XFOIL Version 6.96 Calculated polar for: NACA 65(4)-421 a=0.5 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 ------ -------- --------- --------- -------- -------- -------- -17.750 -0.6881 0.08792 0.08440 -0.0847 0.8489 0.0296 -17.500 -0.7354 0.07759 0.07378 -0.0905 0.8451 0.0295 -17.250 -0.7678 0.07041 0.06635 -0.0938 0.8400 0.0295 -17.000 -0.7814 0.06616 0.06192 -0.0955 0.8341 0.0297 -16.750 -0.7983 0.06178 0.05732 -0.0967 0.8289 0.0298 -16.500 -0.8120 0.05788 0.05325 -0.0977 0.8235 0.0300 -16.250 -0.8214 0.05479 0.04999 -0.0981 0.8178 0.0303 -16.000 -0.8308 0.05177 0.04675 -0.0981 0.8124 0.0305 -15.750 -0.8383 0.04907 0.04388 -0.0980 0.8072 0.0308 -15.500 -0.8445 0.04665 0.04127 -0.0975 0.8016 0.0311 -15.250 -0.8487 0.04438 0.03879 -0.0968 0.7963 0.0314 -15.000 -0.8549 0.04255 0.03675 -0.0957 0.7912 0.0317 -14.750 -0.8614 0.04082 0.03483 -0.0944 0.7860 0.0319 -14.500 -0.8664 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-0.0557 0.6349 0.6573 -0.250 0.2759 0.01090 0.00500 -0.0562 0.6332 0.6608 0.000 0.3052 0.01094 0.00499 -0.0567 0.6317 0.6638 0.250 0.3346 0.01093 0.00499 -0.0573 0.6303 0.6672 0.500 0.3639 0.01100 0.00506 -0.0578 0.6289 0.6704 0.750 0.3930 0.01117 0.00523 -0.0583 0.6271 0.6737 1.000 0.4210 0.01121 0.00530 -0.0587 0.6258 0.6774 1.250 0.4489 0.01127 0.00538 -0.0590 0.6241 0.6813 1.500 0.4769 0.01131 0.00545 -0.0594 0.6223 0.6850 1.750 0.5050 0.01135 0.00555 -0.0597 0.6206 0.6887 2.000 0.5333 0.01142 0.00565 -0.0601 0.6190 0.6925 2.250 0.5619 0.01149 0.00574 -0.0605 0.6173 0.6966 2.500 0.5908 0.01154 0.00579 -0.0611 0.6156 0.7008 2.750 0.6200 0.01157 0.00583 -0.0616 0.6141 0.7048 3.000 0.6492 0.01163 0.00592 -0.0621 0.6126 0.7090 3.250 0.6785 0.01176 0.00607 -0.0627 0.6111 0.7137 3.500 0.7067 0.01197 0.00630 -0.0631 0.6093 0.7187 3.750 0.7328 0.01206 0.00645 -0.0632 0.6076 0.7235 4.000 0.7588 0.01213 0.00663 -0.0632 0.6057 0.7282 4.250 0.7852 0.01223 0.00680 -0.0633 0.6036 0.7333 4.500 0.8125 0.01231 0.00692 -0.0635 0.6015 0.7387 4.750 0.8406 0.01236 0.00700 -0.0639 0.5994 0.7439 5.000 0.8692 0.01236 0.00706 -0.0643 0.5974 0.7492 5.250 0.8990 0.01238 0.00710 -0.0649 0.5954 0.7550 5.500 0.9298 0.01252 0.00722 -0.0657 0.5929 0.7611 5.750 0.9517 0.01253 0.00738 -0.0650 0.5897 0.7672 6.000 0.9754 0.01251 0.00746 -0.0645 0.5859 0.7738 6.250 1.0028 0.01243 0.00740 -0.0646 0.5821 0.7807 6.500 1.0333 0.01220 0.00717 -0.0652 0.5776 0.7867 6.750 1.0542 0.01215 0.00721 -0.0641 0.5718 0.7938 7.000 1.0764 0.01201 0.00712 -0.0633 0.5653 0.8014 7.250 1.1041 0.01185 0.00695 -0.0633 0.5592 0.8081 7.500 1.1157 0.01185 0.00709 -0.0606 0.5517 0.8171 7.750 1.1350 0.01176 0.00700 -0.0592 0.5436 0.8254 8.000 1.1435 0.01187 0.00725 -0.0559 0.5363 0.8354 8.250 1.1508 0.01193 0.00735 -0.0523 0.5282 0.8457 8.500 1.1539 0.01224 0.00775 -0.0483 0.5192 0.8580 8.750 1.1571 0.01257 0.00813 -0.0444 0.5085 0.8707 9.000 1.1593 0.01304 0.00867 -0.0406 0.4967 0.8857 9.250 1.1597 0.01363 0.00934 -0.0366 0.4829 0.9045 9.500 1.1571 0.01443 0.01017 -0.0325 0.4651 0.9316 9.750 1.1706 0.01605 0.01174 -0.0334 0.4308 0.9705 10.000 1.1605 0.01816 0.01368 -0.0304 0.3969 1.0000 10.250 1.1416 0.02061 0.01595 -0.0261 0.3654 1.0000 10.500 1.1263 0.02304 0.01822 -0.0225 0.3364 1.0000 10.750 1.1104 0.02572 0.02074 -0.0191 0.3064 1.0000 11.000 1.0971 0.02840 0.02327 -0.0162 0.2779 1.0000 11.250 1.0859 0.03106 0.02578 -0.0136 0.2504 1.0000 11.500 1.0779 0.03358 0.02816 -0.0115 0.2222 1.0000 11.750 1.0700 0.03621 0.03062 -0.0095 0.1934 1.0000 12.000 1.0640 0.03876 0.03301 -0.0078 0.1662 1.0000 12.250 1.0589 0.04130 0.03537 -0.0063 0.1380 1.0000 12.500 1.0528 0.04399 0.03786 -0.0048 0.1076 1.0000 12.750 1.0453 0.04685 0.04050 -0.0034 0.0763 1.0000 13.000 1.0409 0.04954 0.04301 -0.0022 0.0527 1.0000 13.250 1.0420 0.05184 0.04522 -0.0014 0.0420 1.0000 13.500 1.0464 0.05391 0.04726 -0.0008 0.0376 1.0000 13.750 1.0525 0.05586 0.04922 -0.0003 0.0340 1.0000 14.000 1.0574 0.05798 0.05136 0.0001 0.0322 1.0000 14.250 1.0650 0.05987 0.05330 0.0004 0.0308 1.0000 14.500 1.0708 0.06194 0.05539 0.0007 0.0293 1.0000 14.750 1.0733 0.06441 0.05788 0.0009 0.0283 1.0000 15.000 1.0810 0.06637 0.05990 0.0011 0.0273 1.0000 15.250 1.0876 0.06848 0.06206 0.0011 0.0265 1.0000 15.500 1.0930 0.07075 0.06438 0.0012 0.0260 1.0000 15.750 1.0977 0.07310 0.06676 0.0012 0.0253 1.0000 16.000 1.1011 0.07563 0.06932 0.0011 0.0249 1.0000 16.250 1.1007 0.07859 0.07231 0.0011 0.0243 1.0000 16.500 1.1082 0.08073 0.07452 0.0009 0.0239 1.0000 16.750 1.1135 0.08315 0.07700 0.0007 0.0237 1.0000 17.000 1.1197 0.08547 0.07938 0.0004 0.0233 1.0000 17.250 1.1256 0.08785 0.08181 0.0000 0.0228 1.0000 17.500 1.1305 0.09034 0.08435 -0.0003 0.0224 1.0000 17.750 1.1367 0.09267 0.08673 -0.0008 0.0221 1.0000