NACA 66(1)-212 (naca661212-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 66(1)-212 (naca661212-il) Reynolds number: 1,000,000 Max Cl/Cd: 70.54 at α=2° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca661212-il-1000000-n5.txt Download as CSV file: xf-naca661212-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.000 -0.9710 0.06210 0.05999 -0.0647 1.0000 0.0063
-15.750 -1.0094 0.05282 0.05047 -0.0701 1.0000 0.0063
-15.500 -1.0364 0.04680 0.04424 -0.0720 1.0000 0.0063
-15.250 -1.0559 0.04231 0.03955 -0.0723 1.0000 0.0063
-15.000 -1.0627 0.03942 0.03651 -0.0718 1.0000 0.0064
-14.750 -1.0665 0.03699 0.03393 -0.0710 1.0000 0.0065
-14.500 -1.0732 0.03439 0.03115 -0.0696 1.0000 0.0066
-14.250 -1.0752 0.03234 0.02895 -0.0681 1.0000 0.0066
-14.000 -1.0729 0.03069 0.02716 -0.0665 1.0000 0.0067
-13.750 -1.0686 0.02924 0.02559 -0.0648 1.0000 0.0067
-13.500 -1.0695 0.02747 0.02367 -0.0625 1.0000 0.0069
-13.250 -1.0486 0.02594 0.02200 -0.0640 0.9758 0.0071
-13.000 -1.0182 0.02509 0.02107 -0.0665 0.9648 0.0073
-12.750 -0.9945 0.02401 0.01986 -0.0677 0.9515 0.0075
-12.500 -0.9766 0.02343 0.01918 -0.0671 0.9375 0.0077
-12.250 -0.9650 0.02264 0.01825 -0.0653 0.9245 0.0078
-12.000 -0.9537 0.02189 0.01738 -0.0633 0.9137 0.0080
-11.750 -0.9410 0.02129 0.01666 -0.0613 0.9043 0.0083
-11.500 -0.9276 0.02069 0.01595 -0.0594 0.8955 0.0085
-11.250 -0.9137 0.02003 0.01516 -0.0575 0.8885 0.0087
-11.000 -0.8961 0.01949 0.01452 -0.0563 0.8819 0.0089
-10.750 -0.8774 0.01900 0.01390 -0.0552 0.8762 0.0091
-10.500 -0.8583 0.01841 0.01320 -0.0542 0.8708 0.0093
-10.250 -0.8401 0.01768 0.01236 -0.0531 0.8652 0.0094
-10.000 -0.8224 0.01689 0.01145 -0.0519 0.8603 0.0098
-9.750 -0.8015 0.01641 0.01092 -0.0511 0.8553 0.0101
-9.500 -0.7800 0.01600 0.01045 -0.0504 0.8504 0.0103
-9.250 -0.7581 0.01560 0.00997 -0.0497 0.8462 0.0106
-9.000 -0.7352 0.01524 0.00956 -0.0492 0.8422 0.0109
-8.750 -0.7123 0.01488 0.00915 -0.0487 0.8382 0.0113
-8.500 -0.6899 0.01445 0.00864 -0.0481 0.8343 0.0116
-8.250 -0.6671 0.01404 0.00816 -0.0475 0.8309 0.0120
-8.000 -0.6440 0.01362 0.00767 -0.0470 0.8275 0.0122
-7.750 -0.6205 0.01325 0.00724 -0.0465 0.8239 0.0124
-7.500 -0.5971 0.01288 0.00681 -0.0460 0.8205 0.0126
-7.000 -0.5514 0.01198 0.00582 -0.0448 0.8142 0.0137
-6.750 -0.5267 0.01170 0.00551 -0.0445 0.8110 0.0142
-6.500 -0.5021 0.01141 0.00519 -0.0442 0.8078 0.0146
-6.250 -0.4774 0.01113 0.00487 -0.0439 0.8049 0.0150
-5.750 -0.4272 0.01060 0.00426 -0.0433 0.7999 0.0161
-5.500 -0.4016 0.01036 0.00399 -0.0432 0.7973 0.0165
-5.250 -0.3762 0.01009 0.00370 -0.0429 0.7947 0.0171
-5.000 -0.3508 0.00983 0.00343 -0.0427 0.7922 0.0184
-4.750 -0.3246 0.00965 0.00324 -0.0426 0.7899 0.0196
-4.500 -0.2984 0.00948 0.00304 -0.0426 0.7878 0.0206
-4.250 -0.2718 0.00931 0.00286 -0.0425 0.7858 0.0217
-4.000 -0.2449 0.00916 0.00270 -0.0426 0.7836 0.0225
-3.750 -0.2186 0.00894 0.00247 -0.0425 0.7812 0.0248
-3.500 -0.1919 0.00878 0.00232 -0.0425 0.7788 0.0267
-3.250 -0.1648 0.00865 0.00218 -0.0425 0.7767 0.0285
-3.000 -0.1376 0.00854 0.00205 -0.0426 0.7748 0.0299
-2.750 -0.1106 0.00841 0.00192 -0.0426 0.7729 0.0339
-2.500 -0.0834 0.00827 0.00181 -0.0427 0.7712 0.0392
-2.250 -0.0568 0.00805 0.00169 -0.0427 0.7694 0.0660
-2.000 -0.0321 0.00760 0.00154 -0.0425 0.7675 0.1511
-1.750 -0.0095 0.00691 0.00135 -0.0421 0.7655 0.2971
-1.500 0.0098 0.00582 0.00107 -0.0413 0.7634 0.5289
-1.250 0.0327 0.00526 0.00103 -0.0407 0.7614 0.6860
-1.000 0.0606 0.00523 0.00106 -0.0408 0.7596 0.7111
-0.500 0.1176 0.00524 0.00110 -0.0413 0.7564 0.7354
-0.250 0.1462 0.00525 0.00114 -0.0415 0.7548 0.7468
0.000 0.1746 0.00526 0.00118 -0.0417 0.7523 0.7550
0.250 0.2034 0.00527 0.00118 -0.0420 0.7485 0.7577
0.500 0.2318 0.00530 0.00116 -0.0423 0.7435 0.7592
0.750 0.2602 0.00528 0.00115 -0.0425 0.7357 0.7608
1.000 0.2882 0.00529 0.00115 -0.0426 0.7282 0.7626
1.250 0.3161 0.00530 0.00115 -0.0428 0.7161 0.7644
1.500 0.3439 0.00532 0.00116 -0.0428 0.7025 0.7664
1.750 0.3711 0.00538 0.00117 -0.0428 0.6849 0.7682
2.000 0.3950 0.00560 0.00119 -0.0421 0.6234 0.7702
2.250 0.4059 0.00673 0.00156 -0.0392 0.4439 0.7725
2.500 0.4224 0.00756 0.00188 -0.0375 0.3185 0.7746
2.750 0.4392 0.00835 0.00220 -0.0358 0.1998 0.7767
3.000 0.4581 0.00899 0.00249 -0.0345 0.1080 0.7789
3.500 0.5041 0.00972 0.00292 -0.0332 0.0351 0.7837
3.750 0.5294 0.00992 0.00310 -0.0329 0.0307 0.7862
4.000 0.5546 0.01012 0.00329 -0.0326 0.0273 0.7885
4.250 0.5800 0.01030 0.00348 -0.0323 0.0260 0.7907
4.500 0.6052 0.01046 0.00368 -0.0320 0.0248 0.7929
4.750 0.6300 0.01066 0.00389 -0.0317 0.0232 0.7954
5.000 0.6543 0.01089 0.00412 -0.0312 0.0213 0.7981
5.250 0.6781 0.01116 0.00439 -0.0307 0.0195 0.8009
5.500 0.7027 0.01136 0.00461 -0.0303 0.0185 0.8036
5.750 0.7267 0.01158 0.00485 -0.0298 0.0171 0.8061
6.000 0.7500 0.01183 0.00510 -0.0292 0.0159 0.8090
6.250 0.7723 0.01216 0.00545 -0.0284 0.0146 0.8123
6.500 0.7951 0.01243 0.00576 -0.0277 0.0142 0.8158
6.750 0.8176 0.01273 0.00609 -0.0270 0.0136 0.8192
7.000 0.8394 0.01303 0.00644 -0.0261 0.0132 0.8226
7.250 0.8607 0.01336 0.00680 -0.0252 0.0128 0.8263
7.500 0.8815 0.01368 0.00716 -0.0242 0.0124 0.8302
7.750 0.9009 0.01402 0.00753 -0.0229 0.0120 0.8341
8.000 0.9192 0.01438 0.00794 -0.0214 0.0117 0.8381
8.250 0.9366 0.01482 0.00843 -0.0198 0.0113 0.8427
8.500 0.9522 0.01543 0.00910 -0.0179 0.0109 0.8477
8.750 0.9684 0.01598 0.00972 -0.0162 0.0107 0.8524
9.000 0.9869 0.01637 0.01019 -0.0148 0.0106 0.8580
9.250 1.0044 0.01686 0.01075 -0.0134 0.0104 0.8638
9.500 1.0213 0.01736 0.01133 -0.0119 0.0102 0.8698
9.750 1.0380 0.01789 0.01194 -0.0104 0.0100 0.8766
10.000 1.0539 0.01849 0.01263 -0.0089 0.0099 0.8832
10.250 1.0694 0.01912 0.01334 -0.0073 0.0097 0.8910
10.500 1.0850 0.01972 0.01404 -0.0057 0.0095 0.8988
10.750 1.1001 0.02037 0.01478 -0.0042 0.0093 0.9080
11.000 1.1158 0.02088 0.01537 -0.0027 0.0091 0.9177
11.250 1.1308 0.02144 0.01600 -0.0011 0.0089 0.9288
11.500 1.1446 0.02209 0.01676 0.0005 0.0087 0.9437
11.750 1.1639 0.02284 0.01761 0.0009 0.0086 0.9663
12.000 1.1822 0.02374 0.01860 0.0012 0.0084 1.0000
12.250 1.1943 0.02479 0.01974 0.0026 0.0082 1.0000
12.500 1.2052 0.02596 0.02100 0.0041 0.0081 1.0000
12.750 1.2117 0.02759 0.02277 0.0060 0.0078 1.0000
13.000 1.2229 0.02870 0.02398 0.0073 0.0078 1.0000
13.250 1.2332 0.02990 0.02528 0.0086 0.0077 1.0000
13.500 1.2433 0.03108 0.02658 0.0099 0.0077 1.0000
13.750 1.2540 0.03220 0.02779 0.0110 0.0075 1.0000
14.000 1.2612 0.03368 0.02938 0.0123 0.0074 1.0000
14.250 1.2653 0.03547 0.03131 0.0137 0.0074 1.0000
14.500 1.2745 0.03674 0.03267 0.0147 0.0072 1.0000
14.750 1.2768 0.03874 0.03481 0.0159 0.0071 1.0000
15.000 1.2805 0.04062 0.03681 0.0169 0.0070 1.0000
15.250 1.2841 0.04253 0.03883 0.0177 0.0068 1.0000
15.500 1.2805 0.04528 0.04173 0.0186 0.0068 1.0000
15.750 1.2802 0.04775 0.04432 0.0191 0.0067 1.0000
16.000 1.2785 0.05049 0.04718 0.0194 0.0066 1.0000
16.250 1.2742 0.05367 0.05049 0.0194 0.0065 1.0000
16.500 1.2739 0.05652 0.05344 0.0191 0.0064 1.0000
16.750 1.2658 0.06058 0.05764 0.0183 0.0063 1.0000
17.000 1.2511 0.06591 0.06313 0.0167 0.0063 1.0000
17.250 1.2440 0.07049 0.06782 0.0148 0.0062 1.0000
17.500 1.2286 0.07682 0.07431 0.0117 0.0062 1.0000
17.750 1.2110 0.08412 0.08177 0.0077 0.0062 1.0000
18.000 1.1545 0.10036 0.09833 -0.0022 0.0063 1.0000
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Polar data table (+)
Polar graphs
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