XFOIL Version 6.96 Calculated polar for: EPPLER 333 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -8.500 -0.3487 0.08889 0.08562 -0.0248 1.0000 0.0195 -8.250 -0.3484 0.08546 0.08225 -0.0263 1.0000 0.0198 -8.000 -0.3513 0.08176 0.07861 -0.0283 1.0000 0.0201 -7.750 -0.3576 0.07819 0.07509 -0.0304 1.0000 0.0201 -7.500 -0.3645 0.07488 0.07183 -0.0312 0.9972 0.0202 -7.250 -0.3399 0.06885 0.06564 -0.0401 0.9092 0.0202 -7.000 -0.3190 0.06363 0.06015 -0.0461 0.8543 0.0209 -6.750 -0.3098 0.05984 0.05610 -0.0475 0.8148 0.0211 -6.500 -0.3028 0.05644 0.05247 -0.0474 0.7862 0.0213 -6.000 -0.2905 0.04546 0.04070 -0.0444 0.7484 0.0134 -5.750 -0.2791 0.04332 0.03838 -0.0433 0.7290 0.0130 -5.500 -0.2670 0.03861 0.03318 -0.0408 0.7147 0.0138 -5.250 -0.2506 0.03890 0.03349 -0.0407 0.6965 0.0159 -5.000 -0.2344 0.03610 0.03034 -0.0390 0.6824 0.0166 -4.750 -0.2179 0.03327 0.02717 -0.0371 0.6694 0.0157 -4.250 -0.1802 0.02606 0.01884 -0.0321 0.6464 0.0133 -4.000 -0.1585 0.02406 0.01646 -0.0306 0.6345 0.0132 -3.750 -0.1352 0.02227 0.01430 -0.0294 0.6230 0.0130 -3.500 -0.1106 0.02070 0.01238 -0.0283 0.6119 0.0130 -3.250 -0.0849 0.01928 0.01064 -0.0274 0.6005 0.0130 -3.000 -0.0586 0.01809 0.00919 -0.0267 0.5898 0.0132 -2.750 -0.0327 0.01719 0.00808 -0.0259 0.5799 0.0134 -2.500 -0.0075 0.01633 0.00708 -0.0251 0.5697 0.0138 -2.250 0.0169 0.01565 0.00635 -0.0244 0.5598 0.0146 -2.000 0.0411 0.01515 0.00577 -0.0235 0.5509 0.0157 -1.750 0.0658 0.01478 0.00529 -0.0227 0.5417 0.0180 -1.500 0.0899 0.01441 0.00488 -0.0219 0.5334 0.0211 -1.250 0.1140 0.01403 0.00440 -0.0210 0.5249 0.0260 -1.000 0.1382 0.01368 0.00404 -0.0201 0.5169 0.0417 -0.750 0.1607 0.01320 0.00379 -0.0191 0.5093 0.1113 -0.500 0.1748 0.01116 0.00447 -0.0152 0.5029 0.8902 -0.250 0.2397 0.01202 0.00507 -0.0210 0.4932 0.9437 0.000 0.3294 0.01245 0.00519 -0.0329 0.4818 0.9693 0.250 0.3627 0.01252 0.00510 -0.0341 0.4751 0.9754 0.500 0.3947 0.01250 0.00496 -0.0351 0.4677 0.9772 0.750 0.4250 0.01253 0.00484 -0.0357 0.4616 0.9793 1.000 0.4544 0.01254 0.00478 -0.0362 0.4549 0.9814 1.250 0.4825 0.01259 0.00472 -0.0364 0.4491 0.9837 1.500 0.5095 0.01265 0.00471 -0.0364 0.4432 0.9858 1.750 0.5395 0.01267 0.00466 -0.0370 0.4370 0.9873 2.000 0.5690 0.01273 0.00462 -0.0375 0.4320 0.9888 2.250 0.5984 0.01277 0.00465 -0.0381 0.4259 0.9904 2.500 0.6268 0.01284 0.00466 -0.0384 0.4206 0.9920 2.750 0.6547 0.01293 0.00470 -0.0386 0.4157 0.9935 3.000 0.6828 0.01301 0.00478 -0.0389 0.4102 0.9951 3.250 0.7111 0.01309 0.00483 -0.0392 0.4051 0.9963 3.500 0.7396 0.01319 0.00490 -0.0396 0.4002 0.9976 3.750 0.7683 0.01328 0.00501 -0.0400 0.3948 0.9990 4.000 0.7953 0.01341 0.00510 -0.0401 0.3900 1.0000 4.250 0.8182 0.01355 0.00526 -0.0393 0.3854 1.0000 4.500 0.8411 0.01368 0.00543 -0.0385 0.3804 1.0000 4.750 0.8637 0.01384 0.00558 -0.0377 0.3757 1.0000 5.000 0.8861 0.01401 0.00576 -0.0368 0.3713 1.0000 5.250 0.9085 0.01416 0.00599 -0.0359 0.3661 1.0000 5.500 0.9304 0.01434 0.00618 -0.0350 0.3613 1.0000 5.750 0.9521 0.01453 0.00639 -0.0340 0.3566 1.0000 6.000 0.9738 0.01471 0.00665 -0.0330 0.3511 1.0000 6.250 0.9948 0.01491 0.00688 -0.0319 0.3461 1.0000 6.500 1.0158 0.01512 0.00714 -0.0308 0.3409 1.0000 6.750 1.0364 0.01531 0.00741 -0.0296 0.3351 1.0000 7.000 1.0563 0.01555 0.00766 -0.0283 0.3300 1.0000 7.250 1.0763 0.01575 0.00798 -0.0270 0.3238 1.0000 7.500 1.0954 0.01598 0.00826 -0.0256 0.3177 1.0000 7.750 1.1143 0.01622 0.00857 -0.0242 0.3116 1.0000 8.000 1.1325 0.01646 0.00889 -0.0226 0.3046 1.0000 8.250 1.1500 0.01672 0.00922 -0.0209 0.2982 1.0000 8.500 1.1672 0.01697 0.00956 -0.0192 0.2910 1.0000 8.750 1.1832 0.01726 0.00991 -0.0173 0.2838 1.0000 9.000 1.1985 0.01754 0.01028 -0.0152 0.2755 1.0000 9.250 1.2134 0.01785 0.01067 -0.0132 0.2673 1.0000 9.500 1.2266 0.01820 0.01105 -0.0108 0.2588 1.0000 9.750 1.2402 0.01856 0.01149 -0.0086 0.2487 1.0000 10.000 1.2530 0.01896 0.01195 -0.0063 0.2391 1.0000 10.250 1.2646 0.01943 0.01245 -0.0039 0.2287 1.0000 10.750 1.2861 0.02054 0.01365 0.0008 0.2064 1.0000 11.000 1.2944 0.02121 0.01435 0.0034 0.1941 1.0000 11.250 1.2997 0.02194 0.01511 0.0064 0.1830 1.0000 11.500 1.3033 0.02282 0.01602 0.0093 0.1716 1.0000 11.750 1.3061 0.02388 0.01710 0.0119 0.1609 1.0000 12.000 1.3070 0.02518 0.01843 0.0142 0.1505 1.0000 12.250 1.3063 0.02678 0.02005 0.0161 0.1396 1.0000 12.500 1.3063 0.02855 0.02189 0.0175 0.1298 1.0000 12.750 1.3047 0.03063 0.02403 0.0185 0.1215 1.0000 13.000 1.3000 0.03320 0.02662 0.0190 0.1136 1.0000 13.250 1.2980 0.03571 0.02922 0.0193 0.1058 1.0000 13.500 1.2921 0.03875 0.03231 0.0193 0.0992 1.0000 13.750 1.2869 0.04184 0.03547 0.0191 0.0928 1.0000 14.000 1.2798 0.04525 0.03895 0.0186 0.0873 1.0000 14.250 1.2735 0.04867 0.04244 0.0181 0.0820 1.0000 14.500 1.2637 0.05257 0.04640 0.0173 0.0774 1.0000 14.750 1.2579 0.05606 0.04999 0.0166 0.0728 1.0000 15.000 1.2485 0.06011 0.05409 0.0156 0.0688 1.0000 15.250 1.2404 0.06416 0.05823 0.0145 0.0653 1.0000 15.500 1.2332 0.06820 0.06235 0.0133 0.0610 1.0000 15.750 1.2239 0.07264 0.06685 0.0118 0.0579 1.0000 16.000 1.2171 0.07685 0.07115 0.0104 0.0547 1.0000 16.250 1.2111 0.08101 0.07544 0.0089 0.0517 1.0000 16.500 1.2018 0.08579 0.08026 0.0071 0.0485 1.0000 16.750 1.1940 0.09042 0.08496 0.0053 0.0463 1.0000