XFOIL Version 6.96 Calculated polar for: GOE 14K 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 ------ -------- --------- --------- -------- -------- -------- -15.750 -0.8322 0.08139 0.07921 -0.0786 0.9917 0.0095 -15.500 -0.8791 0.06806 0.06574 -0.0873 0.9902 0.0095 -15.250 -0.9112 0.05588 0.05336 -0.0976 0.9887 0.0095 -15.000 -0.9486 0.04296 0.04004 -0.1109 0.9870 0.0094 -14.750 -0.9460 0.03978 0.03676 -0.1138 0.9861 0.0097 -14.500 -0.9605 0.03652 0.03331 -0.1123 0.9819 0.0096 -14.250 -0.9514 0.03516 0.03192 -0.1120 0.9797 0.0100 -14.000 -0.9648 0.03175 0.02820 -0.1100 0.9774 0.0097 -13.750 -0.9502 0.03060 0.02697 -0.1098 0.9765 0.0100 -13.500 -0.9284 0.02997 0.02628 -0.1103 0.9759 0.0104 -13.250 -0.9335 0.02836 0.02451 -0.1060 0.9712 0.0104 -13.000 -0.9260 0.02710 0.02312 -0.1037 0.9682 0.0106 -12.750 -0.9135 0.02586 0.02173 -0.1022 0.9665 0.0107 -12.500 -0.8929 0.02512 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0.00765 0.00442 -0.1148 0.8163 0.9632 2.000 0.6973 0.00771 0.00446 -0.1163 0.8040 0.9650 2.250 0.7287 0.00777 0.00449 -0.1172 0.7943 0.9670 2.500 0.7492 0.00791 0.00465 -0.1155 0.7837 0.9716 2.750 0.7737 0.00801 0.00475 -0.1147 0.7698 0.9753 3.000 0.7945 0.00810 0.00472 -0.1131 0.7312 0.9783 3.250 0.7880 0.00883 0.00502 -0.1052 0.6335 0.9860 3.500 0.7816 0.01003 0.00542 -0.0982 0.4626 0.9921 3.750 0.7997 0.01079 0.00567 -0.0967 0.3558 0.9964 4.000 0.8275 0.01132 0.00574 -0.0975 0.2544 1.0000 4.250 0.8310 0.01190 0.00603 -0.0926 0.1933 1.0000 4.500 0.8376 0.01238 0.00630 -0.0885 0.1493 1.0000 4.750 0.8479 0.01276 0.00654 -0.0850 0.1177 1.0000 5.000 0.8586 0.01317 0.00681 -0.0817 0.0891 1.0000 5.250 0.8724 0.01346 0.00704 -0.0790 0.0771 1.0000 5.500 0.8868 0.01372 0.00728 -0.0764 0.0690 1.0000 5.750 0.9009 0.01400 0.00753 -0.0738 0.0630 1.0000 6.000 0.9160 0.01426 0.00779 -0.0714 0.0585 1.0000 6.250 0.9325 0.01447 0.00802 -0.0693 0.0555 1.0000 6.500 0.9478 0.01476 0.00829 -0.0669 0.0510 1.0000 6.750 0.9637 0.01502 0.00856 -0.0647 0.0468 1.0000 7.000 0.9792 0.01531 0.00883 -0.0625 0.0418 1.0000 7.250 0.9946 0.01562 0.00913 -0.0602 0.0372 1.0000 7.500 1.0094 0.01598 0.00946 -0.0579 0.0325 1.0000 7.750 1.0250 0.01633 0.00981 -0.0557 0.0289 1.0000 8.000 1.0396 0.01674 0.01021 -0.0533 0.0265 1.0000 8.250 1.0539 0.01718 0.01067 -0.0509 0.0239 1.0000 8.500 1.0693 0.01754 0.01106 -0.0488 0.0226 1.0000 8.750 1.0844 0.01794 0.01147 -0.0466 0.0213 1.0000 9.000 1.0967 0.01857 0.01212 -0.0440 0.0196 1.0000 9.250 1.1121 0.01895 0.01255 -0.0419 0.0188 1.0000 9.500 1.1270 0.01939 0.01303 -0.0398 0.0179 1.0000 9.750 1.1418 0.01985 0.01352 -0.0377 0.0172 1.0000 10.000 1.1553 0.02042 0.01409 -0.0354 0.0161 1.0000 10.250 1.1650 0.02125 0.01498 -0.0325 0.0153 1.0000 10.500 1.1788 0.02179 0.01559 -0.0303 0.0150 1.0000 10.750 1.1914 0.02244 0.01631 -0.0279 0.0147 1.0000 11.000 1.2078 0.02278 0.01668 -0.0263 0.0139 1.0000 11.250 1.2203 0.02342 0.01737 -0.0241 0.0135 1.0000 11.500 1.2320 0.02413 0.01813 -0.0217 0.0131 1.0000 11.750 1.2442 0.02478 0.01882 -0.0196 0.0128 1.0000 12.000 1.2484 0.02608 0.02018 -0.0162 0.0121 1.0000 12.250 1.2545 0.02723 0.02143 -0.0133 0.0118 1.0000 12.500 1.2676 0.02785 0.02212 -0.0113 0.0117 1.0000 12.750 1.2791 0.02860 0.02295 -0.0093 0.0113 1.0000 13.000 1.2893 0.02946 0.02387 -0.0070 0.0111 1.0000 13.250 1.3016 0.03014 0.02460 -0.0053 0.0105 1.0000 13.500 1.3088 0.03123 0.02578 -0.0028 0.0105 1.0000 13.750 1.3181 0.03217 0.02679 -0.0007 0.0103 1.0000 14.000 1.3246 0.03334 0.02802 0.0017 0.0100 1.0000 14.250 1.3274 0.03484 0.02963 0.0044 0.0099 1.0000 14.500 1.3337 0.03603 0.03089 0.0065 0.0097 1.0000 14.750 1.3305 0.03808 0.03303 0.0095 0.0093 1.0000 15.000 1.3277 0.04016 0.03524 0.0123 0.0092 1.0000 15.250 1.3272 0.04208 0.03729 0.0147 0.0090 1.0000 15.500 1.3233 0.04440 0.03975 0.0172 0.0089 1.0000 15.750 1.3320 0.04553 0.04095 0.0185 0.0088 1.0000 16.000 1.3376 0.04699 0.04251 0.0199 0.0084 1.0000 16.250 1.3368 0.04911 0.04473 0.0216 0.0085 1.0000 16.500 1.3279 0.05221 0.04798 0.0236 0.0083 1.0000 16.750 1.3295 0.05428 0.05015 0.0247 0.0081 1.0000 17.000 1.3147 0.05829 0.05432 0.0261 0.0082 1.0000 17.250 1.3048 0.06196 0.05815 0.0269 0.0082 1.0000 17.500 1.2936 0.06599 0.06232 0.0273 0.0083 1.0000 17.750 1.2957 0.06854 0.06493 0.0272 0.0077 1.0000 18.000 1.2743 0.07439 0.07098 0.0265 0.0080 1.0000 18.250 1.2633 0.07917 0.07588 0.0254 0.0079 1.0000 18.500 1.2530 0.08405 0.08088 0.0239 0.0078 1.0000 18.750 1.2425 0.08931 0.08623 0.0218 0.0075 1.0000 19.000 1.1892 0.10234 0.09960 0.0162 0.0080 1.0000 19.250 1.1733 0.10921 0.10658 0.0128 0.0079 1.0000