XFOIL Version 6.96 Calculated polar for: LOCKHEED C-5A BL0 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 ------ -------- --------- --------- -------- -------- -------- -15.500 -0.8475 0.08798 0.08488 -0.0502 1.0000 0.0111 -15.250 -0.8818 0.07755 0.07423 -0.0563 1.0000 0.0110 -15.000 -0.9083 0.06973 0.06621 -0.0603 1.0000 0.0110 -14.750 -0.9307 0.06345 0.05974 -0.0628 1.0000 0.0110 -14.500 -0.9496 0.05824 0.05434 -0.0643 1.0000 0.0110 -14.250 -0.9658 0.05382 0.04973 -0.0648 1.0000 0.0111 -14.000 -0.9795 0.05003 0.04576 -0.0645 1.0000 0.0111 -13.500 -1.0005 0.04389 0.03926 -0.0623 1.0000 0.0112 -13.250 -1.0083 0.04138 0.03658 -0.0605 1.0000 0.0113 -13.000 -1.0144 0.03919 0.03423 -0.0583 1.0000 0.0114 -12.750 -1.0191 0.03730 0.03219 -0.0558 1.0000 0.0115 -12.500 -1.0227 0.03564 0.03038 -0.0530 1.0000 0.0116 -12.250 -1.0258 0.03416 0.02876 -0.0499 1.0000 0.0117 -12.000 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0.9252 0.5658 -2.500 -0.1624 0.00745 0.00257 -0.0387 0.9228 0.5972 -2.250 -0.1311 0.00734 0.00247 -0.0395 0.9199 0.6117 -2.000 -0.1059 0.00726 0.00241 -0.0389 0.9129 0.6220 -1.750 -0.0747 0.00715 0.00230 -0.0396 0.9083 0.6335 -1.500 -0.0432 0.00708 0.00222 -0.0404 0.9045 0.6446 -1.250 -0.0170 0.00703 0.00221 -0.0401 0.8983 0.6552 -1.000 0.0135 0.00695 0.00215 -0.0406 0.8934 0.6660 -0.750 0.0434 0.00690 0.00209 -0.0411 0.8873 0.6759 -0.500 0.0725 0.00683 0.00205 -0.0413 0.8790 0.6839 -0.250 0.1021 0.00678 0.00198 -0.0416 0.8679 0.6915 0.000 0.1321 0.00672 0.00191 -0.0420 0.8537 0.6974 0.250 0.1619 0.00669 0.00185 -0.0423 0.8362 0.7037 0.500 0.1913 0.00670 0.00177 -0.0426 0.8125 0.7096 0.750 0.2185 0.00676 0.00175 -0.0423 0.7822 0.7153 1.000 0.2431 0.00692 0.00173 -0.0414 0.7360 0.7215 1.250 0.2648 0.00718 0.00176 -0.0400 0.6778 0.7278 1.500 0.2857 0.00748 0.00184 -0.0385 0.6228 0.7350 1.750 0.3080 0.00776 0.00195 -0.0374 0.5759 0.7422 2.000 0.3300 0.00806 0.00207 -0.0362 0.5269 0.7491 2.250 0.3515 0.00844 0.00221 -0.0350 0.4594 0.7554 2.500 0.3702 0.00904 0.00243 -0.0334 0.3649 0.7609 2.750 0.3909 0.00960 0.00265 -0.0323 0.2811 0.7671 3.000 0.4141 0.01002 0.00285 -0.0316 0.2265 0.7731 3.250 0.4371 0.01042 0.00308 -0.0308 0.1773 0.7788 3.500 0.4613 0.01075 0.00328 -0.0303 0.1437 0.7852 3.750 0.4863 0.01101 0.00347 -0.0298 0.1265 0.7911 4.000 0.5117 0.01120 0.00367 -0.0294 0.1139 0.7971 4.250 0.5366 0.01148 0.00387 -0.0290 0.0928 0.8036 4.500 0.5609 0.01177 0.00410 -0.0284 0.0743 0.8094 4.750 0.5852 0.01206 0.00436 -0.0279 0.0614 0.8159 5.000 0.6101 0.01233 0.00460 -0.0274 0.0560 0.8222 5.250 0.6344 0.01258 0.00488 -0.0268 0.0524 0.8283 5.500 0.6588 0.01288 0.00518 -0.0263 0.0495 0.8351 5.750 0.6833 0.01312 0.00548 -0.0257 0.0484 0.8412 6.000 0.7075 0.01337 0.00579 -0.0251 0.0473 0.8479 6.250 0.7317 0.01365 0.00612 -0.0245 0.0460 0.8546 6.500 0.7549 0.01394 0.00647 -0.0237 0.0446 0.8613 6.750 0.7781 0.01427 0.00684 -0.0230 0.0432 0.8685 7.000 0.7999 0.01466 0.00726 -0.0219 0.0415 0.8753 7.250 0.8208 0.01513 0.00779 -0.0208 0.0398 0.8828 7.500 0.8437 0.01539 0.00812 -0.0199 0.0391 0.8899 7.750 0.8660 0.01569 0.00849 -0.0190 0.0381 0.8980 8.000 0.8875 0.01600 0.00888 -0.0179 0.0369 0.9062 8.250 0.9089 0.01632 0.00926 -0.0168 0.0356 0.9154 8.500 0.9291 0.01665 0.00965 -0.0155 0.0345 0.9253 8.750 0.9481 0.01706 0.01011 -0.0140 0.0334 0.9375 9.000 0.9653 0.01759 0.01070 -0.0122 0.0322 0.9539 9.500 1.0146 0.01824 0.01151 -0.0117 0.0301 1.0000 9.750 1.0359 0.01862 0.01192 -0.0109 0.0288 1.0000 10.000 1.0567 0.01902 0.01235 -0.0099 0.0277 1.0000 10.250 1.0762 0.01952 0.01286 -0.0088 0.0266 1.0000 10.500 1.0957 0.02002 0.01343 -0.0077 0.0256 1.0000 10.750 1.1157 0.02047 0.01394 -0.0067 0.0243 1.0000 11.000 1.1357 0.02089 0.01440 -0.0058 0.0230 1.0000 11.250 1.1549 0.02138 0.01489 -0.0047 0.0218 1.0000 11.500 1.1725 0.02199 0.01557 -0.0035 0.0208 1.0000 11.750 1.1899 0.02260 0.01626 -0.0022 0.0198 1.0000 12.000 1.2072 0.02321 0.01692 -0.0009 0.0187 1.0000 12.250 1.2235 0.02388 0.01762 0.0004 0.0178 1.0000 12.500 1.2381 0.02468 0.01849 0.0019 0.0171 1.0000 12.750 1.2524 0.02550 0.01940 0.0034 0.0163 1.0000 13.000 1.2661 0.02636 0.02035 0.0049 0.0156 1.0000 13.250 1.2789 0.02728 0.02135 0.0064 0.0150 1.0000 13.500 1.2905 0.02830 0.02244 0.0080 0.0145 1.0000 13.750 1.2997 0.02950 0.02371 0.0098 0.0139 1.0000 14.000 1.3094 0.03069 0.02502 0.0113 0.0136 1.0000 14.250 1.3180 0.03198 0.02643 0.0129 0.0131 1.0000 14.500 1.3255 0.03338 0.02795 0.0144 0.0127 1.0000 14.750 1.3321 0.03490 0.02957 0.0159 0.0123 1.0000 15.000 1.3373 0.03656 0.03136 0.0172 0.0120 1.0000 15.250 1.3408 0.03844 0.03334 0.0184 0.0116 1.0000 15.500 1.3418 0.04063 0.03563 0.0195 0.0113 1.0000 15.750 1.3398 0.04321 0.03832 0.0203 0.0110 1.0000 16.000 1.3393 0.04577 0.04104 0.0208 0.0108 1.0000 16.250 1.3373 0.04865 0.04407 0.0210 0.0106 1.0000 16.500 1.3332 0.05192 0.04750 0.0209 0.0104 1.0000 16.750 1.3266 0.05571 0.05144 0.0202 0.0102 1.0000 17.000 1.3177 0.06011 0.05599 0.0189 0.0100 1.0000 17.250 1.3063 0.06515 0.06120 0.0170 0.0099 1.0000 17.500 1.2907 0.07115 0.06737 0.0143 0.0097 1.0000 17.750 1.2705 0.07833 0.07474 0.0106 0.0097 1.0000 18.000 1.2427 0.08743 0.08404 0.0055 0.0097 1.0000 18.250 1.2039 0.09914 0.09597 -0.0011 0.0098 1.0000 18.500 1.1510 0.11418 0.11125 -0.0094 0.0101 1.0000