XFOIL Version 6.96 Calculated polar for: NACA 66(2)-215 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 ------ -------- --------- --------- -------- -------- -------- -15.500 -0.7694 0.07351 0.07061 -0.0743 1.0000 0.0130 -15.250 -0.8105 0.06354 0.06037 -0.0797 1.0000 0.0130 -15.000 -0.8376 0.05714 0.05376 -0.0820 1.0000 0.0130 -14.750 -0.8511 0.05315 0.04961 -0.0827 1.0000 0.0131 -14.500 -0.8647 0.04886 0.04511 -0.0835 0.9809 0.0132 -14.250 -0.8575 0.04548 0.04152 -0.0868 0.9643 0.0135 -14.000 -0.8561 0.04153 0.03726 -0.0894 0.9521 0.0138 -13.750 -0.8540 0.03839 0.03382 -0.0904 0.9387 0.0139 -13.500 -0.8518 0.03617 0.03135 -0.0898 0.9253 0.0142 -13.250 -0.8500 0.03419 0.02913 -0.0884 0.9141 0.0144 -12.750 -0.8401 0.03103 0.02552 -0.0852 0.8958 0.0148 -12.250 -0.8232 0.02828 0.02241 -0.0821 0.8818 0.0152 -12.000 -0.8120 0.02722 0.02123 -0.0807 0.8753 0.0154 -11.750 -0.7994 0.02635 0.02026 -0.0794 0.8697 0.0156 -11.500 -0.7857 0.02560 0.01942 -0.0782 0.8638 0.0158 -11.250 -0.7718 0.02496 0.01871 -0.0769 0.8585 0.0161 -11.000 -0.7564 0.02419 0.01783 -0.0757 0.8540 0.0164 -10.750 -0.7404 0.02353 0.01709 -0.0746 0.8494 0.0167 -10.500 -0.7235 0.02283 0.01629 -0.0736 0.8451 0.0171 -10.250 -0.7057 0.02206 0.01540 -0.0726 0.8414 0.0174 -10.000 -0.6871 0.02132 0.01456 -0.0717 0.8380 0.0177 -9.750 -0.6684 0.02061 0.01376 -0.0708 0.8344 0.0180 -9.500 -0.6496 0.01996 0.01301 -0.0699 0.8308 0.0184 -9.250 -0.6308 0.01939 0.01234 -0.0689 0.8275 0.0187 -9.000 -0.6135 0.01866 0.01156 -0.0677 0.8245 0.0191 -8.750 -0.5956 0.01807 0.01094 -0.0667 0.8215 0.0195 -8.500 -0.5770 0.01759 0.01044 -0.0656 0.8183 0.0199 -8.250 -0.5579 0.01718 0.00999 -0.0647 0.8151 0.0205 -8.000 -0.5393 0.01672 0.00948 -0.0635 0.8120 0.0210 -7.750 -0.5207 0.01630 0.00900 -0.0624 0.8093 0.0217 -7.500 -0.5020 0.01588 0.00853 -0.0612 0.8067 0.0223 -7.250 -0.4834 0.01548 0.00808 -0.0600 0.8040 0.0229 -7.000 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-2.000 -0.0603 0.00777 0.00264 -0.0374 0.7629 0.7102 -1.750 -0.0322 0.00785 0.00271 -0.0375 0.7617 0.7228 -1.500 -0.0038 0.00792 0.00274 -0.0378 0.7605 0.7315 -1.250 0.0242 0.00798 0.00283 -0.0379 0.7590 0.7383 -1.000 0.0522 0.00806 0.00291 -0.0380 0.7574 0.7464 -0.750 0.0805 0.00810 0.00294 -0.0383 0.7559 0.7508 -0.500 0.1092 0.00810 0.00295 -0.0387 0.7545 0.7522 -0.250 0.1380 0.00811 0.00296 -0.0391 0.7531 0.7536 0.000 0.1667 0.00812 0.00297 -0.0395 0.7518 0.7549 0.250 0.1956 0.00813 0.00298 -0.0399 0.7505 0.7562 0.500 0.2244 0.00814 0.00299 -0.0403 0.7492 0.7576 0.750 0.2533 0.00816 0.00300 -0.0408 0.7478 0.7590 1.000 0.2824 0.00816 0.00299 -0.0412 0.7458 0.7604 1.250 0.3104 0.00816 0.00301 -0.0415 0.7425 0.7619 1.500 0.3383 0.00815 0.00302 -0.0417 0.7384 0.7635 1.750 0.3667 0.00814 0.00301 -0.0420 0.7346 0.7651 2.000 0.3950 0.00808 0.00294 -0.0421 0.7283 0.7663 2.250 0.4215 0.00802 0.00293 -0.0420 0.7194 0.7676 2.500 0.4493 0.00799 0.00291 -0.0420 0.7121 0.7689 2.750 0.4758 0.00795 0.00289 -0.0418 0.7009 0.7703 3.000 0.5017 0.00793 0.00287 -0.0415 0.6853 0.7718 3.250 0.5263 0.00793 0.00285 -0.0409 0.6593 0.7734 3.500 0.5407 0.00824 0.00280 -0.0383 0.5718 0.7754 3.750 0.5383 0.00931 0.00326 -0.0327 0.4507 0.7779 4.000 0.5397 0.01025 0.00374 -0.0282 0.3491 0.7803 4.250 0.5434 0.01105 0.00416 -0.0240 0.2654 0.7825 4.500 0.5458 0.01173 0.00455 -0.0196 0.1944 0.7849 4.750 0.5501 0.01250 0.00502 -0.0157 0.1265 0.7875 5.000 0.5600 0.01318 0.00548 -0.0130 0.0771 0.7901 5.250 0.5736 0.01375 0.00592 -0.0109 0.0477 0.7926 5.500 0.5916 0.01415 0.00628 -0.0095 0.0395 0.7950 5.750 0.6103 0.01453 0.00664 -0.0083 0.0354 0.7973 6.000 0.6289 0.01490 0.00703 -0.0071 0.0327 0.7994 6.250 0.6481 0.01524 0.00743 -0.0059 0.0310 0.8016 6.500 0.6666 0.01564 0.00784 -0.0048 0.0289 0.8041 6.750 0.6843 0.01609 0.00831 -0.0035 0.0275 0.8068 7.000 0.7020 0.01656 0.00881 -0.0022 0.0262 0.8096 7.250 0.7210 0.01698 0.00927 -0.0012 0.0253 0.8125 7.500 0.7393 0.01742 0.00975 -0.0001 0.0241 0.8151 7.750 0.7571 0.01788 0.01025 0.0011 0.0231 0.8178 8.000 0.7736 0.01842 0.01082 0.0024 0.0219 0.8211 8.250 0.7897 0.01903 0.01147 0.0037 0.0210 0.8248 8.500 0.8075 0.01954 0.01203 0.0047 0.0202 0.8283 8.750 0.8240 0.02012 0.01266 0.0060 0.0196 0.8317 9.000 0.8409 0.02066 0.01327 0.0071 0.0189 0.8351 9.250 0.8571 0.02128 0.01393 0.0083 0.0183 0.8389 9.500 0.8731 0.02192 0.01461 0.0094 0.0178 0.8430 9.750 0.8883 0.02263 0.01536 0.0106 0.0172 0.8469 10.000 0.9011 0.02348 0.01627 0.0122 0.0169 0.8511 10.250 0.9161 0.02422 0.01710 0.0134 0.0166 0.8558 10.500 0.9309 0.02501 0.01796 0.0146 0.0163 0.8606 10.750 0.9452 0.02580 0.01885 0.0158 0.0159 0.8654 11.000 0.9592 0.02663 0.01976 0.0171 0.0155 0.8708 11.250 0.9735 0.02746 0.02067 0.0182 0.0151 0.8769 11.500 0.9866 0.02834 0.02166 0.0195 0.0150 0.8831 11.750 1.0002 0.02919 0.02258 0.0207 0.0146 0.8905 12.000 1.0131 0.03007 0.02354 0.0219 0.0143 0.8980 12.250 1.0257 0.03096 0.02451 0.0230 0.0141 0.9069 12.500 1.0369 0.03201 0.02565 0.0243 0.0139 0.9163 12.750 1.0479 0.03308 0.02679 0.0255 0.0136 0.9274 13.000 1.0587 0.03443 0.02827 0.0265 0.0133 0.9403 13.250 1.0754 0.03578 0.02975 0.0262 0.0133 0.9555 13.500 1.0937 0.03727 0.03141 0.0252 0.0131 0.9919 14.000 1.1106 0.04035 0.03473 0.0273 0.0127 1.0000 14.250 1.1179 0.04216 0.03667 0.0281 0.0126 1.0000 14.500 1.1241 0.04408 0.03873 0.0289 0.0124 1.0000 14.750 1.1292 0.04610 0.04089 0.0295 0.0123 1.0000 15.000 1.1325 0.04834 0.04328 0.0302 0.0122 1.0000 15.250 1.1348 0.05071 0.04578 0.0307 0.0121 1.0000 15.500 1.1351 0.05335 0.04857 0.0311 0.0119 1.0000 15.750 1.1341 0.05620 0.05157 0.0313 0.0118 1.0000 16.000 1.1304 0.05947 0.05501 0.0313 0.0118 1.0000 16.250 1.1279 0.06265 0.05832 0.0310 0.0116 1.0000 16.500 1.1247 0.06608 0.06187 0.0304 0.0115 1.0000 16.750 1.1129 0.07093 0.06692 0.0293 0.0115 1.0000 17.000 1.1013 0.07596 0.07214 0.0278 0.0115 1.0000 17.250 1.1014 0.07940 0.07564 0.0262 0.0113 1.0000 17.500 1.0832 0.08606 0.08251 0.0234 0.0113 1.0000 17.750 1.0695 0.09233 0.08894 0.0202 0.0112 1.0000 18.000 1.0582 0.09849 0.09522 0.0168 0.0111 1.0000 18.250 1.0301 0.10833 0.10530 0.0112 0.0112 1.0000