XFOIL Version 6.96 Calculated polar for: EPPLER 327 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -11.250 -0.3480 0.10299 0.10147 -0.0187 1.0000 0.0086 -11.000 -0.3491 0.09847 0.09696 -0.0203 1.0000 0.0086 -6.000 -0.4394 0.01325 0.00888 -0.0152 0.6742 0.0127 -5.750 -0.4212 0.01223 0.00733 -0.0123 0.6599 0.0143 -4.750 -0.3373 0.01422 0.00776 -0.0080 0.6234 0.0088 -4.500 -0.3116 0.01394 0.00739 -0.0074 0.6096 0.0086 -4.250 -0.2870 0.01284 0.00622 -0.0068 0.5973 0.0084 -4.000 -0.2635 0.01215 0.00545 -0.0058 0.5857 0.0083 -3.750 -0.2407 0.01159 0.00479 -0.0047 0.5739 0.0083 -3.500 -0.2175 0.01117 0.00431 -0.0037 0.5622 0.0083 -3.250 -0.1939 0.01080 0.00387 -0.0028 0.5512 0.0083 -3.000 -0.1700 0.01051 0.00351 -0.0019 0.5412 0.0084 -2.750 -0.1458 0.01023 0.00317 -0.0011 0.5309 0.0086 -2.500 -0.1221 0.00990 0.00278 -0.0002 0.5211 0.0093 -2.250 -0.0972 0.00973 0.00255 0.0005 0.5113 0.0112 -2.000 -0.0732 0.00943 0.00228 0.0013 0.5023 0.0232 -1.750 -0.0502 0.00911 0.00212 0.0022 0.4940 0.0729 -1.500 -0.0272 0.00880 0.00200 0.0031 0.4854 0.1362 -1.250 -0.0112 0.00800 0.00180 0.0050 0.4779 0.3244 -1.000 -0.0173 0.00607 0.00151 0.0114 0.4721 0.7710 -0.750 0.0062 0.00626 0.00179 0.0128 0.4643 0.8296 -0.500 0.0329 0.00643 0.00195 0.0134 0.4571 0.8439 -0.250 0.0598 0.00660 0.00203 0.0138 0.4493 0.8515 0.000 0.0870 0.00674 0.00218 0.0143 0.4424 0.8598 0.250 0.1136 0.00694 0.00232 0.0147 0.4352 0.8673 0.500 0.1407 0.00702 0.00238 0.0151 0.4292 0.8724 0.750 0.1679 0.00717 0.00249 0.0155 0.4226 0.8768 1.000 0.1956 0.00723 0.00250 0.0155 0.4164 0.8787 1.250 0.2239 0.00726 0.00248 0.0153 0.4105 0.8798 1.500 0.2518 0.00731 0.00247 0.0152 0.4045 0.8810 1.750 0.2801 0.00735 0.00247 0.0151 0.3991 0.8821 2.000 0.3083 0.00739 0.00247 0.0149 0.3935 0.8830 2.250 0.3361 0.00747 0.00248 0.0148 0.3878 0.8838 2.500 0.3644 0.00747 0.00248 0.0146 0.3833 0.8848 2.750 0.3922 0.00749 0.00247 0.0145 0.3780 0.8860 3.000 0.4196 0.00756 0.00251 0.0145 0.3727 0.8870 3.250 0.4478 0.00759 0.00254 0.0143 0.3684 0.8879 3.500 0.4758 0.00765 0.00258 0.0142 0.3634 0.8888 3.750 0.5032 0.00774 0.00263 0.0141 0.3583 0.8898 4.000 0.5311 0.00779 0.00269 0.0140 0.3539 0.8908 4.250 0.5590 0.00785 0.00275 0.0139 0.3492 0.8918 4.500 0.5864 0.00794 0.00282 0.0138 0.3443 0.8930 4.750 0.6139 0.00803 0.00290 0.0137 0.3395 0.8943 5.000 0.6418 0.00809 0.00296 0.0136 0.3349 0.8955 5.250 0.6691 0.00819 0.00305 0.0135 0.3297 0.8966 5.500 0.6964 0.00829 0.00315 0.0134 0.3247 0.8977 5.750 0.7242 0.00836 0.00323 0.0132 0.3196 0.8987 6.000 0.7513 0.00848 0.00333 0.0131 0.3141 0.8996 6.250 0.7783 0.00856 0.00343 0.0131 0.3091 0.9008 6.500 0.8054 0.00863 0.00352 0.0130 0.3036 0.9021 6.750 0.8315 0.00877 0.00365 0.0131 0.2972 0.9034 7.000 0.8585 0.00886 0.00377 0.0131 0.2920 0.9047 7.250 0.8848 0.00899 0.00390 0.0132 0.2856 0.9062 7.500 0.9109 0.00913 0.00406 0.0133 0.2791 0.9078 7.750 0.9371 0.00927 0.00421 0.0133 0.2720 0.9094 8.000 0.9628 0.00944 0.00438 0.0134 0.2650 0.9111 8.250 0.9887 0.00960 0.00456 0.0135 0.2569 0.9126 8.500 1.0141 0.00979 0.00475 0.0137 0.2486 0.9142 8.750 1.0388 0.01002 0.00496 0.0139 0.2394 0.9157 9.000 1.0634 0.01020 0.00516 0.0142 0.2299 0.9178 9.250 1.0867 0.01045 0.00541 0.0147 0.2188 0.9198 9.500 1.1094 0.01075 0.00569 0.0153 0.2069 0.9220 9.750 1.1311 0.01110 0.00601 0.0160 0.1925 0.9245 10.000 1.1521 0.01148 0.00635 0.0168 0.1781 0.9272 10.250 1.1722 0.01191 0.00674 0.0177 0.1632 0.9299 10.500 1.1909 0.01234 0.00714 0.0189 0.1495 0.9334 10.750 1.2075 0.01282 0.00759 0.0204 0.1353 0.9375 11.000 1.2234 0.01334 0.00807 0.0220 0.1220 0.9421 11.250 1.2383 0.01385 0.00857 0.0237 0.1106 0.9472 11.500 1.2502 0.01438 0.00909 0.0260 0.0994 0.9543 11.750 1.2594 0.01491 0.00963 0.0288 0.0897 0.9644 12.000 1.2748 0.01564 0.01035 0.0299 0.0789 0.9766 12.250 1.2986 0.01653 0.01121 0.0289 0.0683 0.9869 12.500 1.3157 0.01748 0.01213 0.0289 0.0589 1.0000 12.750 1.3227 0.01827 0.01293 0.0311 0.0534 1.0000 13.000 1.3259 0.01934 0.01399 0.0335 0.0469 1.0000 13.250 1.3290 0.02055 0.01522 0.0354 0.0427 1.0000 13.500 1.3309 0.02198 0.01667 0.0370 0.0376 1.0000 13.750 1.3313 0.02373 0.01844 0.0382 0.0342 1.0000 14.000 1.3356 0.02537 0.02015 0.0389 0.0321 1.0000 14.250 1.3315 0.02785 0.02264 0.0395 0.0276 1.0000 14.500 1.3329 0.03003 0.02489 0.0396 0.0259 1.0000 14.750 1.3287 0.03285 0.02774 0.0396 0.0233 1.0000 15.000 1.3269 0.03554 0.03052 0.0394 0.0219 1.0000 15.250 1.3241 0.03841 0.03345 0.0391 0.0206 1.0000 15.500 1.3154 0.04197 0.03705 0.0385 0.0185 1.0000 15.750 1.3099 0.04524 0.04042 0.0380 0.0180 1.0000 16.000 1.3050 0.04852 0.04379 0.0373 0.0174 1.0000 16.250 1.2976 0.05214 0.04750 0.0365 0.0167 1.0000 16.500 1.2883 0.05611 0.05152 0.0354 0.0156 1.0000 16.750 1.2789 0.06024 0.05572 0.0342 0.0148 1.0000 17.000 1.2714 0.06419 0.05977 0.0329 0.0142 1.0000 17.250 1.2651 0.06810 0.06376 0.0316 0.0137 1.0000 17.500 1.2574 0.07227 0.06801 0.0301 0.0132 1.0000 17.750 1.2479 0.07677 0.07256 0.0285 0.0122 1.0000 18.000 1.2380 0.08140 0.07726 0.0267 0.0115 1.0000 18.250 1.2286 0.08610 0.08205 0.0248 0.0115 1.0000 18.500 1.2225 0.09037 0.08641 0.0230 0.0111 1.0000 18.750 1.2168 0.09464 0.09076 0.0212 0.0105 1.0000 19.000 1.2092 0.09928 0.09547 0.0192 0.0102 1.0000 19.250 1.2007 0.10415 0.10042 0.0169 0.0100 1.0000