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 = 1.000 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -19.250 -0.7265 0.14430 0.14209 -0.0340 1.0000 0.0067 -19.000 -0.7802 0.12915 0.12679 -0.0414 1.0000 0.0066 -18.750 -0.8229 0.11700 0.11449 -0.0473 1.0000 0.0065 -18.500 -0.8597 0.10651 0.10385 -0.0525 1.0000 0.0065 -18.250 -0.8915 0.09745 0.09467 -0.0571 1.0000 0.0064 -18.000 -0.9198 0.08928 0.08637 -0.0612 1.0000 0.0065 -17.750 -0.9432 0.08222 0.07921 -0.0647 1.0000 0.0065 -17.500 -0.9699 0.07489 0.07175 -0.0683 1.0000 0.0065 -17.250 -0.9921 0.06843 0.06518 -0.0714 1.0000 0.0065 -17.000 -1.0166 0.06187 0.05849 -0.0745 1.0000 0.0065 -16.750 -1.0332 0.05655 0.05306 -0.0770 1.0000 0.0065 -16.500 -1.0475 0.05158 0.04798 -0.0792 1.0000 0.0065 -16.250 -1.0631 0.04655 0.04282 -0.0814 1.0000 0.0066 -16.000 -1.0735 0.04254 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3.500 0.6163 0.01048 0.00325 -0.0517 0.1233 0.6719 3.750 0.6380 0.01064 0.00340 -0.0505 0.1198 0.6781 4.000 0.6603 0.01080 0.00355 -0.0494 0.1173 0.6836 4.250 0.6821 0.01094 0.00370 -0.0483 0.1152 0.6882 4.500 0.7043 0.01108 0.00385 -0.0472 0.1140 0.6923 4.750 0.7267 0.01122 0.00401 -0.0462 0.1136 0.6954 5.250 0.7707 0.01151 0.00434 -0.0440 0.1128 0.7042 5.500 0.7923 0.01166 0.00451 -0.0429 0.1124 0.7081 5.750 0.8137 0.01183 0.00470 -0.0417 0.1120 0.7130 6.000 0.8352 0.01201 0.00489 -0.0406 0.1115 0.7147 6.250 0.8558 0.01216 0.00510 -0.0393 0.1109 0.7217 6.500 0.8762 0.01234 0.00531 -0.0380 0.1097 0.7261 6.750 0.8967 0.01254 0.00552 -0.0367 0.1088 0.7298 7.000 0.9168 0.01274 0.00576 -0.0354 0.1081 0.7331 7.250 0.9368 0.01294 0.00599 -0.0341 0.1075 0.7365 7.500 0.9551 0.01321 0.00626 -0.0325 0.1047 0.7392 7.750 0.9734 0.01348 0.00656 -0.0310 0.1022 0.7418 8.000 0.9916 0.01377 0.00687 -0.0294 0.1000 0.7446 8.250 1.0115 0.01398 0.00712 -0.0282 0.0991 0.7475 8.500 1.0314 0.01417 0.00736 -0.0269 0.0983 0.7512 8.750 1.0508 0.01438 0.00761 -0.0257 0.0970 0.7557 9.000 1.0698 0.01461 0.00789 -0.0243 0.0942 0.7610 9.250 1.0864 0.01492 0.00821 -0.0226 0.0895 0.7680 9.500 1.0984 0.01541 0.00863 -0.0203 0.0677 0.7785 9.750 1.0958 0.01643 0.00959 -0.0157 0.0411 0.8040 10.000 1.1432 0.01704 0.01055 -0.0214 0.0323 0.9345 10.250 1.2103 0.01810 0.01161 -0.0314 0.0254 0.9992 10.500 1.2264 0.01873 0.01225 -0.0301 0.0227 1.0000 10.750 1.2392 0.01946 0.01298 -0.0284 0.0198 1.0000 11.000 1.2530 0.02015 0.01369 -0.0269 0.0178 1.0000 11.250 1.2652 0.02095 0.01451 -0.0252 0.0159 1.0000 11.500 1.2783 0.02173 0.01532 -0.0238 0.0149 1.0000 11.750 1.2907 0.02258 0.01619 -0.0223 0.0138 1.0000 12.000 1.3015 0.02356 0.01719 -0.0208 0.0126 1.0000 12.250 1.3127 0.02455 0.01823 -0.0194 0.0119 1.0000 12.500 1.3241 0.02557 0.01929 -0.0182 0.0114 1.0000 12.750 1.3345 0.02668 0.02044 -0.0169 0.0107 1.0000 13.000 1.3436 0.02792 0.02172 -0.0157 0.0101 1.0000 13.250 1.3514 0.02933 0.02317 -0.0145 0.0094 1.0000 13.500 1.3597 0.03074 0.02464 -0.0135 0.0092 1.0000 13.750 1.3681 0.03219 0.02615 -0.0125 0.0089 1.0000 14.000 1.3761 0.03371 0.02773 -0.0117 0.0085 1.0000 14.250 1.3833 0.03535 0.02942 -0.0110 0.0080 1.0000 14.500 1.3893 0.03716 0.03129 -0.0102 0.0079 1.0000 14.750 1.3942 0.03909 0.03326 -0.0096 0.0075 1.0000 15.000 1.3978 0.04120 0.03545 -0.0090 0.0073 1.0000 15.250 1.3997 0.04355 0.03786 -0.0085 0.0070 1.0000 15.500 1.4026 0.04585 0.04023 -0.0082 0.0069 1.0000 15.750 1.4052 0.04824 0.04270 -0.0080 0.0068 1.0000 16.000 1.4069 0.05078 0.04532 -0.0078 0.0065 1.0000 16.250 1.4073 0.05352 0.04813 -0.0078 0.0065 1.0000 16.500 1.4078 0.05632 0.05101 -0.0079 0.0063 1.0000 16.750 1.4059 0.05946 0.05424 -0.0081 0.0063 1.0000 17.000 1.4045 0.06257 0.05742 -0.0084 0.0060 1.0000 17.250 1.4014 0.06595 0.06089 -0.0088 0.0060 1.0000 17.500 1.3981 0.06943 0.06445 -0.0094 0.0058 1.0000 17.750 1.3935 0.07313 0.06823 -0.0100 0.0057 1.0000 18.000 1.3874 0.07707 0.07226 -0.0108 0.0056 1.0000 18.250 1.3800 0.08124 0.07652 -0.0117 0.0055 1.0000 18.500 1.3723 0.08555 0.08092 -0.0128 0.0054 1.0000 18.750 1.3635 0.09008 0.08554 -0.0140 0.0053 1.0000 19.000 1.3546 0.09468 0.09023 -0.0154 0.0053 1.0000 19.250 1.3439 0.09959 0.09524 -0.0169 0.0053 1.0000