NACA 64(1)-212 MOD B (n64212mb-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 64(1)-212 MOD B (n64212mb-il) Reynolds number: 1,000,000 Max Cl/Cd: 95.02 at α=9.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-n64212mb-il-1000000-n5.txt Download as CSV file: xf-n64212mb-il-1000000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-17.000 -1.0230 0.08491 0.08230 -0.0278 1.0000 0.0104
-16.750 -1.0583 0.07373 0.07091 -0.0352 1.0000 0.0104
-16.500 -1.0893 0.06453 0.06149 -0.0411 1.0000 0.0103
-16.250 -1.0986 0.05953 0.05639 -0.0440 1.0000 0.0104
-16.000 -1.1148 0.05395 0.05065 -0.0470 1.0000 0.0104
-15.750 -1.1197 0.05016 0.04675 -0.0488 1.0000 0.0105
-15.500 -1.1260 0.04641 0.04289 -0.0504 1.0000 0.0106
-15.250 -1.1305 0.04308 0.03943 -0.0514 1.0000 0.0106
-15.000 -1.1345 0.03997 0.03619 -0.0522 1.0000 0.0106
-14.750 -1.1357 0.03730 0.03340 -0.0525 1.0000 0.0107
-14.500 -1.1357 0.03488 0.03087 -0.0525 1.0000 0.0107
-14.250 -1.1336 0.03280 0.02868 -0.0522 1.0000 0.0108
-14.000 -1.1294 0.03101 0.02679 -0.0516 1.0000 0.0108
-13.750 -1.1247 0.02935 0.02503 -0.0508 1.0000 0.0109
-13.500 -1.1186 0.02790 0.02348 -0.0498 1.0000 0.0110
-13.250 -1.1122 0.02655 0.02204 -0.0485 1.0000 0.0110
-13.000 -1.1053 0.02535 0.02076 -0.0470 1.0000 0.0111
-12.750 -1.0985 0.02428 0.01959 -0.0451 1.0000 0.0111
-12.500 -1.0918 0.02332 0.01854 -0.0428 1.0000 0.0112
-12.250 -1.0791 0.02250 0.01765 -0.0411 1.0000 0.0113
-12.000 -1.0643 0.02164 0.01671 -0.0398 1.0000 0.0114
-11.750 -1.0476 0.02088 0.01588 -0.0386 1.0000 0.0114
-11.500 -1.0300 0.02013 0.01506 -0.0374 1.0000 0.0115
-11.250 -1.0116 0.01941 0.01427 -0.0364 1.0000 0.0116
-11.000 -0.9920 0.01880 0.01360 -0.0354 1.0000 0.0116
-10.750 -0.9722 0.01815 0.01290 -0.0344 1.0000 0.0117
-10.500 -0.9543 0.01730 0.01200 -0.0332 1.0000 0.0119
-10.250 -0.9272 0.01656 0.01120 -0.0338 0.9874 0.0121
-10.000 -0.8938 0.01590 0.01051 -0.0355 0.9743 0.0123
-9.750 -0.8609 0.01536 0.00993 -0.0370 0.9610 0.0125
-9.500 -0.8324 0.01490 0.00941 -0.0374 0.9452 0.0127
-9.250 -0.8082 0.01448 0.00892 -0.0369 0.9292 0.0129
-9.000 -0.7849 0.01408 0.00845 -0.0362 0.9149 0.0130
-8.750 -0.7611 0.01371 0.00802 -0.0355 0.9023 0.0132
-8.500 -0.7371 0.01335 0.00758 -0.0349 0.8911 0.0134
-8.250 -0.7128 0.01299 0.00716 -0.0343 0.8804 0.0136
-8.000 -0.6878 0.01264 0.00676 -0.0338 0.8706 0.0138
-7.750 -0.6626 0.01233 0.00638 -0.0334 0.8613 0.0140
-7.500 -0.6369 0.01201 0.00602 -0.0330 0.8525 0.0141
-7.250 -0.6111 0.01173 0.00567 -0.0326 0.8443 0.0143
-7.000 -0.5852 0.01139 0.00530 -0.0323 0.8359 0.0146
-6.750 -0.5592 0.01109 0.00496 -0.0319 0.8278 0.0150
-6.500 -0.5324 0.01083 0.00467 -0.0317 0.8204 0.0154
-6.250 -0.5057 0.01059 0.00440 -0.0315 0.8129 0.0159
-6.000 -0.4786 0.01037 0.00415 -0.0313 0.8045 0.0164
-5.750 -0.4518 0.01018 0.00390 -0.0310 0.7926 0.0170
-5.500 -0.4248 0.00999 0.00366 -0.0308 0.7781 0.0177
-5.250 -0.3977 0.00980 0.00343 -0.0306 0.7630 0.0187
-5.000 -0.3703 0.00964 0.00324 -0.0304 0.7508 0.0201
-4.750 -0.3428 0.00948 0.00304 -0.0303 0.7404 0.0216
-4.500 -0.3152 0.00933 0.00286 -0.0302 0.7272 0.0236
-4.250 -0.2876 0.00921 0.00269 -0.0300 0.7107 0.0254
-4.000 -0.2599 0.00909 0.00253 -0.0299 0.6948 0.0279
-3.750 -0.2322 0.00898 0.00238 -0.0298 0.6785 0.0304
-3.500 -0.2043 0.00888 0.00224 -0.0297 0.6622 0.0339
-3.250 -0.1764 0.00876 0.00210 -0.0296 0.6487 0.0388
-3.000 -0.1484 0.00865 0.00198 -0.0296 0.6333 0.0472
-2.750 -0.1208 0.00852 0.00185 -0.0295 0.6138 0.0638
-2.500 -0.0934 0.00831 0.00171 -0.0295 0.5917 0.1001
-2.250 -0.0667 0.00796 0.00155 -0.0295 0.5648 0.1764
-2.000 -0.0410 0.00761 0.00138 -0.0294 0.5144 0.2785
-1.750 -0.0196 0.00802 0.00141 -0.0290 0.3105 0.3738
-1.500 0.0073 0.00789 0.00139 -0.0290 0.2730 0.4498
-1.250 0.0350 0.00785 0.00139 -0.0290 0.2475 0.4964
-1.000 0.0627 0.00777 0.00142 -0.0290 0.2291 0.5493
-0.750 0.0908 0.00779 0.00145 -0.0290 0.2159 0.5796
-0.500 0.1192 0.00784 0.00148 -0.0290 0.2052 0.5930
-0.250 0.1478 0.00789 0.00150 -0.0290 0.1979 0.6003
0.000 0.1764 0.00796 0.00154 -0.0291 0.1907 0.6070
0.250 0.2050 0.00804 0.00157 -0.0291 0.1847 0.6124
0.500 0.2336 0.00809 0.00161 -0.0291 0.1796 0.6180
0.750 0.2621 0.00817 0.00165 -0.0292 0.1748 0.6246
1.250 0.3191 0.00830 0.00176 -0.0292 0.1683 0.6371
1.500 0.3477 0.00837 0.00183 -0.0293 0.1657 0.6435
1.750 0.3761 0.00845 0.00190 -0.0293 0.1631 0.6495
2.000 0.4045 0.00853 0.00197 -0.0293 0.1603 0.6563
2.250 0.4327 0.00863 0.00206 -0.0293 0.1571 0.6630
2.500 0.4610 0.00872 0.00215 -0.0293 0.1545 0.6695
2.750 0.4894 0.00879 0.00224 -0.0293 0.1532 0.6769
3.000 0.5176 0.00887 0.00234 -0.0293 0.1517 0.6842
3.250 0.5458 0.00896 0.00245 -0.0293 0.1500 0.6922
3.750 0.6019 0.00916 0.00267 -0.0293 0.1463 0.7072
4.000 0.6298 0.00928 0.00280 -0.0292 0.1444 0.7148
4.250 0.6575 0.00941 0.00294 -0.0292 0.1422 0.7221
4.500 0.6850 0.00956 0.00310 -0.0291 0.1401 0.7301
4.750 0.7130 0.00965 0.00323 -0.0291 0.1392 0.7375
5.000 0.7407 0.00976 0.00338 -0.0290 0.1382 0.7460
5.250 0.7683 0.00988 0.00353 -0.0289 0.1371 0.7542
5.500 0.7958 0.01000 0.00370 -0.0288 0.1358 0.7633
5.750 0.8232 0.01013 0.00386 -0.0287 0.1343 0.7716
6.000 0.8504 0.01027 0.00403 -0.0286 0.1328 0.7805
6.250 0.8775 0.01042 0.00420 -0.0285 0.1309 0.7886
6.500 0.9042 0.01059 0.00440 -0.0283 0.1283 0.7980
6.750 0.9310 0.01075 0.00460 -0.0281 0.1259 0.8071
7.000 0.9581 0.01086 0.00476 -0.0280 0.1240 0.8171
7.250 0.9849 0.01100 0.00492 -0.0278 0.1210 0.8266
7.500 1.0113 0.01117 0.00511 -0.0276 0.1182 0.8368
7.750 1.0372 0.01135 0.00533 -0.0273 0.1154 0.8475
8.000 1.0631 0.01153 0.00555 -0.0270 0.1134 0.8583
8.250 1.0890 0.01168 0.00577 -0.0266 0.1112 0.8702
8.500 1.1141 0.01185 0.00599 -0.0262 0.1081 0.8834
8.750 1.1384 0.01206 0.00622 -0.0256 0.1037 0.8975
9.000 1.1622 0.01225 0.00646 -0.0248 0.1000 0.9137
9.250 1.1849 0.01247 0.00671 -0.0239 0.0945 0.9320
9.500 1.2071 0.01271 0.00697 -0.0229 0.0886 0.9590
9.750 1.2341 0.01311 0.00733 -0.0232 0.0793 1.0000
10.000 1.2570 0.01363 0.00779 -0.0227 0.0688 1.0000
10.250 1.2795 0.01419 0.00829 -0.0221 0.0601 1.0000
10.500 1.3017 0.01475 0.00882 -0.0215 0.0535 1.0000
10.750 1.3238 0.01530 0.00936 -0.0209 0.0481 1.0000
11.000 1.3462 0.01579 0.00985 -0.0203 0.0441 1.0000
11.250 1.3675 0.01637 0.01042 -0.0196 0.0401 1.0000
11.500 1.3887 0.01691 0.01097 -0.0189 0.0366 1.0000
11.750 1.4093 0.01748 0.01155 -0.0181 0.0338 1.0000
12.000 1.4296 0.01803 0.01211 -0.0172 0.0315 1.0000
12.250 1.4486 0.01865 0.01275 -0.0163 0.0294 1.0000
12.500 1.4679 0.01919 0.01333 -0.0153 0.0280 1.0000
12.750 1.4854 0.01980 0.01397 -0.0141 0.0264 1.0000
13.000 1.4996 0.02046 0.01466 -0.0124 0.0250 1.0000
13.250 1.5136 0.02106 0.01531 -0.0106 0.0240 1.0000
13.500 1.5262 0.02173 0.01603 -0.0088 0.0229 1.0000
13.750 1.5373 0.02252 0.01686 -0.0070 0.0218 1.0000
14.000 1.5474 0.02340 0.01778 -0.0052 0.0208 1.0000
14.250 1.5587 0.02422 0.01867 -0.0036 0.0202 1.0000
14.500 1.5688 0.02517 0.01968 -0.0021 0.0195 1.0000
14.750 1.5775 0.02624 0.02081 -0.0006 0.0188 1.0000
15.000 1.5844 0.02749 0.02211 0.0009 0.0180 1.0000
15.250 1.5904 0.02887 0.02355 0.0022 0.0175 1.0000
15.500 1.5973 0.03022 0.02498 0.0033 0.0170 1.0000
15.750 1.6028 0.03175 0.02659 0.0043 0.0165 1.0000
16.000 1.6069 0.03346 0.02839 0.0052 0.0161 1.0000
16.250 1.6087 0.03547 0.03048 0.0059 0.0156 1.0000
16.500 1.6089 0.03772 0.03281 0.0064 0.0152 1.0000
16.750 1.6064 0.04037 0.03554 0.0066 0.0148 1.0000
17.000 1.6021 0.04336 0.03864 0.0065 0.0145 1.0000
17.250 1.5957 0.04677 0.04216 0.0060 0.0143 1.0000
17.500 1.5883 0.05051 0.04603 0.0051 0.0141 1.0000
17.750 1.5760 0.05515 0.05081 0.0035 0.0140 1.0000
18.000 1.5563 0.06130 0.05712 0.0007 0.0139 1.0000
18.250 1.5223 0.07058 0.06662 -0.0044 0.0139 1.0000
18.500 1.4092 0.09700 0.09354 -0.0203 0.0148 1.0000
18.750 1.3156 0.11876 0.11563 -0.0333 0.0155 1.0000
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