NACA 64(1)-212 (n64212-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 64(1)-212 (n64212-il) Reynolds number: 500,000 Max Cl/Cd: 67.76 at α=3.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-n64212-il-500000-n5.txt Download as CSV file: xf-n64212-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 64(1)-212
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
------ -------- --------- --------- -------- -------- --------
-14.000 -0.8726 0.06656 0.06376 -0.0405 1.0000 0.0102
-13.750 -0.9037 0.05782 0.05479 -0.0462 1.0000 0.0102
-13.500 -0.9294 0.05106 0.04780 -0.0499 1.0000 0.0102
-13.250 -0.9466 0.04611 0.04263 -0.0519 1.0000 0.0103
-13.000 -0.9591 0.04210 0.03842 -0.0528 1.0000 0.0103
-12.750 -0.9662 0.03898 0.03509 -0.0530 1.0000 0.0106
-12.500 -0.9730 0.03607 0.03198 -0.0525 1.0000 0.0107
-12.250 -0.9775 0.03354 0.02922 -0.0514 1.0000 0.0108
-12.000 -0.9771 0.03163 0.02713 -0.0500 1.0000 0.0110
-11.750 -0.9754 0.02998 0.02529 -0.0481 1.0000 0.0112
-11.500 -0.9705 0.02862 0.02375 -0.0460 1.0000 0.0113
-11.250 -0.9630 0.02694 0.02189 -0.0444 1.0000 0.0115
-11.000 -0.9513 0.02563 0.02046 -0.0432 1.0000 0.0118
-10.750 -0.9358 0.02469 0.01945 -0.0422 1.0000 0.0120
-10.500 -0.9174 0.02415 0.01887 -0.0414 1.0000 0.0124
-10.250 -0.9003 0.02322 0.01784 -0.0404 1.0000 0.0127
-10.000 -0.8818 0.02249 0.01704 -0.0396 1.0000 0.0131
-9.750 -0.8637 0.02162 0.01606 -0.0386 1.0000 0.0134
-9.500 -0.8458 0.02072 0.01505 -0.0375 1.0000 0.0138
-9.250 -0.8167 0.01973 0.01391 -0.0387 0.9874 0.0142
-9.000 -0.7851 0.01883 0.01288 -0.0403 0.9749 0.0146
-8.750 -0.7539 0.01792 0.01186 -0.0418 0.9630 0.0150
-8.500 -0.7246 0.01707 0.01096 -0.0429 0.9497 0.0157
-8.250 -0.6976 0.01651 0.01032 -0.0433 0.9358 0.0162
-8.000 -0.6732 0.01597 0.00970 -0.0430 0.9215 0.0167
-7.750 -0.6500 0.01544 0.00909 -0.0425 0.9084 0.0171
-7.500 -0.6269 0.01494 0.00850 -0.0419 0.8959 0.0177
-7.250 -0.6037 0.01446 0.00791 -0.0412 0.8847 0.0183
-7.000 -0.5799 0.01404 0.00738 -0.0407 0.8736 0.0189
-6.750 -0.5562 0.01355 0.00682 -0.0402 0.8630 0.0197
-6.500 -0.5320 0.01310 0.00632 -0.0398 0.8533 0.0207
-6.250 -0.5070 0.01275 0.00591 -0.0395 0.8436 0.0218
-6.000 -0.4816 0.01241 0.00550 -0.0392 0.8343 0.0229
-5.750 -0.4559 0.01211 0.00512 -0.0389 0.8255 0.0241
-5.500 -0.4301 0.01177 0.00471 -0.0387 0.8163 0.0256
-5.250 -0.4042 0.01144 0.00434 -0.0385 0.8079 0.0278
-5.000 -0.3777 0.01119 0.00404 -0.0384 0.7992 0.0301
-4.750 -0.3508 0.01097 0.00376 -0.0384 0.7913 0.0325
-4.500 -0.3242 0.01070 0.00346 -0.0383 0.7831 0.0371
-4.250 -0.2971 0.01049 0.00322 -0.0383 0.7751 0.0416
-4.000 -0.2702 0.01025 0.00298 -0.0382 0.7668 0.0511
-3.750 -0.2434 0.00995 0.00275 -0.0382 0.7589 0.0712
-3.500 -0.2169 0.00957 0.00249 -0.0383 0.7511 0.1120
-3.250 -0.1908 0.00905 0.00223 -0.0384 0.7437 0.1844
-3.000 -0.1652 0.00838 0.00193 -0.0385 0.7362 0.2909
-2.750 -0.1399 0.00764 0.00170 -0.0387 0.7291 0.4319
-2.500 -0.1124 0.00745 0.00162 -0.0387 0.7215 0.4817
-2.250 -0.0844 0.00735 0.00156 -0.0388 0.7142 0.5120
-2.000 -0.0568 0.00723 0.00154 -0.0388 0.7066 0.5555
-1.750 -0.0292 0.00714 0.00156 -0.0388 0.6997 0.5951
-1.500 -0.0009 0.00712 0.00154 -0.0389 0.6927 0.6101
-1.250 0.0276 0.00712 0.00150 -0.0390 0.6864 0.6184
-1.000 0.0562 0.00710 0.00148 -0.0391 0.6796 0.6261
-0.500 0.1133 0.00711 0.00145 -0.0394 0.6666 0.6387
-0.250 0.1419 0.00713 0.00144 -0.0395 0.6600 0.6451
0.000 0.1704 0.00713 0.00144 -0.0397 0.6537 0.6508
0.250 0.1990 0.00715 0.00146 -0.0398 0.6475 0.6573
0.500 0.2275 0.00718 0.00147 -0.0400 0.6420 0.6638
0.750 0.2561 0.00718 0.00151 -0.0401 0.6362 0.6708
1.000 0.2846 0.00722 0.00155 -0.0403 0.6303 0.6779
1.250 0.3130 0.00724 0.00160 -0.0404 0.6245 0.6847
1.500 0.3415 0.00728 0.00165 -0.0405 0.6174 0.6919
1.750 0.3697 0.00732 0.00171 -0.0406 0.6100 0.6987
2.000 0.3980 0.00736 0.00178 -0.0407 0.6020 0.7062
2.250 0.4261 0.00741 0.00185 -0.0408 0.5925 0.7134
2.500 0.4535 0.00749 0.00191 -0.0407 0.5718 0.7216
2.750 0.4800 0.00763 0.00197 -0.0404 0.5398 0.7293
3.000 0.5066 0.00780 0.00205 -0.0402 0.5080 0.7376
3.250 0.5329 0.00800 0.00218 -0.0400 0.4715 0.7451
3.500 0.5590 0.00825 0.00232 -0.0398 0.4316 0.7534
3.750 0.5814 0.00892 0.00262 -0.0391 0.3375 0.7612
4.000 0.6025 0.00980 0.00307 -0.0385 0.2353 0.7700
4.250 0.6248 0.01050 0.00349 -0.0379 0.1614 0.7787
4.500 0.6478 0.01112 0.00388 -0.0373 0.1059 0.7877
5.000 0.6955 0.01207 0.00459 -0.0364 0.0477 0.8057
5.250 0.7204 0.01240 0.00493 -0.0360 0.0389 0.8154
5.500 0.7450 0.01270 0.00526 -0.0356 0.0339 0.8250
5.750 0.7697 0.01301 0.00561 -0.0352 0.0304 0.8349
6.000 0.7935 0.01338 0.00602 -0.0346 0.0271 0.8457
6.250 0.8174 0.01366 0.00639 -0.0340 0.0252 0.8566
6.500 0.8406 0.01401 0.00678 -0.0333 0.0232 0.8680
6.750 0.8621 0.01446 0.00728 -0.0323 0.0211 0.8810
7.000 0.8839 0.01481 0.00773 -0.0313 0.0201 0.8950
7.250 0.9045 0.01518 0.00819 -0.0301 0.0190 0.9116
7.500 0.9242 0.01556 0.00863 -0.0287 0.0180 0.9317
7.750 0.9465 0.01598 0.00911 -0.0280 0.0170 0.9599
8.000 0.9710 0.01667 0.00983 -0.0280 0.0161 1.0000
8.250 0.9931 0.01721 0.01043 -0.0274 0.0156 1.0000
8.500 1.0141 0.01783 0.01111 -0.0267 0.0152 1.0000
8.750 1.0342 0.01849 0.01182 -0.0258 0.0147 1.0000
9.000 1.0537 0.01916 0.01255 -0.0249 0.0143 1.0000
9.250 1.0723 0.01987 0.01332 -0.0238 0.0140 1.0000
9.500 1.0902 0.02059 0.01409 -0.0227 0.0136 1.0000
9.750 1.1065 0.02132 0.01488 -0.0214 0.0134 1.0000
10.000 1.1207 0.02210 0.01571 -0.0197 0.0131 1.0000
10.250 1.1334 0.02298 0.01665 -0.0179 0.0129 1.0000
10.500 1.1447 0.02402 0.01775 -0.0161 0.0126 1.0000
10.750 1.1539 0.02532 0.01914 -0.0142 0.0123 1.0000
11.000 1.1666 0.02632 0.02023 -0.0128 0.0122 1.0000
11.250 1.1792 0.02734 0.02136 -0.0115 0.0119 1.0000
11.500 1.1902 0.02855 0.02269 -0.0102 0.0117 1.0000
11.750 1.2003 0.02989 0.02415 -0.0089 0.0116 1.0000
12.000 1.2098 0.03129 0.02567 -0.0076 0.0114 1.0000
12.250 1.2180 0.03285 0.02736 -0.0065 0.0112 1.0000
12.500 1.2256 0.03447 0.02910 -0.0054 0.0110 1.0000
12.750 1.2322 0.03621 0.03098 -0.0045 0.0108 1.0000
13.000 1.2374 0.03814 0.03304 -0.0036 0.0107 1.0000
13.250 1.2416 0.04018 0.03521 -0.0029 0.0105 1.0000
13.500 1.2449 0.04235 0.03751 -0.0024 0.0104 1.0000
13.750 1.2474 0.04465 0.03993 -0.0020 0.0103 1.0000
14.000 1.2503 0.04691 0.04229 -0.0020 0.0101 1.0000
14.250 1.2510 0.04955 0.04505 -0.0021 0.0100 1.0000
14.500 1.2512 0.05232 0.04792 -0.0024 0.0098 1.0000
14.750 1.2483 0.05561 0.05133 -0.0030 0.0097 1.0000
15.000 1.2424 0.05945 0.05532 -0.0039 0.0096 1.0000
15.250 1.2353 0.06362 0.05963 -0.0052 0.0095 1.0000
15.500 1.2241 0.06868 0.06485 -0.0071 0.0095 1.0000
15.750 1.2102 0.07446 0.07081 -0.0096 0.0094 1.0000
16.000 1.1925 0.08128 0.07782 -0.0129 0.0093 1.0000
16.500 1.1563 0.09666 0.09357 -0.0217 0.0093 1.0000
16.750 1.1321 0.10658 0.10369 -0.0277 0.0093 1.0000
17.250 1.0776 0.13053 0.12805 -0.0429 0.0094 1.0000
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