XFOIL Version 6.96 Calculated polar for: USA 48 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 ------ -------- --------- --------- -------- -------- -------- -17.500 -0.7256 0.11619 0.11319 -0.0476 1.0000 0.0096 -17.250 -0.7557 0.10656 0.10344 -0.0522 1.0000 0.0095 -17.000 -0.7831 0.09784 0.09459 -0.0564 1.0000 0.0095 -16.750 -0.8059 0.09027 0.08689 -0.0602 1.0000 0.0095 -16.500 -0.8252 0.08366 0.08018 -0.0634 1.0000 0.0095 -16.250 -0.8464 0.07694 0.07333 -0.0666 1.0000 0.0096 -16.000 -0.8655 0.07084 0.06711 -0.0695 1.0000 0.0095 -15.750 -0.8841 0.06502 0.06118 -0.0722 1.0000 0.0095 -15.500 -0.8979 0.06000 0.05604 -0.0744 1.0000 0.0096 -15.250 -0.9146 0.05472 0.05064 -0.0767 1.0000 0.0096 -15.000 -0.9271 0.05013 0.04593 -0.0786 1.0000 0.0097 -14.750 -0.9398 0.04580 0.04149 -0.0801 1.0000 0.0098 -14.500 -0.9514 0.04210 0.03768 -0.0809 1.0000 0.0098 -14.250 -0.9623 0.03899 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0.000 0.3295 0.00928 0.00199 -0.0716 0.5303 0.3886 0.250 0.3524 0.00927 0.00200 -0.0706 0.5183 0.4130 0.500 0.3747 0.00918 0.00201 -0.0695 0.5078 0.4526 0.750 0.3950 0.00901 0.00202 -0.0681 0.4980 0.5139 1.000 0.4136 0.00885 0.00220 -0.0662 0.4884 0.6242 1.250 0.4371 0.00895 0.00229 -0.0652 0.4776 0.6474 1.500 0.4603 0.00907 0.00237 -0.0642 0.4645 0.6604 1.750 0.4842 0.00918 0.00244 -0.0634 0.4536 0.6709 2.000 0.5069 0.00932 0.00252 -0.0624 0.4382 0.6790 2.250 0.5302 0.00945 0.00260 -0.0614 0.4240 0.6848 2.500 0.5511 0.00962 0.00270 -0.0601 0.4044 0.6913 2.750 0.5720 0.00981 0.00280 -0.0587 0.3861 0.6987 3.000 0.5917 0.01000 0.00293 -0.0570 0.3647 0.7046 3.250 0.6119 0.01020 0.00306 -0.0555 0.3475 0.7114 3.500 0.6317 0.01043 0.00320 -0.0540 0.3285 0.7162 3.750 0.6505 0.01069 0.00339 -0.0523 0.3081 0.7206 4.000 0.6707 0.01090 0.00355 -0.0508 0.2938 0.7273 4.250 0.6910 0.01110 0.00373 -0.0494 0.2800 0.7337 4.500 0.7108 0.01131 0.00392 -0.0479 0.2661 0.7403 4.750 0.7305 0.01157 0.00412 -0.0464 0.2506 0.7446 5.000 0.7493 0.01184 0.00434 -0.0448 0.2333 0.7504 5.250 0.7671 0.01215 0.00460 -0.0430 0.2144 0.7557 5.500 0.7801 0.01268 0.00496 -0.0404 0.1743 0.7608 5.750 0.7914 0.01329 0.00539 -0.0376 0.1391 0.7658 6.000 0.8099 0.01355 0.00566 -0.0360 0.1338 0.7718 6.250 0.8285 0.01381 0.00595 -0.0344 0.1294 0.7781 6.500 0.8483 0.01400 0.00620 -0.0330 0.1282 0.7843 6.750 0.8677 0.01421 0.00647 -0.0316 0.1273 0.7916 7.000 0.8861 0.01443 0.00677 -0.0300 0.1256 0.8011 7.250 0.9028 0.01467 0.00710 -0.0282 0.1229 0.8181 7.500 0.9317 0.01483 0.00753 -0.0289 0.1208 0.8838 7.750 1.0058 0.01546 0.00825 -0.0398 0.1173 0.9586 8.000 1.0298 0.01596 0.00875 -0.0398 0.1141 1.0000 8.250 1.0490 0.01624 0.00907 -0.0385 0.1124 1.0000 8.500 1.0672 0.01658 0.00945 -0.0371 0.1103 1.0000 8.750 1.0844 0.01697 0.00987 -0.0356 0.1081 1.0000 9.000 1.1009 0.01740 0.01034 -0.0340 0.1056 1.0000 9.250 1.1161 0.01792 0.01086 -0.0323 0.1026 1.0000 9.500 1.1312 0.01845 0.01141 -0.0307 0.0989 1.0000 9.750 1.1509 0.01876 0.01178 -0.0297 0.0950 1.0000 10.000 1.1668 0.01928 0.01230 -0.0283 0.0870 1.0000 10.250 1.1677 0.02064 0.01338 -0.0251 0.0479 1.0000 10.500 1.1747 0.02172 0.01447 -0.0227 0.0392 1.0000 10.750 1.1854 0.02263 0.01541 -0.0210 0.0347 1.0000 11.000 1.1949 0.02365 0.01645 -0.0192 0.0306 1.0000 11.250 1.2058 0.02462 0.01746 -0.0176 0.0278 1.0000 11.500 1.2146 0.02577 0.01865 -0.0160 0.0251 1.0000 11.750 1.2254 0.02682 0.01975 -0.0147 0.0230 1.0000 12.000 1.2335 0.02811 0.02107 -0.0133 0.0206 1.0000 12.250 1.2423 0.02940 0.02241 -0.0120 0.0189 1.0000 12.500 1.2506 0.03078 0.02384 -0.0109 0.0176 1.0000 12.750 1.2576 0.03232 0.02543 -0.0098 0.0165 1.0000 13.000 1.2632 0.03402 0.02718 -0.0088 0.0156 1.0000 13.250 1.2701 0.03568 0.02892 -0.0079 0.0148 1.0000 13.500 1.2758 0.03749 0.03081 -0.0072 0.0142 1.0000 13.750 1.2805 0.03944 0.03283 -0.0065 0.0136 1.0000 14.000 1.2837 0.04159 0.03504 -0.0059 0.0129 1.0000 14.250 1.2849 0.04401 0.03754 -0.0054 0.0124 1.0000 14.500 1.2858 0.04655 0.04016 -0.0050 0.0120 1.0000 14.750 1.2882 0.04897 0.04268 -0.0047 0.0117 1.0000 15.000 1.2895 0.05159 0.04539 -0.0046 0.0113 1.0000 15.250 1.2899 0.05436 0.04826 -0.0046 0.0110 1.0000 15.500 1.2904 0.05720 0.05118 -0.0048 0.0105 1.0000 15.750 1.2882 0.06041 0.05448 -0.0050 0.0104 1.0000 16.000 1.2857 0.06372 0.05788 -0.0054 0.0099 1.0000 16.250 1.2816 0.06730 0.06155 -0.0059 0.0098 1.0000 16.500 1.2754 0.07126 0.06560 -0.0066 0.0096 1.0000 16.750 1.2684 0.07537 0.06981 -0.0074 0.0095 1.0000 17.000 1.2591 0.07987 0.07441 -0.0084 0.0092 1.0000 17.250 1.2536 0.08393 0.07858 -0.0094 0.0091 1.0000 17.500 1.2477 0.08812 0.08288 -0.0105 0.0090 1.0000 17.750 1.2414 0.09241 0.08727 -0.0117 0.0088 1.0000 18.000 1.2336 0.09697 0.09194 -0.0131 0.0087 1.0000 18.250 1.2270 0.10141 0.09648 -0.0145 0.0085 1.0000 18.500 1.2189 0.10616 0.10132 -0.0161 0.0084 1.0000 18.750 1.2128 0.11064 0.10590 -0.0177 0.0082 1.0000 19.000 1.2046 0.11547 0.11082 -0.0195 0.0081 1.0000 19.250 1.1970 0.12025 0.11569 -0.0214 0.0080 1.0000