XFOIL Version 6.96 Calculated polar for: GOE 432 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 -0.3480 0.10027 0.09683 -0.0273 1.0000 0.0221 -8.250 -0.3496 0.09761 0.09422 -0.0268 1.0000 0.0221 -8.000 -0.3532 0.09514 0.09181 -0.0259 1.0000 0.0221 -7.750 -0.2703 0.07827 0.07521 -0.0241 1.0000 0.0210 -7.500 -0.2735 0.07555 0.07253 -0.0226 1.0000 0.0197 -7.250 -0.2811 0.07289 0.06993 -0.0213 1.0000 0.0188 -6.750 -0.3701 0.07886 0.07575 -0.0228 0.9996 0.0157 -6.500 -0.3460 0.07398 0.07083 -0.0293 0.9953 0.0154 -6.250 -0.3197 0.06847 0.06529 -0.0371 0.9902 0.0152 -6.000 -0.2890 0.06257 0.05932 -0.0457 0.9855 0.0151 -5.750 -0.2552 0.05506 0.05168 -0.0558 0.9792 0.0156 -5.500 -0.2231 0.05031 0.04683 -0.0625 0.9745 0.0167 -5.250 -0.1876 0.04251 0.03876 -0.0706 0.9681 0.0166 -5.000 -0.1504 0.03493 0.03077 -0.0773 0.9635 0.0169 -4.750 -0.1206 0.02878 0.02411 -0.0804 0.9564 0.0174 -4.500 -0.0855 0.02407 0.01876 -0.0832 0.9525 0.0192 -4.250 -0.0585 0.01962 0.01339 -0.0833 0.9459 0.0218 -4.000 -0.0261 0.01807 0.01154 -0.0844 0.9406 0.0233 -3.750 0.0116 0.01735 0.01063 -0.0863 0.9368 0.0265 -3.500 0.0382 0.01617 0.00910 -0.0856 0.9271 0.0300 -3.250 0.0725 0.01557 0.00846 -0.0868 0.9208 0.0333 -3.000 0.1008 0.01511 0.00780 -0.0865 0.9101 0.0381 -2.750 0.1294 0.01432 0.00695 -0.0865 0.8996 0.0418 -2.500 0.1613 0.01392 0.00647 -0.0870 0.8899 0.0471 -2.250 0.1941 0.01342 0.00582 -0.0877 0.8789 0.0508 -2.000 0.2263 0.01267 0.00506 -0.0884 0.8648 0.0551 -1.750 0.2602 0.01216 0.00447 -0.0892 0.8449 0.0583 -1.500 0.2962 0.01176 0.00392 -0.0904 0.8202 0.0624 -1.250 0.3284 0.01142 0.00345 -0.0909 0.7909 0.0667 -1.000 0.3573 0.01123 0.00311 -0.0908 0.7603 0.0712 -0.750 0.3844 0.01115 0.00286 -0.0903 0.7292 0.0766 -0.500 0.4103 0.01109 0.00268 -0.0896 0.6963 0.0858 -0.250 0.4351 0.01102 0.00254 -0.0887 0.6619 0.1142 0.000 0.4579 0.01074 0.00254 -0.0877 0.6266 0.2527 0.250 0.4806 0.01066 0.00254 -0.0866 0.5928 0.3507 0.750 0.5509 0.00971 0.00259 -0.0895 0.5355 1.0000 1.000 0.5754 0.00992 0.00263 -0.0887 0.5190 1.0000 1.250 0.6002 0.01013 0.00268 -0.0879 0.5052 1.0000 1.500 0.6251 0.01033 0.00275 -0.0872 0.4925 1.0000 1.750 0.6503 0.01051 0.00284 -0.0866 0.4799 1.0000 2.000 0.6753 0.01070 0.00293 -0.0859 0.4670 1.0000 2.250 0.7003 0.01089 0.00304 -0.0852 0.4538 1.0000 2.500 0.7253 0.01109 0.00315 -0.0846 0.4423 1.0000 2.750 0.7503 0.01129 0.00329 -0.0839 0.4310 1.0000 3.000 0.7753 0.01148 0.00342 -0.0833 0.4185 1.0000 3.250 0.8001 0.01168 0.00357 -0.0826 0.4052 1.0000 3.500 0.8247 0.01189 0.00374 -0.0819 0.3917 1.0000 3.750 0.8494 0.01211 0.00391 -0.0812 0.3788 1.0000 4.000 0.8738 0.01234 0.00410 -0.0805 0.3654 1.0000 4.250 0.8980 0.01259 0.00432 -0.0798 0.3507 1.0000 4.500 0.9219 0.01286 0.00454 -0.0790 0.3344 1.0000 4.750 0.9456 0.01315 0.00478 -0.0782 0.3175 1.0000 5.000 0.9691 0.01346 0.00505 -0.0774 0.2996 1.0000 5.250 0.9925 0.01379 0.00534 -0.0766 0.2808 1.0000 5.500 1.0155 0.01414 0.00564 -0.0758 0.2580 1.0000 5.750 1.0376 0.01458 0.00598 -0.0748 0.2335 1.0000 6.000 1.0591 0.01508 0.00638 -0.0738 0.2124 1.0000 6.250 1.0809 0.01556 0.00681 -0.0728 0.1996 1.0000 6.500 1.1033 0.01599 0.00724 -0.0719 0.1924 1.0000 6.750 1.1251 0.01645 0.00772 -0.0709 0.1867 1.0000 7.000 1.1469 0.01691 0.00824 -0.0699 0.1820 1.0000 7.250 1.1690 0.01735 0.00875 -0.0690 0.1776 1.0000 7.500 1.1901 0.01786 0.00931 -0.0679 0.1733 1.0000 7.750 1.2102 0.01846 0.00993 -0.0667 0.1694 1.0000 8.000 1.2323 0.01889 0.01052 -0.0658 0.1658 1.0000 8.250 1.2532 0.01940 0.01114 -0.0647 0.1607 1.0000 8.500 1.2720 0.02005 0.01180 -0.0634 0.1532 1.0000 8.750 1.2929 0.02043 0.01230 -0.0624 0.1429 1.0000 9.000 1.3138 0.02082 0.01280 -0.0614 0.1325 1.0000 9.250 1.3344 0.02120 0.01325 -0.0603 0.1186 1.0000 9.500 1.3529 0.02174 0.01376 -0.0591 0.0976 1.0000 9.750 1.3665 0.02268 0.01457 -0.0572 0.0795 1.0000 10.000 1.3791 0.02371 0.01558 -0.0552 0.0578 1.0000 10.250 1.3807 0.02544 0.01707 -0.0517 0.0304 1.0000 10.500 1.3846 0.02693 0.01856 -0.0485 0.0215 1.0000 10.750 1.3896 0.02830 0.02003 -0.0455 0.0179 1.0000 11.000 1.3952 0.02963 0.02151 -0.0428 0.0160 1.0000 11.250 1.3989 0.03110 0.02312 -0.0401 0.0148 1.0000 11.500 1.3988 0.03290 0.02508 -0.0373 0.0137 1.0000 11.750 1.3954 0.03501 0.02739 -0.0346 0.0129 1.0000 12.000 1.3960 0.03692 0.02948 -0.0326 0.0123 1.0000 12.250 1.3948 0.03912 0.03186 -0.0309 0.0118 1.0000 12.500 1.3922 0.04161 0.03451 -0.0296 0.0111 1.0000 12.750 1.3869 0.04461 0.03769 -0.0288 0.0108 1.0000 13.000 1.3805 0.04799 0.04123 -0.0285 0.0104 1.0000 13.250 1.3725 0.05185 0.04526 -0.0288 0.0102 1.0000 13.500 1.3637 0.05615 0.04971 -0.0297 0.0100 1.0000 13.750 1.3536 0.06094 0.05467 -0.0312 0.0098 1.0000 14.000 1.3425 0.06610 0.05999 -0.0330 0.0097 1.0000 14.250 1.3312 0.07149 0.06552 -0.0350 0.0097 1.0000 14.500 1.3190 0.07713 0.07131 -0.0373 0.0096 1.0000 14.750 1.3056 0.08310 0.07741 -0.0397 0.0094 1.0000 15.000 1.2939 0.08893 0.08337 -0.0421 0.0093 1.0000