NACA 64(1)-212 MOD A (n64212ma-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
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Airfoil: NACA 64(1)-212 MOD A (n64212ma-il) Reynolds number: 1,000,000 Max Cl/Cd: 79.07 at α=8.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-n64212ma-il-1000000-n5.txt Download as CSV file: xf-n64212ma-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.750 -0.4618 0.10852 0.10667 -0.0223 1.0000 0.0121
-11.500 -0.4569 0.10544 0.10360 -0.0237 1.0000 0.0123
-10.000 -0.7572 0.02275 0.01849 -0.0586 0.8806 0.0174
-9.750 -0.7406 0.02113 0.01664 -0.0576 0.8682 0.0176
-9.500 -0.7190 0.02050 0.01588 -0.0567 0.8527 0.0178
-9.250 -0.6962 0.01987 0.01516 -0.0561 0.8390 0.0179
-9.000 -0.6728 0.01933 0.01451 -0.0555 0.8275 0.0180
-8.750 -0.6489 0.01880 0.01388 -0.0550 0.8145 0.0181
-8.500 -0.6246 0.01829 0.01327 -0.0545 0.8024 0.0183
-8.250 -0.5999 0.01784 0.01272 -0.0540 0.7899 0.0185
-8.000 -0.5750 0.01732 0.01209 -0.0536 0.7784 0.0187
-7.500 -0.5252 0.01614 0.01067 -0.0527 0.7510 0.0192
-7.250 -0.5002 0.01547 0.00985 -0.0523 0.7392 0.0194
-7.000 -0.4747 0.01482 0.00908 -0.0519 0.7277 0.0197
-6.750 -0.4490 0.01426 0.00839 -0.0515 0.7156 0.0199
-6.500 -0.4231 0.01376 0.00778 -0.0511 0.7013 0.0201
-6.250 -0.3971 0.01335 0.00724 -0.0507 0.6824 0.0203
-6.000 -0.3712 0.01303 0.00677 -0.0503 0.6565 0.0205
-5.500 -0.3196 0.01231 0.00577 -0.0495 0.6040 0.0208
-5.250 -0.2940 0.01207 0.00539 -0.0491 0.5649 0.0211
-5.000 -0.2687 0.01205 0.00511 -0.0487 0.4969 0.0213
-4.750 -0.2492 0.01304 0.00512 -0.0477 0.1779 0.0215
-4.500 -0.2230 0.01304 0.00491 -0.0474 0.1053 0.0218
-4.250 -0.1958 0.01288 0.00471 -0.0472 0.1000 0.0221
-4.000 -0.1684 0.01272 0.00452 -0.0470 0.0978 0.0225
-3.750 -0.1411 0.01253 0.00429 -0.0469 0.0962 0.0229
-3.500 -0.1138 0.01235 0.00407 -0.0467 0.0944 0.0232
-3.250 -0.0863 0.01218 0.00386 -0.0465 0.0933 0.0235
-3.000 -0.0587 0.01202 0.00368 -0.0464 0.0926 0.0237
-2.750 -0.0310 0.01189 0.00351 -0.0463 0.0919 0.0240
-2.500 -0.0033 0.01173 0.00333 -0.0461 0.0912 0.0242
-2.250 0.0243 0.01157 0.00315 -0.0460 0.0905 0.0247
-2.000 0.0521 0.01148 0.00305 -0.0459 0.0899 0.0251
-1.750 0.0800 0.01142 0.00297 -0.0459 0.0893 0.0256
-1.500 0.1079 0.01137 0.00290 -0.0458 0.0887 0.0261
-1.250 0.1359 0.01132 0.00283 -0.0457 0.0883 0.0267
-1.000 0.1640 0.01128 0.00278 -0.0456 0.0879 0.0274
-0.750 0.1921 0.01124 0.00273 -0.0456 0.0875 0.0279
-0.500 0.2201 0.01120 0.00268 -0.0455 0.0871 0.0287
-0.250 0.2482 0.01118 0.00266 -0.0455 0.0867 0.0296
0.000 0.2763 0.01119 0.00265 -0.0454 0.0864 0.0306
0.250 0.3043 0.01120 0.00265 -0.0453 0.0860 0.0316
0.500 0.3323 0.01121 0.00267 -0.0453 0.0857 0.0334
0.750 0.3603 0.01123 0.00269 -0.0452 0.0854 0.0356
1.000 0.3882 0.01126 0.00273 -0.0451 0.0851 0.0397
1.250 0.4162 0.01129 0.00277 -0.0451 0.0843 0.0471
1.500 0.4440 0.01133 0.00283 -0.0450 0.0834 0.0597
1.750 0.4717 0.01051 0.00278 -0.0456 0.0828 0.3860
2.000 0.4991 0.01004 0.00285 -0.0459 0.0823 0.5723
2.250 0.5268 0.01002 0.00295 -0.0458 0.0818 0.6182
2.500 0.5545 0.01003 0.00306 -0.0458 0.0811 0.6546
2.750 0.5823 0.01008 0.00316 -0.0457 0.0802 0.6821
3.000 0.6097 0.01012 0.00326 -0.0455 0.0792 0.7162
3.250 0.6372 0.01020 0.00338 -0.0454 0.0784 0.7348
3.500 0.6648 0.01030 0.00350 -0.0452 0.0776 0.7442
3.750 0.6923 0.01042 0.00362 -0.0451 0.0763 0.7519
4.000 0.7199 0.01054 0.00371 -0.0450 0.0743 0.7587
4.250 0.7470 0.01067 0.00376 -0.0449 0.0562 0.7662
4.500 0.7731 0.01092 0.00399 -0.0446 0.0531 0.7746
5.000 0.8258 0.01134 0.00444 -0.0440 0.0506 0.7913
5.250 0.8520 0.01154 0.00466 -0.0437 0.0496 0.8002
5.500 0.8783 0.01174 0.00488 -0.0434 0.0483 0.8080
5.750 0.9040 0.01196 0.00512 -0.0431 0.0470 0.8171
6.000 0.9302 0.01214 0.00532 -0.0428 0.0458 0.8260
6.250 0.9559 0.01232 0.00554 -0.0424 0.0435 0.8357
6.500 0.9810 0.01258 0.00576 -0.0420 0.0337 0.8454
6.750 1.0051 0.01286 0.00604 -0.0414 0.0313 0.8554
7.000 1.0295 0.01314 0.00633 -0.0408 0.0303 0.8666
7.250 1.0530 0.01341 0.00664 -0.0401 0.0296 0.8785
7.500 1.0761 0.01371 0.00697 -0.0393 0.0289 0.8911
8.000 1.1204 0.01422 0.00758 -0.0373 0.0283 0.9241
8.250 1.1405 0.01446 0.00788 -0.0359 0.0280 0.9480
8.500 1.1670 0.01476 0.00822 -0.0359 0.0277 1.0000
8.750 1.1903 0.01512 0.00860 -0.0353 0.0274 1.0000
9.000 1.2132 0.01550 0.00899 -0.0347 0.0272 1.0000
9.250 1.2354 0.01591 0.00941 -0.0340 0.0269 1.0000
9.500 1.2570 0.01634 0.00985 -0.0332 0.0267 1.0000
9.750 1.2777 0.01682 0.01034 -0.0323 0.0264 1.0000
10.000 1.2976 0.01731 0.01086 -0.0313 0.0260 1.0000
10.250 1.3180 0.01772 0.01129 -0.0303 0.0258 1.0000
10.500 1.3362 0.01814 0.01174 -0.0290 0.0256 1.0000
10.750 1.3528 0.01859 0.01221 -0.0274 0.0253 1.0000
11.000 1.3683 0.01908 0.01274 -0.0257 0.0252 1.0000
11.250 1.3832 0.01962 0.01331 -0.0240 0.0250 1.0000
11.500 1.3978 0.02019 0.01392 -0.0224 0.0249 1.0000
11.750 1.4121 0.02080 0.01457 -0.0208 0.0247 1.0000
12.000 1.4257 0.02147 0.01528 -0.0193 0.0246 1.0000
12.250 1.4391 0.02218 0.01604 -0.0178 0.0244 1.0000
12.500 1.4518 0.02296 0.01686 -0.0164 0.0243 1.0000
12.750 1.4641 0.02379 0.01774 -0.0150 0.0242 1.0000
13.000 1.4756 0.02471 0.01870 -0.0136 0.0240 1.0000
13.250 1.4863 0.02570 0.01975 -0.0123 0.0239 1.0000
13.500 1.4962 0.02680 0.02089 -0.0110 0.0237 1.0000
13.750 1.5048 0.02802 0.02217 -0.0098 0.0236 1.0000
14.000 1.5125 0.02936 0.02357 -0.0086 0.0235 1.0000
14.250 1.5176 0.03096 0.02523 -0.0075 0.0233 1.0000
14.500 1.5264 0.03231 0.02665 -0.0067 0.0232 1.0000
14.750 1.5353 0.03369 0.02810 -0.0060 0.0231 1.0000
15.000 1.5428 0.03524 0.02972 -0.0053 0.0230 1.0000
15.250 1.5493 0.03693 0.03149 -0.0047 0.0229 1.0000
15.500 1.5548 0.03878 0.03341 -0.0043 0.0227 1.0000
15.750 1.5590 0.04081 0.03552 -0.0040 0.0226 1.0000
16.000 1.5622 0.04301 0.03780 -0.0038 0.0225 1.0000
16.250 1.5640 0.04543 0.04031 -0.0038 0.0224 1.0000
16.500 1.5647 0.04808 0.04305 -0.0040 0.0223 1.0000
16.750 1.5656 0.05083 0.04589 -0.0043 0.0221 1.0000
17.000 1.5633 0.05409 0.04923 -0.0050 0.0220 1.0000
17.250 1.5607 0.05751 0.05276 -0.0059 0.0219 1.0000
17.500 1.5562 0.06135 0.05669 -0.0071 0.0218 1.0000
17.750 1.5492 0.06572 0.06118 -0.0087 0.0217 1.0000
18.000 1.5416 0.07038 0.06594 -0.0106 0.0216 1.0000
18.250 1.5301 0.07587 0.07156 -0.0130 0.0215 1.0000
18.500 1.5126 0.08267 0.07851 -0.0165 0.0215 1.0000
18.750 1.4934 0.09024 0.08623 -0.0206 0.0214 1.0000
19.000 1.4657 0.09975 0.09592 -0.0260 0.0214 1.0000
19.250 1.4343 0.11034 0.10670 -0.0321 0.0214 1.0000
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