NACA 64(1)-212 MOD B (n64212mb-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 64(1)-212 MOD B (n64212mb-il) Reynolds number: 200,000 Max Cl/Cd: 51.26 at α=10.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-n64212mb-il-200000-n5.txt Download as CSV file: xf-n64212mb-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.250 -0.6950 0.07408 0.06986 -0.0360 1.0000 0.0208
-12.000 -0.7156 0.06723 0.06290 -0.0408 1.0000 0.0207
-11.750 -0.7440 0.06037 0.05584 -0.0452 1.0000 0.0207
-11.500 -0.7652 0.05536 0.05063 -0.0473 1.0000 0.0206
-11.250 -0.7845 0.05120 0.04626 -0.0479 1.0000 0.0206
-11.000 -0.8084 0.04729 0.04204 -0.0469 1.0000 0.0208
-10.750 -0.8252 0.04415 0.03860 -0.0445 1.0000 0.0209
-10.500 -0.8209 0.04221 0.03657 -0.0433 1.0000 0.0211
-10.250 -0.8134 0.04055 0.03481 -0.0421 1.0000 0.0214
-10.000 -0.8053 0.03865 0.03276 -0.0409 1.0000 0.0216
-9.750 -0.7960 0.03670 0.03062 -0.0396 1.0000 0.0219
-9.500 -0.7859 0.03457 0.02826 -0.0382 1.0000 0.0221
-9.250 -0.7736 0.03260 0.02605 -0.0368 1.0000 0.0223
-9.000 -0.7599 0.03079 0.02402 -0.0354 1.0000 0.0225
-8.750 -0.7450 0.02916 0.02219 -0.0339 1.0000 0.0228
-8.500 -0.7300 0.02768 0.02052 -0.0323 1.0000 0.0232
-8.250 -0.7152 0.02634 0.01900 -0.0305 1.0000 0.0236
-8.000 -0.6981 0.02510 0.01760 -0.0290 0.9988 0.0239
-7.750 -0.6665 0.02370 0.01597 -0.0303 0.9910 0.0245
-7.500 -0.6337 0.02247 0.01464 -0.0318 0.9847 0.0252
-7.250 -0.6020 0.02155 0.01374 -0.0332 0.9771 0.0260
-7.000 -0.5693 0.02069 0.01282 -0.0346 0.9702 0.0270
-6.750 -0.5374 0.01979 0.01185 -0.0357 0.9625 0.0281
-6.500 -0.5064 0.01892 0.01091 -0.0366 0.9545 0.0289
-6.250 -0.4755 0.01804 0.01000 -0.0375 0.9466 0.0300
-6.000 -0.4472 0.01733 0.00931 -0.0380 0.9373 0.0311
-5.750 -0.4175 0.01669 0.00865 -0.0386 0.9295 0.0328
-5.500 -0.3914 0.01616 0.00805 -0.0384 0.9192 0.0346
-5.250 -0.3648 0.01560 0.00749 -0.0383 0.9106 0.0370
-5.000 -0.3390 0.01516 0.00702 -0.0380 0.9012 0.0402
-4.750 -0.3135 0.01469 0.00653 -0.0377 0.8929 0.0436
-4.500 -0.2878 0.01432 0.00612 -0.0372 0.8841 0.0486
-4.250 -0.2624 0.01391 0.00572 -0.0368 0.8758 0.0559
-4.000 -0.2376 0.01349 0.00532 -0.0361 0.8648 0.0685
-3.750 -0.2138 0.01296 0.00493 -0.0354 0.8516 0.0998
-3.500 -0.1916 0.01211 0.00448 -0.0347 0.8382 0.1942
-3.250 -0.1716 0.01087 0.00403 -0.0340 0.8257 0.3829
-3.000 -0.1478 0.01046 0.00397 -0.0331 0.8127 0.4955
-2.750 -0.1220 0.01033 0.00390 -0.0323 0.7986 0.5382
-2.500 -0.0959 0.01025 0.00386 -0.0316 0.7849 0.5766
-2.250 -0.0708 0.01026 0.00399 -0.0304 0.7729 0.6265
-2.000 -0.0449 0.01031 0.00408 -0.0295 0.7612 0.6560
-1.750 -0.0172 0.01029 0.00398 -0.0291 0.7487 0.6661
-1.500 0.0099 0.01026 0.00389 -0.0286 0.7342 0.6736
-1.250 0.0377 0.01024 0.00376 -0.0283 0.7180 0.6812
-1.000 0.0649 0.01022 0.00368 -0.0279 0.7004 0.6868
-0.750 0.0922 0.01022 0.00359 -0.0275 0.6803 0.6933
-0.500 0.1196 0.01024 0.00350 -0.0271 0.6589 0.7005
-0.250 0.1462 0.01027 0.00345 -0.0266 0.6298 0.7068
0.000 0.1725 0.01038 0.00336 -0.0260 0.5876 0.7141
0.250 0.1956 0.01072 0.00328 -0.0249 0.4846 0.7205
0.500 0.2139 0.01175 0.00348 -0.0235 0.3140 0.7275
0.750 0.2395 0.01207 0.00362 -0.0232 0.2793 0.7355
1.000 0.2653 0.01230 0.00376 -0.0227 0.2584 0.7428
1.250 0.2920 0.01251 0.00387 -0.0225 0.2443 0.7514
1.500 0.3178 0.01271 0.00402 -0.0220 0.2339 0.7583
1.750 0.3443 0.01289 0.00416 -0.0218 0.2255 0.7668
2.000 0.3701 0.01310 0.00433 -0.0213 0.2188 0.7744
2.250 0.3965 0.01328 0.00449 -0.0210 0.2127 0.7835
2.500 0.4221 0.01348 0.00468 -0.0205 0.2072 0.7918
2.750 0.4477 0.01373 0.00488 -0.0200 0.2026 0.8015
3.000 0.4733 0.01390 0.00509 -0.0195 0.1989 0.8100
3.250 0.4993 0.01411 0.00531 -0.0191 0.1953 0.8197
3.500 0.5240 0.01432 0.00553 -0.0184 0.1920 0.8288
3.750 0.5489 0.01459 0.00578 -0.0178 0.1890 0.8392
4.000 0.5728 0.01488 0.00606 -0.0170 0.1862 0.8497
4.250 0.5974 0.01507 0.00632 -0.0163 0.1835 0.8603
4.500 0.6220 0.01528 0.00657 -0.0156 0.1806 0.8719
4.750 0.6457 0.01551 0.00685 -0.0147 0.1780 0.8842
5.000 0.6694 0.01575 0.00712 -0.0138 0.1757 0.8973
5.250 0.6929 0.01603 0.00740 -0.0129 0.1736 0.9121
5.500 0.7171 0.01637 0.00773 -0.0123 0.1715 0.9286
5.750 0.7440 0.01669 0.00810 -0.0121 0.1696 0.9473
6.000 0.7764 0.01697 0.00846 -0.0132 0.1672 0.9693
6.250 0.8078 0.01731 0.00885 -0.0142 0.1646 1.0000
6.500 0.8346 0.01769 0.00926 -0.0143 0.1625 1.0000
6.750 0.8612 0.01809 0.00968 -0.0143 0.1605 1.0000
7.000 0.8876 0.01851 0.01011 -0.0143 0.1586 1.0000
7.250 0.9136 0.01898 0.01056 -0.0143 0.1566 1.0000
7.500 0.9397 0.01955 0.01112 -0.0143 0.1545 1.0000
7.750 0.9656 0.01994 0.01165 -0.0142 0.1525 1.0000
8.000 0.9910 0.02032 0.01212 -0.0140 0.1497 1.0000
8.250 1.0161 0.02066 0.01253 -0.0138 0.1466 1.0000
8.500 1.0407 0.02098 0.01289 -0.0135 0.1437 1.0000
8.750 1.0649 0.02142 0.01331 -0.0133 0.1409 1.0000
9.000 1.0889 0.02182 0.01383 -0.0129 0.1379 1.0000
9.250 1.1126 0.02214 0.01429 -0.0125 0.1342 1.0000
9.500 1.1358 0.02244 0.01467 -0.0121 0.1308 1.0000
9.750 1.1582 0.02276 0.01501 -0.0115 0.1278 1.0000
10.000 1.1806 0.02319 0.01556 -0.0110 0.1245 1.0000
10.250 1.2029 0.02357 0.01609 -0.0104 0.1204 1.0000
10.500 1.2240 0.02388 0.01648 -0.0098 0.1166 1.0000
10.750 1.2442 0.02427 0.01692 -0.0090 0.1128 1.0000
11.000 1.2652 0.02470 0.01753 -0.0083 0.1074 1.0000
11.250 1.2834 0.02508 0.01793 -0.0073 0.1026 1.0000
11.500 1.3028 0.02561 0.01861 -0.0064 0.0964 1.0000
11.750 1.3178 0.02615 0.01918 -0.0050 0.0906 1.0000
12.000 1.3324 0.02683 0.01994 -0.0037 0.0834 1.0000
12.250 1.3447 0.02767 0.02082 -0.0021 0.0766 1.0000
12.500 1.3544 0.02870 0.02188 -0.0006 0.0706 1.0000
12.750 1.3627 0.02991 0.02314 0.0010 0.0649 1.0000
13.000 1.3691 0.03130 0.02459 0.0025 0.0604 1.0000
13.250 1.3736 0.03289 0.02626 0.0039 0.0566 1.0000
13.500 1.3761 0.03467 0.02814 0.0051 0.0536 1.0000
13.750 1.3783 0.03658 0.03017 0.0062 0.0508 1.0000
14.000 1.3769 0.03889 0.03257 0.0070 0.0486 1.0000
14.250 1.3734 0.04152 0.03531 0.0075 0.0468 1.0000
14.500 1.3709 0.04424 0.03820 0.0076 0.0450 1.0000
14.750 1.3646 0.04752 0.04162 0.0073 0.0436 1.0000
15.000 1.3542 0.05152 0.04576 0.0064 0.0424 1.0000
15.250 1.3398 0.05634 0.05074 0.0048 0.0416 1.0000
15.500 1.3205 0.06234 0.05691 0.0020 0.0412 1.0000
15.750 1.2950 0.07004 0.06480 -0.0022 0.0409 1.0000
16.000 1.2626 0.08019 0.07519 -0.0084 0.0409 1.0000
16.250 1.2246 0.09207 0.08730 -0.0156 0.0410 1.0000
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