NACA 66(1)-212 (naca661212-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 66(1)-212 (naca661212-il) Reynolds number: 50,000 Max Cl/Cd: 22.25 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca661212-il-50000-n5.txt Download as CSV file: xf-naca661212-il-50000-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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.500 -0.4959 0.11247 0.10507 -0.0456 1.0000 0.0634
-11.250 -0.4933 0.10832 0.10094 -0.0464 1.0000 0.0617
-11.000 -0.4953 0.10362 0.09630 -0.0482 1.0000 0.0600
-10.750 -0.5007 0.09840 0.09114 -0.0508 1.0000 0.0584
-10.500 -0.5124 0.09192 0.08474 -0.0549 1.0000 0.0566
-10.250 -0.5384 0.08489 0.07775 -0.0595 1.0000 0.0546
-9.750 -0.6114 0.07793 0.07068 -0.0574 1.0000 0.0523
-9.500 -0.6288 0.07570 0.06847 -0.0538 1.0000 0.0521
-9.250 -0.6448 0.07346 0.06623 -0.0501 1.0000 0.0518
-9.000 -0.6627 0.07132 0.06404 -0.0460 1.0000 0.0516
-8.750 -0.6790 0.06910 0.06174 -0.0418 1.0000 0.0514
-8.500 -0.6928 0.06678 0.05931 -0.0379 1.0000 0.0511
-8.250 -0.7047 0.06429 0.05665 -0.0340 1.0000 0.0509
-8.000 -0.7140 0.06167 0.05383 -0.0303 1.0000 0.0508
-7.750 -0.7205 0.05904 0.05093 -0.0268 1.0000 0.0508
-7.500 -0.7250 0.05639 0.04793 -0.0234 1.0000 0.0512
-7.250 -0.7259 0.05383 0.04494 -0.0201 1.0000 0.0519
-7.000 -0.7235 0.05147 0.04208 -0.0170 1.0000 0.0525
-6.750 -0.7166 0.04852 0.03895 -0.0150 1.0000 0.0534
-6.500 -0.7031 0.04581 0.03591 -0.0136 0.9988 0.0539
-6.250 -0.6817 0.04309 0.03276 -0.0134 0.9959 0.0544
-6.000 -0.6584 0.04069 0.02999 -0.0133 0.9931 0.0552
-5.750 -0.6339 0.03863 0.02762 -0.0132 0.9902 0.0565
-5.500 -0.6078 0.03696 0.02564 -0.0134 0.9874 0.0597
-5.250 -0.5793 0.03541 0.02368 -0.0136 0.9850 0.0626
-5.000 -0.5516 0.03401 0.02195 -0.0133 0.9826 0.0643
-4.750 -0.5228 0.03261 0.02049 -0.0132 0.9808 0.0665
-4.500 -0.4952 0.03165 0.01949 -0.0132 0.9787 0.0715
-4.250 -0.4665 0.03092 0.01852 -0.0132 0.9765 0.0771
-4.000 -0.4414 0.03002 0.01754 -0.0129 0.9740 0.0816
-3.750 -0.4205 0.02926 0.01670 -0.0120 0.9707 0.0883
-3.500 -0.3993 0.02850 0.01591 -0.0114 0.9676 0.0999
-3.250 -0.3774 0.02771 0.01514 -0.0110 0.9650 0.1160
-3.000 -0.3600 0.02631 0.01427 -0.0102 0.9622 0.1843
-2.750 -0.3695 0.02484 0.01573 -0.0006 0.9587 0.7271
-2.500 -0.2451 0.02978 0.02017 -0.0059 0.9673 0.9273
-2.250 -0.2071 0.02975 0.01979 -0.0087 0.9652 0.9383
-2.000 -0.1641 0.02965 0.01940 -0.0127 0.9635 0.9444
-1.750 -0.1375 0.02954 0.01907 -0.0135 0.9603 0.9522
-1.500 -0.1022 0.02943 0.01877 -0.0161 0.9577 0.9576
-1.250 -0.0727 0.02941 0.01860 -0.0177 0.9546 0.9640
-1.000 -0.0350 0.02938 0.01843 -0.0208 0.9520 0.9683
-0.750 -0.0027 0.02941 0.01833 -0.0229 0.9493 0.9735
-0.500 0.0256 0.02938 0.01822 -0.0243 0.9455 0.9783
-0.250 0.0565 0.02942 0.01819 -0.0261 0.9418 0.9827
0.000 0.0890 0.02952 0.01824 -0.0283 0.9384 0.9866
0.250 0.1231 0.02963 0.01831 -0.0308 0.9350 0.9902
0.500 0.1481 0.02971 0.01840 -0.0315 0.9301 0.9946
0.750 0.1792 0.02986 0.01855 -0.0334 0.9258 0.9984
1.000 0.2096 0.03007 0.01879 -0.0351 0.9218 1.0000
1.250 0.2199 0.03022 0.01897 -0.0329 0.9148 1.0000
1.500 0.2410 0.03043 0.01923 -0.0327 0.9091 1.0000
1.750 0.2589 0.03064 0.01950 -0.0319 0.9028 1.0000
2.000 0.2745 0.03084 0.01976 -0.0306 0.8956 1.0000
2.250 0.2979 0.03110 0.02010 -0.0307 0.8896 1.0000
2.500 0.3092 0.03129 0.02039 -0.0286 0.8810 1.0000
2.750 0.3313 0.03154 0.02075 -0.0283 0.8742 1.0000
3.000 0.3450 0.03175 0.02106 -0.0265 0.8652 1.0000
3.250 0.3604 0.03197 0.02140 -0.0250 0.8563 1.0000
3.500 0.3855 0.03219 0.02180 -0.0251 0.8482 1.0000
3.750 0.3957 0.03236 0.02210 -0.0225 0.8370 1.0000
4.000 0.4152 0.03253 0.02244 -0.0214 0.8266 1.0000
4.250 0.4479 0.03263 0.02278 -0.0224 0.8173 1.0000
4.500 0.4625 0.03269 0.02306 -0.0203 0.8041 1.0000
5.000 0.5709 0.02728 0.01841 -0.0201 0.7086 1.0000
5.250 0.5576 0.02659 0.01775 -0.0119 0.6640 1.0000
5.500 0.5464 0.02641 0.01761 -0.0050 0.6105 1.0000
5.750 0.5843 0.02626 0.01462 -0.0011 0.1669 1.0000
6.000 0.5810 0.02762 0.01550 0.0032 0.1217 1.0000
6.250 0.5874 0.02879 0.01652 0.0061 0.1041 1.0000
6.500 0.5982 0.02993 0.01762 0.0083 0.0929 1.0000
6.750 0.6120 0.03111 0.01877 0.0099 0.0834 1.0000
7.000 0.6317 0.03218 0.01997 0.0111 0.0765 1.0000
7.250 0.6622 0.03356 0.02130 0.0109 0.0711 1.0000
7.500 0.7075 0.03487 0.02292 0.0088 0.0641 1.0000
7.750 0.7622 0.03720 0.02530 0.0049 0.0593 1.0000
8.000 0.8020 0.03955 0.02799 0.0034 0.0568 1.0000
8.250 0.8284 0.04171 0.03054 0.0035 0.0539 1.0000
8.500 0.8501 0.04393 0.03309 0.0041 0.0514 1.0000
8.750 0.8699 0.04654 0.03602 0.0049 0.0504 1.0000
9.000 0.8856 0.04931 0.03912 0.0061 0.0497 1.0000
9.250 0.8971 0.05221 0.04236 0.0076 0.0492 1.0000
9.500 0.9044 0.05523 0.04573 0.0096 0.0490 1.0000
9.750 0.9096 0.05831 0.04909 0.0115 0.0485 1.0000
10.000 0.9115 0.06150 0.05253 0.0134 0.0479 1.0000
10.250 0.9110 0.06510 0.05632 0.0152 0.0473 1.0000
10.500 0.9000 0.06802 0.05953 0.0183 0.0470 1.0000
10.750 0.8847 0.07094 0.06272 0.0214 0.0468 1.0000
11.000 0.8690 0.07421 0.06621 0.0236 0.0467 1.0000
11.250 0.8522 0.07778 0.06999 0.0251 0.0467 1.0000
11.500 0.8342 0.08177 0.07415 0.0257 0.0467 1.0000
11.750 0.8170 0.08617 0.07869 0.0255 0.0469 1.0000
12.000 0.7991 0.09110 0.08374 0.0243 0.0470 1.0000
12.250 0.7832 0.09642 0.08914 0.0224 0.0472 1.0000
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Polar data table (+)
Polar graphs
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