XFOIL Version 6.96 Calculated polar for: RAE 102 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 ------ -------- --------- --------- -------- -------- -------- -13.750 -0.9800 0.06146 0.05923 -0.0266 1.0000 0.0067 -13.500 -0.9898 0.05627 0.05394 -0.0301 1.0000 0.0068 -13.250 -1.0238 0.04798 0.04533 -0.0345 1.0000 0.0066 -13.000 -1.0398 0.04326 0.04043 -0.0362 1.0000 0.0066 -12.750 -1.0535 0.03942 0.03641 -0.0365 1.0000 0.0067 -12.500 -1.0592 0.03694 0.03381 -0.0358 1.0000 0.0068 -12.250 -1.0655 0.03463 0.03137 -0.0342 1.0000 0.0069 -12.000 -1.0650 0.03321 0.02986 -0.0323 1.0000 0.0070 -11.750 -1.0788 0.03046 0.02684 -0.0281 1.0000 0.0069 -11.500 -1.0757 0.02929 0.02557 -0.0252 1.0000 0.0071 -11.250 -1.0649 0.02835 0.02455 -0.0234 1.0000 0.0072 -11.000 -1.0575 0.02670 0.02272 -0.0212 1.0000 0.0073 -10.750 -1.0449 0.02554 0.02144 -0.0195 1.0000 0.0075 -10.500 -1.0334 0.02400 0.01972 -0.0176 1.0000 0.0077 -10.250 -1.0189 0.02277 0.01834 -0.0160 1.0000 0.0078 -10.000 -1.0036 0.02154 0.01696 -0.0144 1.0000 0.0080 -9.750 -0.9867 0.02049 0.01578 -0.0129 1.0000 0.0082 -9.500 -0.9686 0.01958 0.01475 -0.0116 1.0000 0.0086 -9.250 -0.9501 0.01868 0.01374 -0.0102 1.0000 0.0088 -9.000 -0.9284 0.01829 0.01329 -0.0093 1.0000 0.0091 -8.750 -0.9144 0.01672 0.01154 -0.0072 1.0000 0.0095 -8.500 -0.8992 0.01547 0.01018 -0.0053 1.0000 0.0100 -8.250 -0.8793 0.01486 0.00952 -0.0040 1.0000 0.0105 -8.000 -0.8586 0.01435 0.00897 -0.0028 1.0000 0.0109 -7.750 -0.8380 0.01382 0.00840 -0.0016 1.0000 0.0114 -7.500 -0.8171 0.01334 0.00787 -0.0004 1.0000 0.0121 -7.250 -0.7959 0.01293 0.00741 0.0008 1.0000 0.0126 -7.000 -0.7743 0.01257 0.00700 0.0020 1.0000 0.0129 -6.750 -0.7584 0.01162 0.00595 0.0041 1.0000 0.0143 -6.500 -0.7375 0.01125 0.00557 0.0054 1.0000 0.0154 -6.250 -0.7163 0.01095 0.00527 0.0066 1.0000 0.0166 -6.000 -0.6949 0.01071 0.00501 0.0078 1.0000 0.0177 -5.750 -0.6666 0.01016 0.00438 0.0075 0.9987 0.0200 -5.500 -0.6319 0.00980 0.00404 0.0058 0.9963 0.0230 -5.250 -0.5969 0.00953 0.00375 0.0041 0.9936 0.0255 -5.000 -0.5644 0.00912 0.00337 0.0029 0.9897 0.0324 -4.750 -0.5300 0.00878 0.00305 0.0013 0.9859 0.0415 -4.500 -0.4949 0.00845 0.00278 -0.0005 0.9828 0.0563 -4.250 -0.4638 0.00806 0.00252 -0.0014 0.9759 0.0834 -4.000 -0.4291 0.00760 0.00225 -0.0032 0.9706 0.1285 -3.750 -0.3986 0.00705 0.00198 -0.0041 0.9605 0.1974 -3.500 -0.3684 0.00642 0.00171 -0.0050 0.9478 0.2904 -3.250 -0.3421 0.00576 0.00146 -0.0051 0.9301 0.4043 -3.000 -0.3160 0.00549 0.00133 -0.0047 0.9099 0.4671 -2.750 -0.2902 0.00536 0.00124 -0.0042 0.8885 0.5028 -2.500 -0.2644 0.00529 0.00117 -0.0037 0.8682 0.5280 -2.250 -0.2383 0.00525 0.00111 -0.0032 0.8483 0.5492 -2.000 -0.2123 0.00521 0.00105 -0.0028 0.8294 0.5683 -1.750 -0.1861 0.00519 0.00100 -0.0023 0.8114 0.5867 -1.500 -0.1597 0.00517 0.00096 -0.0019 0.7943 0.6041 -1.250 -0.1331 0.00516 0.00093 -0.0016 0.7780 0.6208 -1.000 -0.1065 0.00514 0.00091 -0.0013 0.7628 0.6371 -0.750 -0.0799 0.00512 0.00089 -0.0010 0.7479 0.6532 -0.500 -0.0532 0.00511 0.00088 -0.0006 0.7327 0.6693 -0.250 -0.0266 0.00510 0.00087 -0.0003 0.7172 0.6854 0.000 0.0000 0.00510 0.00087 0.0000 0.7014 0.7015 0.250 0.0266 0.00510 0.00087 0.0003 0.6854 0.7172 0.500 0.0533 0.00511 0.00088 0.0006 0.6693 0.7327 0.750 0.0799 0.00512 0.00089 0.0010 0.6532 0.7479 1.000 0.1065 0.00514 0.00091 0.0013 0.6371 0.7629 1.250 0.1331 0.00516 0.00093 0.0016 0.6207 0.7780 1.500 0.1597 0.00517 0.00096 0.0019 0.6039 0.7942 1.750 0.1861 0.00519 0.00100 0.0023 0.5865 0.8114 2.000 0.2123 0.00521 0.00105 0.0028 0.5689 0.8294 2.250 0.2383 0.00525 0.00111 0.0032 0.5498 0.8483 2.500 0.2644 0.00529 0.00117 0.0037 0.5276 0.8682 2.750 0.2903 0.00536 0.00124 0.0042 0.5026 0.8885 3.000 0.3160 0.00549 0.00133 0.0047 0.4665 0.9099 3.250 0.3423 0.00575 0.00146 0.0050 0.4066 0.9300 3.500 0.3686 0.00641 0.00170 0.0050 0.2920 0.9479 3.750 0.3986 0.00705 0.00198 0.0041 0.1971 0.9606 4.000 0.4293 0.00759 0.00225 0.0032 0.1287 0.9707 4.250 0.4639 0.00806 0.00252 0.0014 0.0836 0.9761 4.500 0.4947 0.00845 0.00278 0.0005 0.0560 0.9831 4.750 0.5304 0.00878 0.00305 -0.0014 0.0415 0.9861 5.000 0.5646 0.00912 0.00337 -0.0029 0.0324 0.9898 5.250 0.5971 0.00953 0.00375 -0.0041 0.0256 0.9937 5.500 0.6322 0.00980 0.00404 -0.0059 0.0229 0.9964 5.750 0.6670 0.01017 0.00440 -0.0076 0.0198 0.9989 6.000 0.6942 0.01070 0.00499 -0.0077 0.0177 1.0000 6.250 0.7155 0.01096 0.00528 -0.0064 0.0167 1.0000 6.500 0.7368 0.01125 0.00557 -0.0052 0.0154 1.0000 6.750 0.7576 0.01162 0.00595 -0.0040 0.0142 1.0000 7.000 0.7737 0.01258 0.00701 -0.0018 0.0129 1.0000 7.250 0.7955 0.01291 0.00739 -0.0007 0.0126 1.0000 7.500 0.8168 0.01333 0.00786 0.0004 0.0120 1.0000 7.750 0.8376 0.01383 0.00841 0.0017 0.0114 1.0000 8.000 0.8583 0.01435 0.00898 0.0029 0.0110 1.0000 8.250 0.8791 0.01487 0.00953 0.0040 0.0105 1.0000 8.500 0.8991 0.01548 0.01019 0.0053 0.0101 1.0000 8.750 0.9144 0.01674 0.01156 0.0072 0.0095 1.0000 9.000 0.9291 0.01823 0.01322 0.0092 0.0091 1.0000 9.250 0.9496 0.01884 0.01392 0.0103 0.0089 1.0000 9.500 0.9698 0.01946 0.01462 0.0114 0.0085 1.0000 9.750 0.9869 0.02055 0.01585 0.0129 0.0083 1.0000 10.000 1.0040 0.02160 0.01702 0.0143 0.0081 1.0000 10.250 1.0198 0.02277 0.01833 0.0158 0.0079 1.0000 10.500 1.0339 0.02409 0.01981 0.0175 0.0077 1.0000 10.750 1.0474 0.02532 0.02119 0.0191 0.0075 1.0000 11.000 1.0569 0.02695 0.02300 0.0212 0.0074 1.0000 11.250 1.0703 0.02780 0.02393 0.0227 0.0072 1.0000 11.500 1.0744 0.02963 0.02595 0.0252 0.0071 1.0000 11.750 1.0748 0.03105 0.02750 0.0284 0.0070 1.0000 12.000 1.0708 0.03280 0.02940 0.0316 0.0070 1.0000 12.250 1.0713 0.03423 0.03092 0.0337 0.0068 1.0000 12.500 1.0644 0.03659 0.03343 0.0354 0.0068 1.0000 12.750 1.0571 0.03927 0.03626 0.0362 0.0067 1.0000 13.000 1.0400 0.04352 0.04071 0.0358 0.0067 1.0000 13.250 1.0176 0.04926 0.04671 0.0337 0.0068 1.0000 13.500 1.0039 0.05438 0.05196 0.0307 0.0067 1.0000 13.750 0.9863 0.06079 0.05851 0.0265 0.0066 1.0000