NACA 64(1)-212 MOD B (n64212mb-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 64(1)-212 MOD B (n64212mb-il) Reynolds number: 1,000,000 Max Cl/Cd: 96.82 at α=10° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-n64212mb-il-1000000.txt Download as CSV file: xf-n64212mb-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.750 -0.8378 0.06576 0.06351 -0.0402 1.0000 0.0142
-13.500 -0.8822 0.05562 0.05311 -0.0470 1.0000 0.0141
-13.250 -0.9216 0.04781 0.04502 -0.0507 1.0000 0.0141
-13.000 -0.9490 0.04236 0.03932 -0.0520 1.0000 0.0140
-12.750 -0.9634 0.03883 0.03559 -0.0518 1.0000 0.0141
-12.500 -0.9814 0.03521 0.03171 -0.0505 1.0000 0.0141
-12.250 -0.9893 0.03285 0.02917 -0.0484 1.0000 0.0142
-12.000 -0.9959 0.03086 0.02700 -0.0455 1.0000 0.0143
-11.750 -0.9935 0.02907 0.02503 -0.0432 1.0000 0.0144
-11.500 -0.9850 0.02749 0.02327 -0.0415 1.0000 0.0146
-11.250 -0.9731 0.02609 0.02172 -0.0400 1.0000 0.0148
-11.000 -0.9571 0.02517 0.02067 -0.0388 1.0000 0.0149
-10.750 -0.9399 0.02436 0.01975 -0.0377 1.0000 0.0151
-10.500 -0.9254 0.02275 0.01795 -0.0363 1.0000 0.0153
-10.250 -0.9109 0.02083 0.01589 -0.0350 1.0000 0.0155
-10.000 -0.8929 0.01973 0.01472 -0.0338 1.0000 0.0157
-9.750 -0.8738 0.01893 0.01389 -0.0327 1.0000 0.0159
-9.500 -0.8549 0.01823 0.01316 -0.0314 1.0000 0.0161
-9.250 -0.8362 0.01765 0.01255 -0.0301 0.9998 0.0163
-9.000 -0.8035 0.01690 0.01175 -0.0315 0.9935 0.0166
-8.750 -0.7706 0.01615 0.01095 -0.0330 0.9879 0.0169
-8.500 -0.7365 0.01541 0.01016 -0.0347 0.9823 0.0172
-8.250 -0.7035 0.01473 0.00944 -0.0361 0.9737 0.0175
-8.000 -0.6716 0.01415 0.00880 -0.0372 0.9634 0.0179
-7.750 -0.6434 0.01368 0.00826 -0.0374 0.9505 0.0182
-7.500 -0.6182 0.01333 0.00784 -0.0369 0.9371 0.0184
-7.250 -0.5977 0.01247 0.00691 -0.0358 0.9236 0.0192
-7.000 -0.5736 0.01211 0.00652 -0.0351 0.9118 0.0197
-6.750 -0.5486 0.01179 0.00616 -0.0345 0.9013 0.0202
-6.500 -0.5235 0.01147 0.00579 -0.0339 0.8918 0.0208
-6.250 -0.4978 0.01115 0.00542 -0.0335 0.8822 0.0213
-6.000 -0.4718 0.01089 0.00510 -0.0331 0.8733 0.0219
-5.750 -0.4467 0.01046 0.00461 -0.0325 0.8620 0.0227
-5.500 -0.4209 0.01014 0.00425 -0.0321 0.8490 0.0238
-5.250 -0.3943 0.00993 0.00399 -0.0317 0.8378 0.0250
-5.000 -0.3672 0.00973 0.00375 -0.0315 0.8281 0.0261
-4.750 -0.3405 0.00941 0.00340 -0.0312 0.8182 0.0282
-4.500 -0.3134 0.00925 0.00319 -0.0309 0.8066 0.0305
-4.250 -0.2863 0.00900 0.00292 -0.0307 0.7939 0.0337
-4.000 -0.2586 0.00884 0.00273 -0.0306 0.7829 0.0369
-3.750 -0.2312 0.00863 0.00250 -0.0304 0.7733 0.0431
-3.500 -0.2034 0.00838 0.00231 -0.0303 0.7634 0.0554
-3.250 -0.1764 0.00803 0.00209 -0.0302 0.7531 0.0947
-3.000 -0.1502 0.00744 0.00184 -0.0302 0.7417 0.1889
-2.750 -0.1249 0.00654 0.00152 -0.0302 0.7302 0.3497
-2.500 -0.0985 0.00600 0.00137 -0.0302 0.7180 0.4718
-2.250 -0.0704 0.00589 0.00132 -0.0301 0.7051 0.5126
-2.000 -0.0420 0.00582 0.00128 -0.0301 0.6914 0.5387
-1.750 -0.0135 0.00579 0.00124 -0.0301 0.6763 0.5575
-1.500 0.0149 0.00580 0.00121 -0.0300 0.6586 0.5707
-1.250 0.0431 0.00582 0.00121 -0.0299 0.6386 0.5914
-1.000 0.0710 0.00585 0.00122 -0.0298 0.6109 0.6183
-0.750 0.0984 0.00599 0.00124 -0.0295 0.5675 0.6350
-0.500 0.1217 0.00673 0.00136 -0.0289 0.3950 0.6436
-0.250 0.1470 0.00728 0.00152 -0.0286 0.2932 0.6511
0.000 0.1745 0.00749 0.00158 -0.0285 0.2559 0.6587
0.250 0.2026 0.00765 0.00164 -0.0285 0.2325 0.6654
0.500 0.2307 0.00776 0.00170 -0.0285 0.2177 0.6723
0.750 0.2591 0.00788 0.00176 -0.0285 0.2073 0.6796
1.000 0.2873 0.00797 0.00182 -0.0285 0.1997 0.6866
1.250 0.3155 0.00808 0.00190 -0.0285 0.1925 0.6945
1.500 0.3440 0.00815 0.00197 -0.0285 0.1884 0.7020
1.750 0.3722 0.00824 0.00206 -0.0285 0.1839 0.7101
2.000 0.4002 0.00838 0.00217 -0.0284 0.1787 0.7177
2.250 0.4284 0.00846 0.00227 -0.0284 0.1762 0.7258
2.500 0.4568 0.00855 0.00236 -0.0284 0.1740 0.7337
2.750 0.4848 0.00863 0.00247 -0.0284 0.1715 0.7419
3.250 0.5405 0.00888 0.00272 -0.0282 0.1657 0.7584
3.750 0.5957 0.00916 0.00304 -0.0280 0.1608 0.7760
4.000 0.6237 0.00926 0.00317 -0.0280 0.1594 0.7847
4.250 0.6513 0.00936 0.00331 -0.0279 0.1578 0.7935
4.500 0.6790 0.00949 0.00346 -0.0278 0.1561 0.8022
4.750 0.7062 0.00962 0.00362 -0.0276 0.1543 0.8111
5.000 0.7334 0.00978 0.00379 -0.0275 0.1523 0.8199
5.250 0.7599 0.00998 0.00402 -0.0272 0.1497 0.8294
5.500 0.7857 0.01027 0.00434 -0.0268 0.1470 0.8389
5.750 0.8129 0.01037 0.00449 -0.0267 0.1463 0.8490
6.000 0.8396 0.01048 0.00466 -0.0264 0.1453 0.8589
6.250 0.8663 0.01062 0.00485 -0.0261 0.1440 0.8691
6.500 0.8927 0.01072 0.00499 -0.0258 0.1421 0.8802
6.750 0.9188 0.01080 0.00511 -0.0254 0.1398 0.8919
7.000 0.9441 0.01094 0.00528 -0.0249 0.1372 0.9046
7.250 0.9670 0.01125 0.00561 -0.0240 0.1335 0.9191
7.500 0.9913 0.01129 0.00572 -0.0232 0.1323 0.9353
7.750 1.0146 0.01133 0.00584 -0.0222 0.1310 0.9576
8.000 1.0463 0.01142 0.00597 -0.0231 0.1289 1.0000
8.250 1.0740 0.01157 0.00613 -0.0232 0.1267 1.0000
8.500 1.1012 0.01177 0.00631 -0.0232 0.1240 1.0000
8.750 1.1266 0.01212 0.00664 -0.0230 0.1202 1.0000
9.000 1.1544 0.01220 0.00677 -0.0231 0.1185 1.0000
9.250 1.1815 0.01235 0.00694 -0.0231 0.1157 1.0000
9.500 1.2079 0.01254 0.00713 -0.0230 0.1122 1.0000
9.750 1.2332 0.01283 0.00740 -0.0228 0.1079 1.0000
10.000 1.2596 0.01301 0.00762 -0.0226 0.1046 1.0000
10.250 1.2848 0.01329 0.00787 -0.0224 0.0993 1.0000
10.500 1.3095 0.01359 0.00817 -0.0221 0.0936 1.0000
10.750 1.3329 0.01401 0.00854 -0.0216 0.0848 1.0000
11.000 1.3550 0.01455 0.00901 -0.0210 0.0743 1.0000
11.250 1.3756 0.01521 0.00960 -0.0202 0.0640 1.0000
11.500 1.3955 0.01590 0.01025 -0.0194 0.0558 1.0000
11.750 1.4148 0.01661 0.01094 -0.0184 0.0495 1.0000
12.000 1.4341 0.01729 0.01162 -0.0175 0.0446 1.0000
12.250 1.4532 0.01793 0.01227 -0.0165 0.0407 1.0000
12.500 1.4702 0.01870 0.01304 -0.0152 0.0370 1.0000
12.750 1.4884 0.01930 0.01368 -0.0141 0.0347 1.0000
13.000 1.5026 0.02005 0.01445 -0.0125 0.0324 1.0000
13.250 1.5148 0.02078 0.01522 -0.0105 0.0305 1.0000
13.500 1.5274 0.02145 0.01595 -0.0086 0.0291 1.0000
13.750 1.5371 0.02233 0.01685 -0.0066 0.0276 1.0000
14.000 1.5441 0.02340 0.01798 -0.0044 0.0261 1.0000
14.250 1.5561 0.02418 0.01883 -0.0029 0.0252 1.0000
14.500 1.5652 0.02519 0.01990 -0.0013 0.0242 1.0000
14.750 1.5715 0.02643 0.02119 0.0004 0.0233 1.0000
15.000 1.5734 0.02805 0.02288 0.0021 0.0222 1.0000
15.250 1.5793 0.02945 0.02437 0.0034 0.0217 1.0000
15.500 1.5860 0.03084 0.02584 0.0045 0.0211 1.0000
15.750 1.5906 0.03248 0.02756 0.0054 0.0205 1.0000
16.000 1.5925 0.03442 0.02959 0.0063 0.0200 1.0000
16.250 1.5909 0.03680 0.03206 0.0069 0.0195 1.0000
16.500 1.5852 0.03972 0.03506 0.0072 0.0189 1.0000
16.750 1.5756 0.04325 0.03871 0.0071 0.0185 1.0000
17.000 1.5659 0.04705 0.04264 0.0064 0.0182 1.0000
17.250 1.5574 0.05101 0.04673 0.0054 0.0181 1.0000
17.500 1.5459 0.05564 0.05150 0.0037 0.0179 1.0000
17.750 1.5231 0.06240 0.05843 0.0005 0.0178 1.0000
18.000 1.4832 0.07317 0.06944 -0.0057 0.0179 1.0000
18.250 1.3889 0.09607 0.09274 -0.0194 0.0186 1.0000
18.500 1.3340 0.11044 0.10731 -0.0278 0.0192 1.0000
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