NACA 63(4)-221 (naca634221-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
Details | Polar file |
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Airfoil: NACA 63(4)-221 (naca634221-il) Reynolds number: 1,000,000 Max Cl/Cd: 95.82 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca634221-il-1000000-n5.txt Download as CSV file: xf-naca634221-il-1000000-n5.csv |
XFOIL Version 6.96 Calculated polar for: NACA 63(4)-221 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 ------ -------- --------- --------- -------- -------- -------- -19.750 -1.1613 0.08301 0.07853 -0.0399 1.0000 0.0224 -19.500 -1.1590 0.08020 0.07567 -0.0408 1.0000 0.0227 -19.250 -1.1600 0.07699 0.07241 -0.0419 1.0000 0.0232 -19.000 -1.1581 0.07421 0.06959 -0.0428 1.0000 0.0238 -18.750 -1.1569 0.07134 0.06667 -0.0436 1.0000 0.0241 -18.500 -1.1528 0.06886 0.06415 -0.0443 1.0000 0.0246 -18.250 -1.1506 0.06618 0.06142 -0.0450 1.0000 0.0250 -18.000 -1.1450 0.06393 0.05913 -0.0456 1.0000 0.0255 -17.750 -1.1402 0.06159 0.05673 -0.0462 1.0000 0.0259 -17.500 -1.1338 0.05945 0.05454 -0.0467 1.0000 0.0263 -17.250 -1.1312 0.05693 0.05198 -0.0472 1.0000 0.0268 -17.000 -1.1263 0.05471 0.04973 -0.0476 1.0000 0.0272 -16.750 -1.1210 0.05253 0.04752 -0.0480 1.0000 0.0279 -16.250 -1.1124 0.04865 0.04357 -0.0473 0.9795 0.0287 -16.000 -1.0660 0.04600 0.04084 -0.0561 0.9429 0.0297 -15.750 -1.0345 0.04408 0.03868 -0.0609 0.8892 0.0302 -15.500 -1.0301 0.04232 0.03678 -0.0605 0.8600 0.0307 -15.250 -1.0240 0.04071 0.03507 -0.0601 0.8412 0.0313 -15.000 -1.0173 0.03911 0.03337 -0.0598 0.8264 0.0319 -14.750 -1.0090 0.03763 0.03182 -0.0595 0.8142 0.0324 -14.500 -1.0009 0.03613 0.03026 -0.0592 0.8042 0.0330 -14.250 -0.9915 0.03478 0.02884 -0.0588 0.7945 0.0336 -14.000 -0.9823 0.03344 0.02742 -0.0584 0.7854 0.0341 -13.750 -0.9723 0.03217 0.02609 -0.0580 0.7763 0.0347 -13.500 -0.9645 0.03079 0.02465 -0.0574 0.7685 0.0354 -13.250 -0.9556 0.02952 0.02335 -0.0568 0.7615 0.0365 -13.000 -0.9464 0.02831 0.02208 -0.0562 0.7540 0.0372 -12.750 -0.9359 0.02721 0.02093 -0.0555 0.7470 0.0381 -12.500 -0.9254 0.02611 0.01978 -0.0548 0.7397 0.0389 -12.250 -0.9160 0.02500 0.01863 -0.0540 0.7325 0.0405 -12.000 -0.9061 0.02392 0.01752 -0.0531 0.7266 0.0420 -11.750 -0.8954 0.02291 0.01647 -0.0523 0.7199 0.0440 -11.500 -0.8848 0.02193 0.01546 -0.0513 0.7133 0.0457 -11.250 -0.8741 0.02098 0.01448 -0.0503 0.7072 0.0475 -11.000 -0.8621 0.02010 0.01357 -0.0493 0.7014 0.0496 -10.750 -0.8518 0.01919 0.01264 -0.0482 0.6954 0.0527 -10.500 -0.8407 0.01835 0.01178 -0.0470 0.6896 0.0564 -10.250 -0.8291 0.01754 0.01096 -0.0457 0.6842 0.0593 -10.000 -0.8183 0.01675 0.01015 -0.0443 0.6779 0.0641 -9.750 -0.8078 0.01600 0.00939 -0.0428 0.6723 0.0689 -9.500 -0.7967 0.01530 0.00868 -0.0412 0.6677 0.0735 -9.250 -0.7864 0.01465 0.00803 -0.0394 0.6625 0.0793 -9.000 -0.7803 0.01403 0.00741 -0.0367 0.6568 0.0851 -8.750 -0.7717 0.01360 0.00697 -0.0341 0.6513 0.0922 -8.500 -0.7551 0.01316 0.00656 -0.0328 0.6470 0.1014 -8.250 -0.7368 0.01274 0.00617 -0.0317 0.6423 0.1122 -8.000 -0.7168 0.01236 0.00582 -0.0309 0.6372 0.1235 -7.750 -0.6957 0.01200 0.00548 -0.0302 0.6320 0.1355 -7.500 -0.6733 0.01163 0.00516 -0.0297 0.6278 0.1480 -7.250 -0.6501 0.01129 0.00486 -0.0293 0.6231 0.1613 -7.000 -0.6266 0.01093 0.00456 -0.0289 0.6186 0.1772 -6.750 -0.6028 0.01058 0.00426 -0.0286 0.6140 0.1968 -6.500 -0.5793 0.01013 0.00394 -0.0284 0.6101 0.2232 -6.250 -0.5546 0.00974 0.00365 -0.0282 0.6056 0.2493 -6.000 -0.5291 0.00940 0.00339 -0.0282 0.6007 0.2735 -5.750 -0.5038 0.00901 0.00312 -0.0281 0.5960 0.3043 -5.500 -0.4784 0.00859 0.00286 -0.0281 0.5924 0.3431 -5.250 -0.4512 0.00830 0.00268 -0.0283 0.5887 0.3733 -5.000 -0.4227 0.00815 0.00257 -0.0286 0.5846 0.3903 -4.750 -0.3936 0.00807 0.00248 -0.0290 0.5802 0.4020 -4.250 -0.3349 0.00793 0.00233 -0.0297 0.5720 0.4189 -4.000 -0.3055 0.00785 0.00226 -0.0301 0.5677 0.4256 -3.750 -0.2759 0.00780 0.00221 -0.0305 0.5635 0.4324 -3.500 -0.2463 0.00778 0.00215 -0.0309 0.5594 0.4387 -3.250 -0.2169 0.00772 0.00211 -0.0313 0.5558 0.4470 -3.000 -0.1869 0.00769 0.00207 -0.0317 0.5525 0.4534 -2.750 -0.1571 0.00765 0.00203 -0.0322 0.5488 0.4582 -2.500 -0.1274 0.00762 0.00199 -0.0326 0.5448 0.4626 -2.250 -0.0976 0.00762 0.00196 -0.0330 0.5406 0.4666 -2.000 -0.0677 0.00762 0.00194 -0.0334 0.5368 0.4704 -1.750 -0.0376 0.00761 0.00192 -0.0339 0.5333 0.4739 -1.500 -0.0078 0.00758 0.00190 -0.0344 0.5297 0.4784 -1.250 0.0220 0.00757 0.00189 -0.0348 0.5260 0.4829 -1.000 0.0518 0.00759 0.00188 -0.0352 0.5223 0.4871 -0.750 0.0817 0.00761 0.00188 -0.0356 0.5190 0.4906 -0.500 0.1117 0.00759 0.00188 -0.0361 0.5160 0.4946 -0.250 0.1416 0.00758 0.00189 -0.0366 0.5123 0.4988 0.000 0.1715 0.00759 0.00189 -0.0370 0.5083 0.5028 0.250 0.2012 0.00762 0.00191 -0.0374 0.5047 0.5063 0.500 0.2310 0.00766 0.00193 -0.0378 0.5012 0.5090 0.750 0.2609 0.00766 0.00195 -0.0383 0.4982 0.5127 1.000 0.2908 0.00766 0.00197 -0.0387 0.4945 0.5169 1.250 0.3205 0.00769 0.00200 -0.0391 0.4904 0.5209 1.500 0.3499 0.00774 0.00204 -0.0395 0.4861 0.5244 1.750 0.3796 0.00778 0.00207 -0.0399 0.4824 0.5274 2.000 0.4094 0.00780 0.00211 -0.0404 0.4789 0.5309 2.250 0.4390 0.00783 0.00216 -0.0408 0.4748 0.5347 2.500 0.4684 0.00787 0.00221 -0.0411 0.4706 0.5386 2.750 0.4975 0.00795 0.00227 -0.0415 0.4662 0.5427 3.000 0.5272 0.00798 0.00233 -0.0419 0.4631 0.5464 3.250 0.5567 0.00802 0.00239 -0.0423 0.4594 0.5505 3.500 0.5860 0.00806 0.00246 -0.0426 0.4553 0.5547 3.750 0.6149 0.00814 0.00254 -0.0429 0.4509 0.5587 4.000 0.6439 0.00821 0.00262 -0.0432 0.4458 0.5626 4.250 0.6729 0.00829 0.00270 -0.0435 0.4385 0.5658 4.500 0.7008 0.00841 0.00281 -0.0437 0.4302 0.5699 4.750 0.7298 0.00846 0.00290 -0.0440 0.4246 0.5743 5.000 0.7581 0.00856 0.00300 -0.0442 0.4180 0.5790 5.250 0.7861 0.00869 0.00312 -0.0444 0.4114 0.5832 5.500 0.8143 0.00878 0.00323 -0.0446 0.4039 0.5874 5.750 0.8414 0.00894 0.00338 -0.0446 0.3945 0.5919 6.000 0.8684 0.00909 0.00353 -0.0446 0.3821 0.5964 6.250 0.8940 0.00933 0.00371 -0.0445 0.3656 0.6006 6.500 0.9174 0.00967 0.00396 -0.0440 0.3426 0.6042 6.750 0.9381 0.01013 0.00429 -0.0431 0.3129 0.6087 7.000 0.9565 0.01068 0.00470 -0.0419 0.2812 0.6137 7.250 0.9742 0.01122 0.00512 -0.0406 0.2542 0.6187 7.500 0.9915 0.01173 0.00552 -0.0391 0.2315 0.6230 7.750 1.0076 0.01221 0.00593 -0.0375 0.2126 0.6275 8.000 1.0213 0.01270 0.00636 -0.0355 0.1950 0.6323 8.250 1.0288 0.01318 0.00679 -0.0324 0.1803 0.6373 8.500 1.0370 0.01375 0.00733 -0.0296 0.1677 0.6422 8.750 1.0457 0.01438 0.00794 -0.0272 0.1563 0.6472 9.000 1.0544 0.01508 0.00862 -0.0249 0.1457 0.6528 9.250 1.0631 0.01585 0.00938 -0.0228 0.1364 0.6580 9.500 1.0696 0.01680 0.01028 -0.0207 0.1243 0.6628 9.750 1.0764 0.01779 0.01125 -0.0187 0.1130 0.6683 10.000 1.0839 0.01881 0.01226 -0.0170 0.1031 0.6746 10.250 1.0945 0.01974 0.01319 -0.0156 0.0978 0.6804 10.500 1.1000 0.02097 0.01440 -0.0139 0.0883 0.6854 10.750 1.1084 0.02209 0.01554 -0.0126 0.0819 0.6916 11.000 1.1175 0.02322 0.01667 -0.0114 0.0766 0.6980 11.500 1.1315 0.02584 0.01932 -0.0090 0.0653 0.7103 11.750 1.1387 0.02720 0.02069 -0.0079 0.0604 0.7168 12.000 1.1460 0.02860 0.02210 -0.0070 0.0566 0.7225 12.250 1.1526 0.03007 0.02361 -0.0061 0.0522 0.7289 12.500 1.1593 0.03157 0.02514 -0.0052 0.0486 0.7366 12.750 1.1666 0.03311 0.02669 -0.0045 0.0457 0.7427 13.000 1.1736 0.03470 0.02833 -0.0039 0.0430 0.7499 13.250 1.1820 0.03622 0.02990 -0.0034 0.0410 0.7574 13.500 1.1887 0.03795 0.03166 -0.0029 0.0392 0.7643 13.750 1.1976 0.03949 0.03326 -0.0025 0.0378 0.7732 14.000 1.2047 0.04126 0.03508 -0.0022 0.0363 0.7815 14.250 1.2112 0.04307 0.03694 -0.0019 0.0346 0.7900 14.500 1.2192 0.04483 0.03876 -0.0017 0.0339 0.7990 14.750 1.2268 0.04660 0.04060 -0.0015 0.0325 0.8095 15.250 1.2394 0.05052 0.04466 -0.0013 0.0307 0.8341 15.500 1.2451 0.05253 0.04677 -0.0012 0.0298 0.8500 15.750 1.2519 0.05437 0.04873 -0.0010 0.0293 0.8727 16.000 1.2604 0.05635 0.05094 -0.0014 0.0285 0.9467 16.500 1.2762 0.06093 0.05561 -0.0030 0.0273 1.0000 16.750 1.2809 0.06339 0.05811 -0.0034 0.0267 1.0000 17.000 1.2871 0.06571 0.06047 -0.0039 0.0263 1.0000 17.250 1.2924 0.06820 0.06301 -0.0045 0.0258 1.0000 17.500 1.2989 0.07056 0.06541 -0.0050 0.0253 1.0000 17.750 1.3031 0.07322 0.06812 -0.0057 0.0249 1.0000 18.000 1.3079 0.07585 0.07079 -0.0065 0.0244 1.0000 18.250 1.3115 0.07865 0.07364 -0.0073 0.0238 1.0000 18.500 1.3146 0.08158 0.07662 -0.0082 0.0234 1.0000 18.750 1.3172 0.08458 0.07966 -0.0091 0.0229 1.0000 19.000 1.3204 0.08757 0.08271 -0.0102 0.0226 1.0000 19.250 1.3249 0.09036 0.08556 -0.0112 0.0222 1.0000 |
Polar data table (+)
Polar graphs
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