NACA 64(1)-212 MOD B (n64212mb-il) Xfoil prediction polar at RE=500,000 Ncrit=9
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Airfoil: NACA 64(1)-212 MOD B (n64212mb-il) Reynolds number: 500,000 Max Cl/Cd: 74.36 at α=11° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-n64212mb-il-500000.txt Download as CSV file: xf-n64212mb-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.000 -0.6005 0.09222 0.08973 -0.0282 1.0000 0.0312
-11.750 -0.6333 0.08183 0.07923 -0.0368 1.0000 0.0312
-11.500 -0.6639 0.07466 0.07193 -0.0425 1.0000 0.0312
-11.250 -0.6889 0.06949 0.06665 -0.0455 1.0000 0.0312
-11.000 -0.7126 0.06564 0.06268 -0.0468 1.0000 0.0312
-10.750 -0.7366 0.06253 0.05944 -0.0459 1.0000 0.0313
-10.500 -0.7667 0.05573 0.05250 -0.0448 1.0000 0.0316
-10.250 -0.7565 0.05277 0.04957 -0.0445 1.0000 0.0319
-10.000 -0.7510 0.05041 0.04718 -0.0438 1.0000 0.0321
-9.750 -0.7457 0.04821 0.04493 -0.0428 1.0000 0.0324
-9.500 -0.7404 0.04593 0.04256 -0.0417 1.0000 0.0327
-9.250 -0.7332 0.04383 0.04037 -0.0406 1.0000 0.0333
-9.000 -0.7874 0.02634 0.02095 -0.0327 1.0000 0.0229
-8.750 -0.7739 0.02487 0.01934 -0.0307 1.0000 0.0230
-8.500 -0.7649 0.02364 0.01799 -0.0279 1.0000 0.0231
-8.250 -0.7314 0.02219 0.01643 -0.0296 0.9963 0.0234
-8.000 -0.6974 0.02090 0.01504 -0.0314 0.9920 0.0239
-7.750 -0.6635 0.01965 0.01367 -0.0330 0.9874 0.0243
-7.500 -0.6278 0.01859 0.01251 -0.0349 0.9839 0.0250
-7.250 -0.5936 0.01773 0.01155 -0.0363 0.9784 0.0258
-7.000 -0.5585 0.01697 0.01067 -0.0379 0.9729 0.0263
-6.750 -0.5276 0.01557 0.00927 -0.0389 0.9657 0.0270
-6.500 -0.4962 0.01479 0.00851 -0.0399 0.9579 0.0278
-6.250 -0.4690 0.01423 0.00792 -0.0398 0.9472 0.0287
-6.000 -0.4432 0.01372 0.00738 -0.0394 0.9367 0.0297
-5.750 -0.4189 0.01329 0.00688 -0.0386 0.9262 0.0307
-5.500 -0.3961 0.01270 0.00625 -0.0377 0.9153 0.0319
-5.250 -0.3725 0.01225 0.00579 -0.0369 0.9054 0.0338
-5.000 -0.3486 0.01193 0.00542 -0.0359 0.8932 0.0358
-4.750 -0.3249 0.01147 0.00490 -0.0350 0.8798 0.0381
-4.500 -0.3001 0.01110 0.00451 -0.0343 0.8680 0.0413
-4.250 -0.2747 0.01076 0.00411 -0.0337 0.8583 0.0456
-4.000 -0.2484 0.01046 0.00380 -0.0333 0.8476 0.0518
-3.750 -0.2228 0.01005 0.00345 -0.0327 0.8364 0.0667
-3.500 -0.1988 0.00931 0.00303 -0.0323 0.8248 0.1488
-3.250 -0.1774 0.00784 0.00250 -0.0321 0.8134 0.3807
-3.000 -0.1520 0.00734 0.00240 -0.0317 0.8040 0.5036
-2.750 -0.1246 0.00722 0.00234 -0.0314 0.7937 0.5450
-2.500 -0.0967 0.00715 0.00230 -0.0312 0.7838 0.5709
-2.000 -0.0408 0.00709 0.00220 -0.0307 0.7613 0.6055
-1.750 -0.0129 0.00708 0.00218 -0.0304 0.7489 0.6244
-1.500 0.0143 0.00712 0.00225 -0.0299 0.7368 0.6537
-1.250 0.0419 0.00715 0.00226 -0.0295 0.7230 0.6700
-1.000 0.0701 0.00717 0.00222 -0.0293 0.7074 0.6788
-0.750 0.0981 0.00717 0.00218 -0.0291 0.6907 0.6860
-0.500 0.1260 0.00720 0.00214 -0.0289 0.6697 0.6933
-0.250 0.1536 0.00726 0.00209 -0.0286 0.6407 0.7003
0.000 0.1803 0.00737 0.00207 -0.0282 0.5956 0.7069
0.250 0.2020 0.00812 0.00211 -0.0271 0.4211 0.7144
0.500 0.2242 0.00895 0.00239 -0.0264 0.2907 0.7212
0.750 0.2509 0.00924 0.00251 -0.0263 0.2573 0.7293
1.000 0.2781 0.00943 0.00262 -0.0261 0.2392 0.7369
1.250 0.3053 0.00962 0.00274 -0.0259 0.2270 0.7449
1.500 0.3330 0.00975 0.00285 -0.0258 0.2193 0.7528
1.750 0.3600 0.00993 0.00299 -0.0256 0.2119 0.7609
2.000 0.3876 0.01007 0.00312 -0.0255 0.2065 0.7692
2.250 0.4149 0.01019 0.00326 -0.0252 0.2018 0.7776
2.500 0.4419 0.01038 0.00342 -0.0250 0.1973 0.7864
2.750 0.4681 0.01062 0.00366 -0.0247 0.1930 0.7954
3.000 0.4955 0.01073 0.00381 -0.0245 0.1905 0.8043
3.250 0.5225 0.01087 0.00398 -0.0242 0.1877 0.8135
3.500 0.5491 0.01103 0.00416 -0.0239 0.1849 0.8223
3.750 0.5756 0.01123 0.00436 -0.0236 0.1819 0.8320
4.000 0.6005 0.01155 0.00467 -0.0230 0.1784 0.8411
4.250 0.6268 0.01176 0.00491 -0.0227 0.1763 0.8516
4.500 0.6525 0.01190 0.00512 -0.0221 0.1746 0.8616
4.750 0.6780 0.01206 0.00534 -0.0216 0.1726 0.8720
5.250 0.7276 0.01244 0.00580 -0.0202 0.1686 0.8945
5.500 0.7512 0.01264 0.00604 -0.0193 0.1666 0.9069
5.750 0.7735 0.01294 0.00634 -0.0182 0.1641 0.9210
6.000 0.7944 0.01337 0.00680 -0.0168 0.1617 0.9373
6.250 0.8178 0.01347 0.00698 -0.0158 0.1607 0.9579
6.500 0.8513 0.01367 0.00725 -0.0170 0.1590 0.9821
6.750 0.8821 0.01392 0.00752 -0.0179 0.1569 1.0000
7.000 0.9102 0.01415 0.00777 -0.0182 0.1546 1.0000
7.250 0.9378 0.01436 0.00797 -0.0183 0.1520 1.0000
7.500 0.9644 0.01474 0.00831 -0.0184 0.1491 1.0000
7.750 0.9906 0.01522 0.00881 -0.0184 0.1464 1.0000
8.000 1.0176 0.01529 0.00895 -0.0184 0.1442 1.0000
8.250 1.0442 0.01544 0.00915 -0.0183 0.1415 1.0000
8.500 1.0705 0.01563 0.00936 -0.0182 0.1389 1.0000
8.750 1.0962 0.01586 0.00959 -0.0181 0.1364 1.0000
9.000 1.1205 0.01643 0.01012 -0.0178 0.1331 1.0000
9.250 1.1465 0.01649 0.01030 -0.0176 0.1310 1.0000
9.500 1.1721 0.01659 0.01047 -0.0174 0.1280 1.0000
9.750 1.1975 0.01670 0.01061 -0.0171 0.1247 1.0000
10.000 1.2211 0.01701 0.01089 -0.0167 0.1209 1.0000
10.250 1.2463 0.01716 0.01114 -0.0164 0.1177 1.0000
10.500 1.2714 0.01728 0.01132 -0.0162 0.1134 1.0000
10.750 1.2944 0.01755 0.01156 -0.0157 0.1084 1.0000
11.000 1.3192 0.01774 0.01185 -0.0153 0.1031 1.0000
11.250 1.3415 0.01808 0.01216 -0.0148 0.0964 1.0000
11.500 1.3637 0.01847 0.01255 -0.0142 0.0878 1.0000
11.750 1.3830 0.01908 0.01312 -0.0133 0.0774 1.0000
12.000 1.3994 0.01991 0.01390 -0.0121 0.0675 1.0000
12.250 1.4132 0.02080 0.01479 -0.0105 0.0599 1.0000
12.500 1.4248 0.02171 0.01571 -0.0086 0.0545 1.0000
12.750 1.4320 0.02287 0.01687 -0.0062 0.0500 1.0000
13.000 1.4435 0.02375 0.01784 -0.0045 0.0468 1.0000
13.250 1.4493 0.02503 0.01914 -0.0024 0.0438 1.0000
13.500 1.4570 0.02620 0.02040 -0.0007 0.0415 1.0000
13.750 1.4644 0.02744 0.02172 0.0009 0.0393 1.0000
14.000 1.4663 0.02913 0.02345 0.0026 0.0375 1.0000
14.250 1.4680 0.03091 0.02533 0.0041 0.0360 1.0000
14.500 1.4735 0.03249 0.02702 0.0051 0.0346 1.0000
14.750 1.4755 0.03444 0.02907 0.0060 0.0334 1.0000
15.000 1.4729 0.03690 0.03162 0.0068 0.0324 1.0000
15.250 1.4633 0.04019 0.03500 0.0072 0.0314 1.0000
15.500 1.4566 0.04343 0.03837 0.0071 0.0308 1.0000
15.750 1.4539 0.04649 0.04157 0.0067 0.0301 1.0000
16.000 1.4464 0.05028 0.04550 0.0057 0.0295 1.0000
16.250 1.4351 0.05486 0.05022 0.0041 0.0290 1.0000
16.500 1.4201 0.06034 0.05585 0.0017 0.0285 1.0000
16.750 1.4010 0.06706 0.06274 -0.0018 0.0283 1.0000
17.000 1.3741 0.07593 0.07181 -0.0070 0.0282 1.0000
17.250 1.3453 0.08584 0.08190 -0.0129 0.0282 1.0000
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