XFOIL Version 6.96 Calculated polar for: EPPLER 339 AIRFOIL 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 ------ -------- --------- --------- -------- -------- -------- -10.250 -0.1501 0.09084 0.08765 -0.0532 0.7061 0.0104 -10.000 -0.1482 0.08710 0.08388 -0.0543 0.6931 0.0104 -9.750 -0.1483 0.08296 0.07969 -0.0556 0.6798 0.0104 -9.500 -0.1460 0.07955 0.07623 -0.0566 0.6677 0.0104 -9.250 -0.1461 0.07548 0.07213 -0.0580 0.6574 0.0104 -9.000 -0.1478 0.07127 0.06789 -0.0595 0.6479 0.0104 -8.750 -0.1502 0.06702 0.06363 -0.0611 0.6390 0.0104 -8.500 -0.1536 0.06280 0.05939 -0.0629 0.6304 0.0104 -8.000 -0.2180 0.06478 0.06121 -0.0733 0.6401 0.0103 -7.500 -0.2366 0.05791 0.05418 -0.0708 0.6215 0.0079 -7.250 -0.2355 0.05539 0.05156 -0.0699 0.6114 0.0077 -7.000 -0.2329 0.05254 0.04859 -0.0689 0.6021 0.0075 -6.750 -0.2307 0.04909 0.04499 -0.0675 0.5932 0.0074 -6.500 -0.2243 0.04614 0.04188 -0.0661 0.5844 0.0071 -6.250 -0.2182 0.04257 0.03811 -0.0641 0.5768 0.0070 -6.000 -0.2112 0.03870 0.03400 -0.0618 0.5697 0.0069 -5.750 -0.2023 0.03494 0.02996 -0.0592 0.5626 0.0069 -5.500 -0.1920 0.03082 0.02550 -0.0563 0.5562 0.0072 -5.250 -0.1801 0.02667 0.02094 -0.0532 0.5493 0.0073 -5.000 -0.1670 0.02211 0.01582 -0.0499 0.5432 0.0075 -4.750 -0.1471 0.01916 0.01228 -0.0478 0.5359 0.0080 -4.500 -0.1246 0.01776 0.01058 -0.0467 0.5274 0.0082 -4.250 -0.1003 0.01681 0.00945 -0.0459 0.5193 0.0083 -4.000 -0.0755 0.01584 0.00826 -0.0451 0.5116 0.0083 -3.750 -0.0502 0.01509 0.00735 -0.0445 0.5050 0.0083 -3.500 -0.0251 0.01443 0.00656 -0.0438 0.4979 0.0083 -3.250 -0.0004 0.01387 0.00589 -0.0431 0.4913 0.0084 -3.000 0.0246 0.01340 0.00534 -0.0424 0.4844 0.0085 -2.750 0.0491 0.01301 0.00488 -0.0416 0.4775 0.0087 -2.500 0.0737 0.01266 0.00447 -0.0409 0.4716 0.0088 -2.250 0.0985 0.01235 0.00411 -0.0402 0.4657 0.0091 -2.000 0.1231 0.01209 0.00379 -0.0395 0.4601 0.0095 -1.750 0.1483 0.01187 0.00352 -0.0389 0.4550 0.0099 -1.500 0.1735 0.01166 0.00326 -0.0383 0.4496 0.0107 -1.250 0.1988 0.01151 0.00306 -0.0377 0.4439 0.0119 -1.000 0.2243 0.01138 0.00289 -0.0372 0.4391 0.0137 -0.750 0.2501 0.01124 0.00275 -0.0367 0.4343 0.0185 -0.500 0.2754 0.01110 0.00265 -0.0362 0.4297 0.0357 -0.250 0.2997 0.01090 0.00260 -0.0355 0.4254 0.0830 0.000 0.3197 0.01023 0.00252 -0.0344 0.4216 0.2805 0.500 0.3336 0.00887 0.00312 -0.0248 0.4142 0.8984 0.750 0.3564 0.00908 0.00326 -0.0233 0.4102 0.9099 1.000 0.3784 0.00926 0.00338 -0.0218 0.4068 0.9205 1.250 0.4010 0.00948 0.00359 -0.0200 0.4034 0.9316 1.500 0.4261 0.00962 0.00367 -0.0191 0.3996 0.9381 1.750 0.4528 0.00967 0.00366 -0.0189 0.3955 0.9393 2.000 0.4789 0.00974 0.00366 -0.0186 0.3919 0.9406 2.250 0.5056 0.00978 0.00366 -0.0185 0.3890 0.9416 2.500 0.5320 0.00981 0.00366 -0.0183 0.3856 0.9427 2.750 0.5580 0.00987 0.00368 -0.0180 0.3822 0.9441 3.000 0.5835 0.00994 0.00370 -0.0176 0.3785 0.9455 3.250 0.6088 0.01002 0.00373 -0.0173 0.3754 0.9466 3.500 0.6350 0.01007 0.00377 -0.0171 0.3726 0.9477 3.750 0.6611 0.01012 0.00381 -0.0169 0.3694 0.9487 4.000 0.6878 0.01019 0.00387 -0.0168 0.3659 0.9495 4.250 0.7142 0.01028 0.00393 -0.0167 0.3627 0.9504 4.500 0.7401 0.01040 0.00401 -0.0164 0.3596 0.9515 4.750 0.7668 0.01047 0.00411 -0.0164 0.3567 0.9525 5.000 0.7934 0.01055 0.00420 -0.0163 0.3537 0.9534 5.250 0.8194 0.01065 0.00429 -0.0162 0.3501 0.9545 5.500 0.8451 0.01076 0.00439 -0.0159 0.3468 0.9556 5.750 0.8700 0.01090 0.00452 -0.0156 0.3436 0.9568 6.000 0.8960 0.01099 0.00464 -0.0155 0.3407 0.9580 6.250 0.9216 0.01108 0.00476 -0.0153 0.3371 0.9593 6.500 0.9466 0.01120 0.00489 -0.0150 0.3337 0.9606 6.750 0.9710 0.01134 0.00504 -0.0146 0.3299 0.9619 7.000 0.9965 0.01149 0.00519 -0.0144 0.3266 0.9632 7.250 1.0227 0.01160 0.00536 -0.0144 0.3228 0.9645 7.500 1.0482 0.01174 0.00553 -0.0143 0.3185 0.9659 7.750 1.0728 0.01191 0.00571 -0.0140 0.3143 0.9674 8.000 1.0977 0.01207 0.00591 -0.0138 0.3102 0.9690 8.250 1.1226 0.01222 0.00610 -0.0136 0.3051 0.9707 8.500 1.1457 0.01241 0.00631 -0.0131 0.2996 0.9728 8.750 1.1708 0.01261 0.00654 -0.0130 0.2947 0.9744 9.000 1.1973 0.01281 0.00679 -0.0133 0.2892 0.9758 9.250 1.2223 0.01307 0.00707 -0.0133 0.2834 0.9776 9.500 1.2483 0.01329 0.00736 -0.0135 0.2779 0.9794 9.750 1.2724 0.01358 0.00767 -0.0134 0.2703 0.9818 10.000 1.2962 0.01387 0.00799 -0.0133 0.2631 0.9845 10.250 1.3206 0.01427 0.00840 -0.0134 0.2535 0.9870 10.500 1.3449 0.01465 0.00880 -0.0136 0.2435 0.9904 10.750 1.3676 0.01510 0.00927 -0.0136 0.2337 0.9968 11.000 1.3793 0.01556 0.00973 -0.0114 0.2243 1.0000 11.250 1.3898 0.01605 0.01022 -0.0091 0.2146 1.0000 11.500 1.4009 0.01662 0.01080 -0.0070 0.2052 1.0000 11.750 1.4101 0.01733 0.01151 -0.0049 0.1950 1.0000 12.000 1.4170 0.01819 0.01236 -0.0026 0.1842 1.0000 12.250 1.4230 0.01916 0.01333 -0.0005 0.1732 1.0000 12.500 1.4276 0.02028 0.01445 0.0016 0.1627 1.0000 12.750 1.4304 0.02161 0.01579 0.0035 0.1532 1.0000 13.000 1.4312 0.02320 0.01739 0.0052 0.1442 1.0000 13.250 1.4320 0.02494 0.01916 0.0066 0.1358 1.0000 13.500 1.4313 0.02695 0.02120 0.0077 0.1278 1.0000 13.750 1.4279 0.02933 0.02360 0.0086 0.1209 1.0000 14.000 1.4265 0.03168 0.02600 0.0092 0.1141 1.0000 14.250 1.4185 0.03475 0.02909 0.0098 0.1061 1.0000 14.500 1.4114 0.03786 0.03225 0.0100 0.1000 1.0000 14.750 1.4046 0.04103 0.03548 0.0101 0.0945 1.0000 15.000 1.3940 0.04469 0.03917 0.0100 0.0888 1.0000 15.250 1.3845 0.04834 0.04287 0.0098 0.0828 1.0000 15.500 1.3785 0.05170 0.04631 0.0095 0.0802 1.0000 15.750 1.3677 0.05574 0.05039 0.0089 0.0750 1.0000 16.000 1.3530 0.06035 0.05502 0.0080 0.0684 1.0000 16.250 1.3498 0.06369 0.05845 0.0073 0.0668 1.0000 16.500 1.3334 0.06876 0.06352 0.0061 0.0589 1.0000 16.750 1.3294 0.07235 0.06719 0.0052 0.0569 1.0000 17.000 1.3129 0.07769 0.07251 0.0037 0.0488 1.0000 17.250 1.3048 0.08201 0.07688 0.0024 0.0462 1.0000 17.500 1.3011 0.08578 0.08073 0.0011 0.0440 1.0000 17.750 1.2962 0.08977 0.08478 -0.0002 0.0416 1.0000 18.000 1.2898 0.09407 0.08914 -0.0017 0.0389 1.0000 18.250 1.2851 0.09815 0.09328 -0.0033 0.0364 1.0000