01801 0.01099 -0.0098 0.0149 0.8825
8.250 0.8714 0.01885 0.01191 -0.0079 0.0145 0.8889
8.500 0.8891 0.01949 0.01264 -0.0066 0.0142 0.8952
8.750 0.9059 0.02020 0.01346 -0.0050 0.0140 0.9019
9.250 0.9407 0.02175 0.01524 -0.0023 0.0134 0.9168
9.500 0.9581 0.02248 0.01608 -0.0010 0.0130 0.9255
9.750 0.9745 0.02310 0.01681 0.0005 0.0125 0.9363
10.000 0.9921 0.02393 0.01776 0.0016 0.0122 0.9493
10.500 1.0363 0.02583 0.01989 0.0014 0.0117 1.0000
10.750 1.0524 0.02686 0.02103 0.0024 0.0115 1.0000
11.000 1.0672 0.02792 0.02217 0.0035 0.0113 1.0000
11.250 1.0804 0.02925 0.02363 0.0048 0.0110 1.0000
11.500 1.0902 0.03131 0.02588 0.0063 0.0108 1.0000
11.750 1.1008 0.03261 0.02736 0.0077 0.0106 1.0000
12.000 1.1083 0.03442 0.02939 0.0094 0.0104 1.0000
12.250 1.1129 0.03643 0.03163 0.0112 0.0102 1.0000
12.500 1.1145 0.03864 0.03407 0.0131 0.0100 1.0000
12.750 1.1118 0.04128 0.03696 0.0151 0.0097 1.0000
13.000 1.1048 0.04432 0.04025 0.0171 0.0095 1.0000
13.250 1.0927 0.04794 0.04413 0.0189 0.0094 1.0000
13.500 1.0800 0.05163 0.04807 0.0201 0.0093 1.0000
13.750 1.0620 0.05611 0.05279 0.0209 0.0092 1.0000
14.000 1.0440 0.06081 0.05770 0.0209 0.0090 1.0000
14.250 1.0118 0.06803 0.06517 0.0194 0.0091 1.0000
14.500 0.9560 0.08060 0.07807 0.0139 0.0092 1.0000
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Polar data table (+)
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