NACA 64(1)-212 MOD A (n64212ma-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 64(1)-212 MOD A (n64212ma-il) Reynolds number: 500,000 Max Cl/Cd: 68.67 at α=7.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-n64212ma-il-500000-n5.txt Download as CSV file: xf-n64212ma-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 64(1)-212 MOD A
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
------ -------- --------- --------- -------- -------- --------
-10.500 -0.4156 0.09797 0.09547 -0.0282 1.0000 0.0163
-10.250 -0.4410 0.08738 0.08488 -0.0346 1.0000 0.0175
-10.000 -0.4398 0.08383 0.08135 -0.0364 1.0000 0.0175
-9.750 -0.4371 0.08074 0.07830 -0.0380 1.0000 0.0177
-9.500 -0.4450 0.07515 0.07273 -0.0420 1.0000 0.0177
-9.250 -0.4495 0.06702 0.06456 -0.0528 0.9631 0.0178
-9.000 -0.4575 0.05953 0.05685 -0.0624 0.9178 0.0179
-8.750 -0.4626 0.05654 0.05369 -0.0624 0.8909 0.0180
-8.500 -0.4674 0.05318 0.05015 -0.0619 0.8718 0.0182
-7.500 -0.4813 0.02891 0.02414 -0.0569 0.8219 0.0207
-7.250 -0.4620 0.02756 0.02261 -0.0561 0.8104 0.0209
-7.000 -0.4402 0.02659 0.02152 -0.0556 0.7993 0.0211
-6.500 -0.3947 0.02491 0.01957 -0.0546 0.7746 0.0216
-6.250 -0.3724 0.02352 0.01796 -0.0540 0.7626 0.0220
-6.000 -0.3507 0.02106 0.01515 -0.0532 0.7509 0.0227
-5.750 -0.3281 0.01868 0.01236 -0.0524 0.7397 0.0233
-5.500 -0.3035 0.01714 0.01052 -0.0518 0.7271 0.0237
-5.250 -0.2780 0.01619 0.00931 -0.0513 0.7136 0.0241
-5.000 -0.2526 0.01548 0.00850 -0.0508 0.6979 0.0244
-4.750 -0.2265 0.01502 0.00797 -0.0505 0.6804 0.0247
-4.500 -0.2003 0.01470 0.00755 -0.0501 0.6609 0.0250
-4.250 -0.1742 0.01437 0.00710 -0.0497 0.6390 0.0255
-4.000 -0.1482 0.01403 0.00662 -0.0493 0.6135 0.0260
-3.750 -0.1226 0.01367 0.00609 -0.0488 0.5818 0.0265
-3.500 -0.0974 0.01339 0.00559 -0.0482 0.5394 0.0269
-3.250 -0.0760 0.01369 0.00527 -0.0472 0.3822 0.0272
-3.000 -0.0553 0.01431 0.00517 -0.0464 0.1833 0.0276
-2.500 -0.0039 0.01401 0.00459 -0.0456 0.1079 0.0283
-2.250 0.0229 0.01383 0.00439 -0.0454 0.1044 0.0288
-2.000 0.0500 0.01367 0.00420 -0.0452 0.1026 0.0294
-1.750 0.0771 0.01354 0.00405 -0.0450 0.1011 0.0302
-1.500 0.1043 0.01342 0.00390 -0.0448 0.1000 0.0311
-1.250 0.1316 0.01331 0.00375 -0.0447 0.0991 0.0318
-1.000 0.1589 0.01316 0.00361 -0.0445 0.0984 0.0325
-0.750 0.1864 0.01308 0.00352 -0.0444 0.0978 0.0334
-0.500 0.2139 0.01302 0.00345 -0.0443 0.0972 0.0344
-0.250 0.2415 0.01298 0.00340 -0.0442 0.0967 0.0356
0.000 0.2690 0.01295 0.00336 -0.0440 0.0963 0.0370
0.250 0.2965 0.01295 0.00336 -0.0439 0.0959 0.0392
0.500 0.3240 0.01297 0.00338 -0.0438 0.0956 0.0422
0.750 0.3514 0.01300 0.00341 -0.0436 0.0952 0.0463
1.000 0.3787 0.01305 0.00346 -0.0435 0.0949 0.0532
1.250 0.4059 0.01308 0.00352 -0.0434 0.0947 0.0685
1.500 0.4316 0.01174 0.00351 -0.0441 0.0944 0.5594
1.750 0.4580 0.01169 0.00369 -0.0438 0.0942 0.6349
2.000 0.4843 0.01179 0.00388 -0.0435 0.0939 0.6752
2.250 0.5110 0.01186 0.00404 -0.0432 0.0934 0.7080
2.500 0.5374 0.01193 0.00420 -0.0427 0.0924 0.7411
2.750 0.5636 0.01204 0.00437 -0.0423 0.0914 0.7654
3.000 0.5901 0.01219 0.00453 -0.0419 0.0907 0.7792
3.250 0.6165 0.01236 0.00470 -0.0416 0.0901 0.7874
3.500 0.6427 0.01254 0.00488 -0.0413 0.0896 0.7963
4.000 0.6945 0.01295 0.00528 -0.0405 0.0883 0.8135
4.250 0.7209 0.01309 0.00544 -0.0402 0.0876 0.8224
4.500 0.7470 0.01324 0.00562 -0.0398 0.0869 0.8308
4.750 0.7726 0.01340 0.00580 -0.0394 0.0860 0.8407
5.000 0.7981 0.01357 0.00599 -0.0389 0.0853 0.8504
5.250 0.8230 0.01374 0.00619 -0.0383 0.0845 0.8610
5.500 0.8477 0.01392 0.00639 -0.0378 0.0838 0.8713
5.750 0.8719 0.01409 0.00659 -0.0370 0.0830 0.8833
6.000 0.8958 0.01421 0.00677 -0.0362 0.0818 0.8962
6.250 0.9191 0.01435 0.00697 -0.0353 0.0805 0.9107
6.500 0.9419 0.01447 0.00713 -0.0343 0.0792 0.9275
6.750 0.9652 0.01461 0.00732 -0.0334 0.0776 0.9496
7.000 0.9961 0.01478 0.00754 -0.0342 0.0741 1.0000
7.250 1.0232 0.01490 0.00747 -0.0343 0.0547 1.0000
7.500 1.0459 0.01538 0.00792 -0.0337 0.0519 1.0000
7.750 1.0682 0.01588 0.00843 -0.0330 0.0498 1.0000
8.000 1.0915 0.01626 0.00884 -0.0324 0.0481 1.0000
8.250 1.1141 0.01669 0.00928 -0.0318 0.0464 1.0000
8.500 1.1373 0.01702 0.00965 -0.0312 0.0443 1.0000
8.750 1.1603 0.01734 0.01000 -0.0306 0.0402 1.0000
9.000 1.1811 0.01784 0.01047 -0.0297 0.0362 1.0000
9.250 1.2014 0.01833 0.01094 -0.0288 0.0345 1.0000
9.500 1.2213 0.01880 0.01142 -0.0278 0.0337 1.0000
9.750 1.2395 0.01928 0.01191 -0.0265 0.0331 1.0000
10.000 1.2566 0.01979 0.01244 -0.0251 0.0325 1.0000
10.250 1.2731 0.02033 0.01301 -0.0236 0.0321 1.0000
10.500 1.2889 0.02092 0.01363 -0.0222 0.0317 1.0000
10.750 1.3044 0.02152 0.01428 -0.0207 0.0315 1.0000
11.000 1.3195 0.02217 0.01497 -0.0193 0.0312 1.0000
11.250 1.3338 0.02287 0.01572 -0.0179 0.0309 1.0000
11.500 1.3474 0.02365 0.01654 -0.0165 0.0306 1.0000
11.750 1.3601 0.02450 0.01745 -0.0151 0.0303 1.0000
12.000 1.3719 0.02544 0.01845 -0.0138 0.0300 1.0000
12.250 1.3821 0.02652 0.01958 -0.0124 0.0295 1.0000
12.500 1.3909 0.02773 0.02085 -0.0110 0.0292 1.0000
12.750 1.3993 0.02901 0.02220 -0.0098 0.0290 1.0000
13.000 1.4062 0.03046 0.02370 -0.0086 0.0288 1.0000
13.250 1.4158 0.03174 0.02506 -0.0076 0.0286 1.0000
13.500 1.4239 0.03316 0.02657 -0.0068 0.0284 1.0000
13.750 1.4309 0.03475 0.02824 -0.0060 0.0282 1.0000
14.000 1.4368 0.03648 0.03005 -0.0053 0.0281 1.0000
14.250 1.4416 0.03837 0.03203 -0.0047 0.0279 1.0000
14.500 1.4457 0.04040 0.03415 -0.0043 0.0276 1.0000
14.750 1.4485 0.04262 0.03646 -0.0040 0.0274 1.0000
15.000 1.4498 0.04510 0.03903 -0.0039 0.0272 1.0000
15.250 1.4496 0.04782 0.04184 -0.0040 0.0270 1.0000
15.500 1.4481 0.05081 0.04492 -0.0044 0.0268 1.0000
15.750 1.4452 0.05411 0.04833 -0.0050 0.0267 1.0000
16.000 1.4408 0.05776 0.05208 -0.0059 0.0266 1.0000
16.250 1.4350 0.06177 0.05620 -0.0071 0.0265 1.0000
16.500 1.4273 0.06627 0.06080 -0.0088 0.0264 1.0000
16.750 1.4177 0.07123 0.06587 -0.0108 0.0262 1.0000
17.000 1.4078 0.07651 0.07126 -0.0132 0.0262 1.0000
17.250 1.3960 0.08234 0.07720 -0.0160 0.0261 1.0000
17.500 1.3861 0.08816 0.08317 -0.0190 0.0260 1.0000
17.750 1.3750 0.09440 0.08955 -0.0224 0.0259 1.0000
18.000 1.3630 0.10098 0.09626 -0.0260 0.0258 1.0000
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