NACA 64(1)-212 MOD B (n64212mb-il) Xfoil prediction polar at RE=200,000 Ncrit=9
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Airfoil: NACA 64(1)-212 MOD B (n64212mb-il) Reynolds number: 200,000 Max Cl/Cd: 45.77 at α=11.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-n64212mb-il-200000.txt Download as CSV file: xf-n64212mb-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 64(1)-212 MOD B
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.4436 0.08948 0.08609 -0.0238 1.0000 0.0741
-10.250 -0.4392 0.08598 0.08260 -0.0243 1.0000 0.0758
-10.000 -0.4442 0.08087 0.07751 -0.0265 1.0000 0.0779
-9.750 -0.4686 0.07203 0.06870 -0.0324 1.0000 0.0802
-9.500 -0.6601 0.06581 0.06194 -0.0424 1.0000 0.0731
-9.250 -0.6450 0.06324 0.05944 -0.0419 1.0000 0.0745
-9.000 -0.6451 0.06040 0.05656 -0.0414 1.0000 0.0760
-8.750 -0.6488 0.05743 0.05348 -0.0407 1.0000 0.0783
-8.250 -0.6686 0.05079 0.04629 -0.0377 1.0000 0.0855
-8.000 -0.6565 0.04830 0.04386 -0.0365 1.0000 0.0873
-7.750 -0.6889 0.03745 0.03126 -0.0284 1.0000 0.0520
-7.500 -0.6776 0.03501 0.02884 -0.0261 1.0000 0.0503
-7.250 -0.6713 0.03252 0.02619 -0.0234 1.0000 0.0492
-7.000 -0.6632 0.02989 0.02327 -0.0206 1.0000 0.0472
-6.750 -0.6440 0.02678 0.01950 -0.0193 0.9985 0.0449
-6.500 -0.6070 0.02476 0.01724 -0.0213 0.9945 0.0449
-6.250 -0.5710 0.02311 0.01547 -0.0231 0.9900 0.0455
-6.000 -0.5332 0.02186 0.01417 -0.0252 0.9856 0.0470
-5.750 -0.4949 0.02080 0.01303 -0.0274 0.9814 0.0492
-5.500 -0.4588 0.01985 0.01195 -0.0289 0.9758 0.0510
-5.250 -0.4216 0.01841 0.01057 -0.0309 0.9721 0.0530
-5.000 -0.3861 0.01749 0.00973 -0.0327 0.9668 0.0561
-4.750 -0.3490 0.01686 0.00906 -0.0346 0.9613 0.0608
-4.500 -0.3104 0.01579 0.00811 -0.0373 0.9577 0.0679
-4.250 -0.2785 0.01500 0.00737 -0.0384 0.9508 0.0770
-4.000 -0.2425 0.01412 0.00659 -0.0403 0.9443 0.1000
-3.750 -0.2244 0.01139 0.00574 -0.0403 0.9334 0.4724
-3.500 -0.1911 0.01116 0.00577 -0.0405 0.9244 0.5779
-3.250 -0.1644 0.01115 0.00576 -0.0394 0.9120 0.6138
-3.000 -0.1384 0.01118 0.00581 -0.0382 0.9007 0.6380
-2.750 -0.1114 0.01121 0.00580 -0.0371 0.8907 0.6581
-2.500 -0.0871 0.01132 0.00588 -0.0356 0.8792 0.6815
-2.250 -0.0652 0.01164 0.00632 -0.0329 0.8684 0.7103
-2.000 -0.0414 0.01182 0.00649 -0.0308 0.8588 0.7308
-1.750 -0.0163 0.01175 0.00639 -0.0297 0.8468 0.7379
-1.500 0.0100 0.01168 0.00626 -0.0289 0.8365 0.7464
-1.250 0.0362 0.01159 0.00611 -0.0280 0.8261 0.7538
-1.000 0.0622 0.01151 0.00600 -0.0272 0.8143 0.7610
-0.750 0.0888 0.01139 0.00581 -0.0266 0.8019 0.7686
-0.500 0.1145 0.01129 0.00567 -0.0255 0.7887 0.7752
-0.250 0.1415 0.01117 0.00546 -0.0249 0.7738 0.7837
0.000 0.1666 0.01106 0.00534 -0.0238 0.7570 0.7897
0.250 0.1927 0.01097 0.00520 -0.0230 0.7378 0.7985
0.500 0.2177 0.01087 0.00507 -0.0218 0.7129 0.8057
0.750 0.2426 0.01081 0.00490 -0.0207 0.6784 0.8143
1.000 0.2649 0.01085 0.00468 -0.0189 0.6068 0.8220
1.250 0.2759 0.01204 0.00465 -0.0158 0.3545 0.8316
1.500 0.2958 0.01266 0.00494 -0.0144 0.3068 0.8402
1.750 0.3195 0.01303 0.00516 -0.0136 0.2865 0.8509
2.000 0.3413 0.01334 0.00537 -0.0123 0.2740 0.8598
2.250 0.3651 0.01357 0.00555 -0.0114 0.2642 0.8701
2.500 0.3879 0.01386 0.00577 -0.0103 0.2567 0.8809
2.750 0.4101 0.01404 0.00595 -0.0089 0.2499 0.8916
3.000 0.4318 0.01435 0.00616 -0.0076 0.2439 0.9038
3.250 0.4542 0.01453 0.00636 -0.0063 0.2389 0.9172
3.500 0.4769 0.01470 0.00654 -0.0051 0.2342 0.9312
3.750 0.5021 0.01494 0.00674 -0.0045 0.2299 0.9455
4.000 0.5329 0.01543 0.00713 -0.0051 0.2258 0.9590
4.250 0.5702 0.01571 0.00748 -0.0071 0.2220 0.9712
4.500 0.6117 0.01609 0.00787 -0.0100 0.2175 0.9811
4.750 0.6541 0.01656 0.00828 -0.0133 0.2131 0.9909
5.000 0.6910 0.01735 0.00898 -0.0156 0.2095 1.0000
5.250 0.7086 0.01764 0.00934 -0.0142 0.2076 1.0000
5.500 0.7337 0.01807 0.00982 -0.0141 0.2051 1.0000
5.750 0.7608 0.01855 0.01035 -0.0143 0.2022 1.0000
6.000 0.7883 0.01904 0.01084 -0.0146 0.1991 1.0000
6.250 0.8161 0.01963 0.01138 -0.0149 0.1963 1.0000
6.500 0.8443 0.02071 0.01242 -0.0154 0.1936 1.0000
6.750 0.8711 0.02125 0.01309 -0.0155 0.1915 1.0000
7.000 0.8976 0.02177 0.01375 -0.0155 0.1886 1.0000
7.250 0.9241 0.02235 0.01442 -0.0155 0.1855 1.0000
7.500 0.9503 0.02291 0.01502 -0.0155 0.1825 1.0000
7.750 0.9770 0.02358 0.01563 -0.0156 0.1793 1.0000
8.000 1.0023 0.02459 0.01674 -0.0156 0.1760 1.0000
8.250 1.0264 0.02506 0.01741 -0.0152 0.1725 1.0000
8.500 1.0511 0.02549 0.01793 -0.0150 0.1685 1.0000
8.750 1.0764 0.02585 0.01827 -0.0149 0.1649 1.0000
9.000 1.1013 0.02684 0.01925 -0.0149 0.1612 1.0000
9.250 1.1229 0.02716 0.01982 -0.0142 0.1570 1.0000
9.500 1.1460 0.02742 0.02017 -0.0137 0.1528 1.0000
9.750 1.1711 0.02760 0.02027 -0.0135 0.1491 1.0000
10.000 1.1926 0.02831 0.02112 -0.0130 0.1451 1.0000
10.250 1.2124 0.02855 0.02157 -0.0121 0.1402 1.0000
10.500 1.2353 0.02843 0.02142 -0.0115 0.1361 1.0000
10.750 1.2565 0.02881 0.02182 -0.0109 0.1318 1.0000
11.000 1.2730 0.02894 0.02219 -0.0096 0.1263 1.0000
11.250 1.2934 0.02867 0.02185 -0.0087 0.1219 1.0000
11.500 1.3082 0.02903 0.02240 -0.0072 0.1163 1.0000
11.750 1.3237 0.02892 0.02233 -0.0057 0.1107 1.0000
12.000 1.3363 0.02929 0.02278 -0.0040 0.1049 1.0000
12.250 1.3455 0.02949 0.02305 -0.0018 0.0990 1.0000
12.500 1.3526 0.03021 0.02385 0.0005 0.0928 1.0000
12.750 1.3586 0.03095 0.02458 0.0025 0.0872 1.0000
13.000 1.3640 0.03223 0.02598 0.0042 0.0812 1.0000
13.250 1.3666 0.03363 0.02734 0.0058 0.0766 1.0000
13.500 1.3693 0.03543 0.02929 0.0072 0.0721 1.0000
13.750 1.3699 0.03734 0.03124 0.0083 0.0685 1.0000
14.000 1.3677 0.03973 0.03368 0.0093 0.0656 1.0000
14.250 1.3663 0.04220 0.03633 0.0099 0.0627 1.0000
14.500 1.3633 0.04489 0.03909 0.0102 0.0604 1.0000
14.750 1.3585 0.04791 0.04208 0.0103 0.0583 1.0000
15.000 1.3516 0.05143 0.04580 0.0099 0.0566 1.0000
15.250 1.3434 0.05528 0.04984 0.0090 0.0550 1.0000
15.500 1.3352 0.05931 0.05400 0.0078 0.0536 1.0000
15.750 1.3267 0.06357 0.05836 0.0062 0.0523 1.0000
16.000 1.3195 0.06778 0.06261 0.0046 0.0511 1.0000
16.250 1.3122 0.07221 0.06707 0.0031 0.0498 1.0000
16.500 1.2947 0.07872 0.07382 -0.0005 0.0492 1.0000
16.750 1.2762 0.08586 0.08118 -0.0047 0.0487 1.0000
17.000 1.2544 0.09410 0.08964 -0.0099 0.0482 1.0000
17.250 1.2291 0.10343 0.09918 -0.0159 0.0479 1.0000
17.500 1.1973 0.11442 0.11039 -0.0230 0.0478 1.0000
17.750 1.1418 0.13106 0.12731 -0.0339 0.0484 1.0000
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