XFOIL Version 6.96 Calculated polar for: EPPLER 329 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 = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -9.000 -0.3389 0.08723 0.08512 -0.0343 1.0000 0.0157 -8.750 -0.3431 0.08331 0.08124 -0.0360 1.0000 0.0158 -8.500 -0.3509 0.07907 0.07705 -0.0382 1.0000 0.0159 -8.250 -0.3655 0.07478 0.07278 -0.0407 1.0000 0.0158 -8.000 -0.3758 0.07067 0.06867 -0.0429 0.9976 0.0158 -7.750 -0.3678 0.06507 0.06298 -0.0485 0.9808 0.0161 -7.500 -0.3560 0.05973 0.05750 -0.0527 0.9438 0.0165 -7.250 -0.3186 0.04997 0.04712 -0.0624 0.9162 0.0174 -7.000 -0.2925 0.04494 0.04183 -0.0674 0.8664 0.0178 -6.750 -0.2663 0.02970 0.02642 -0.0621 0.7655 0.0182 -6.500 -0.2596 0.02725 0.02379 -0.0604 0.7459 0.0185 -6.250 -0.2512 0.02479 0.02113 -0.0587 0.7285 0.0189 -6.000 -0.2413 0.02226 0.01839 -0.0569 0.7129 0.0196 -5.750 -0.2317 0.01939 0.01481 -0.0526 0.7000 0.0215 -5.500 -0.2215 0.01595 0.01131 -0.0517 0.6870 0.0220 -5.250 -0.2053 0.01442 0.00966 -0.0507 0.6728 0.0225 -5.000 -0.1879 0.01301 0.00809 -0.0495 0.6596 0.0233 -4.750 -0.1692 0.01156 0.00640 -0.0481 0.6477 0.0247 -4.500 -0.1521 0.00967 0.00406 -0.0459 0.6373 0.0272 -4.250 -0.1311 0.00868 0.00296 -0.0452 0.6254 0.0281 -4.000 -0.1050 0.01739 0.01033 -0.0441 0.6323 0.0141 -3.750 -0.0793 0.01576 0.00859 -0.0434 0.6203 0.0133 -3.500 -0.0538 0.01466 0.00732 -0.0427 0.6086 0.0127 -3.250 -0.0288 0.01379 0.00632 -0.0418 0.5976 0.0125 -3.000 -0.0050 0.01313 0.00554 -0.0408 0.5874 0.0127 -2.750 0.0185 0.01260 0.00491 -0.0397 0.5771 0.0132 -2.500 0.0424 0.01221 0.00445 -0.0388 0.5672 0.0139 -2.250 0.0646 0.01176 0.00393 -0.0377 0.5576 0.0152 -2.000 0.0890 0.01143 0.00357 -0.0369 0.5483 0.0179 -1.750 0.1130 0.01117 0.00327 -0.0361 0.5399 0.0232 -1.500 0.1368 0.01081 0.00299 -0.0352 0.5312 0.0450 -1.000 0.1499 0.00800 0.00282 -0.0275 0.5173 0.7958 -0.750 0.1726 0.00834 0.00312 -0.0257 0.5099 0.8348 -0.500 0.1955 0.00868 0.00344 -0.0239 0.5027 0.8582 -0.250 0.2174 0.00904 0.00375 -0.0218 0.4957 0.8740 0.000 0.2394 0.00933 0.00401 -0.0198 0.4892 0.8852 0.250 0.2624 0.00951 0.00412 -0.0183 0.4823 0.8942 0.500 0.2838 0.00980 0.00434 -0.0162 0.4764 0.9040 0.750 0.3063 0.00993 0.00445 -0.0145 0.4704 0.9119 1.000 0.3323 0.00997 0.00442 -0.0141 0.4644 0.9144 1.250 0.3587 0.01000 0.00437 -0.0139 0.4587 0.9161 1.500 0.3854 0.01000 0.00432 -0.0138 0.4529 0.9179 1.750 0.4118 0.01004 0.00428 -0.0138 0.4476 0.9195 2.000 0.4386 0.01007 0.00426 -0.0137 0.4423 0.9213 2.250 0.4659 0.01008 0.00424 -0.0138 0.4369 0.9226 2.500 0.4922 0.01011 0.00421 -0.0136 0.4321 0.9238 2.750 0.5185 0.01016 0.00422 -0.0135 0.4274 0.9250 3.000 0.5450 0.01017 0.00423 -0.0133 0.4225 0.9265 3.250 0.5715 0.01023 0.00425 -0.0132 0.4178 0.9279 3.500 0.5979 0.01034 0.00430 -0.0131 0.4133 0.9293 3.750 0.6248 0.01036 0.00435 -0.0131 0.4089 0.9308 4.000 0.6515 0.01041 0.00438 -0.0131 0.4043 0.9323 4.250 0.6778 0.01052 0.00444 -0.0130 0.3999 0.9340 4.500 0.7043 0.01061 0.00453 -0.0130 0.3957 0.9359 4.750 0.7312 0.01066 0.00461 -0.0130 0.3912 0.9375 5.000 0.7570 0.01072 0.00465 -0.0128 0.3869 0.9390 5.250 0.7826 0.01087 0.00476 -0.0126 0.3824 0.9405 5.500 0.8087 0.01090 0.00486 -0.0124 0.3783 0.9422 5.750 0.8345 0.01097 0.00495 -0.0123 0.3738 0.9441 6.000 0.8598 0.01109 0.00505 -0.0120 0.3693 0.9462 6.250 0.8854 0.01122 0.00520 -0.0119 0.3650 0.9484 6.500 0.9108 0.01129 0.00532 -0.0116 0.3605 0.9509 6.750 0.9355 0.01137 0.00541 -0.0113 0.3558 0.9532 7.000 0.9604 0.01154 0.00558 -0.0110 0.3511 0.9556 7.250 0.9857 0.01159 0.00571 -0.0108 0.3463 0.9583 7.500 1.0104 0.01169 0.00584 -0.0105 0.3413 0.9614 7.750 1.0345 0.01188 0.00602 -0.0101 0.3360 0.9645 8.000 1.0615 0.01194 0.00618 -0.0103 0.3304 0.9673 8.250 1.0877 0.01209 0.00634 -0.0104 0.3246 0.9707 8.500 1.1139 0.01226 0.00656 -0.0105 0.3188 0.9744 8.750 1.1440 0.01242 0.00679 -0.0115 0.3121 0.9772 9.000 1.1743 0.01268 0.00706 -0.0126 0.3055 0.9800 9.250 1.2056 0.01287 0.00733 -0.0139 0.2976 0.9831 9.500 1.2362 0.01315 0.00764 -0.0152 0.2900 0.9864 9.750 1.2680 0.01342 0.00795 -0.0167 0.2808 0.9896 10.000 1.2987 0.01371 0.00830 -0.0180 0.2715 0.9944 10.250 1.3181 0.01404 0.00863 -0.0172 0.2625 1.0000 10.500 1.3341 0.01431 0.00893 -0.0156 0.2527 1.0000 10.750 1.3511 0.01466 0.00931 -0.0142 0.2427 1.0000 11.000 1.3658 0.01509 0.00973 -0.0125 0.2316 1.0000 11.250 1.3792 0.01562 0.01024 -0.0107 0.2201 1.0000 11.750 1.4031 0.01686 0.01145 -0.0068 0.1954 1.0000 12.000 1.4130 0.01759 0.01219 -0.0048 0.1833 1.0000 12.250 1.4205 0.01847 0.01305 -0.0025 0.1709 1.0000 12.500 1.4260 0.01949 0.01406 -0.0003 0.1590 1.0000 12.750 1.4301 0.02066 0.01523 0.0019 0.1483 1.0000 13.000 1.4314 0.02209 0.01666 0.0039 0.1377 1.0000 13.500 1.4322 0.02556 0.02015 0.0070 0.1188 1.0000 13.750 1.4307 0.02770 0.02232 0.0081 0.1102 1.0000 14.000 1.4262 0.03027 0.02490 0.0089 0.1029 1.0000 14.250 1.4247 0.03273 0.02742 0.0094 0.0961 1.0000 14.500 1.4184 0.03579 0.03051 0.0096 0.0895 1.0000 14.750 1.4129 0.03887 0.03364 0.0097 0.0840 1.0000 15.000 1.4045 0.04236 0.03718 0.0095 0.0792 1.0000 15.250 1.3980 0.04573 0.04061 0.0093 0.0742 1.0000 15.500 1.3861 0.04977 0.04470 0.0088 0.0703 1.0000 15.750 1.3798 0.05331 0.04832 0.0082 0.0660 1.0000 16.000 1.3690 0.05748 0.05254 0.0074 0.0625 1.0000 16.250 1.3580 0.06182 0.05694 0.0064 0.0593 1.0000 16.500 1.3517 0.06565 0.06085 0.0055 0.0559 1.0000 16.750 1.3398 0.07029 0.06553 0.0042 0.0527 1.0000 17.000 1.3299 0.07480 0.07010 0.0029 0.0503 1.0000 17.250 1.3236 0.07887 0.07427 0.0017 0.0472 1.0000 17.500 1.3135 0.08355 0.07900 0.0001 0.0448 1.0000 17.750 1.3020 0.08854 0.08403 -0.0016 0.0425 1.0000