XFOIL Version 6.96 Calculated polar for: AS5048 (18%) 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 ------ -------- --------- --------- -------- -------- -------- -17.250 -0.7776 0.11328 0.11022 -0.0381 1.0000 0.0069 -17.000 -0.8228 0.09972 0.09637 -0.0453 1.0000 0.0068 -16.750 -0.8502 0.09074 0.08718 -0.0498 1.0000 0.0068 -16.500 -0.8708 0.08349 0.07974 -0.0531 1.0000 0.0068 -16.250 -0.8873 0.07736 0.07342 -0.0555 1.0000 0.0068 -16.000 -0.9000 0.07217 0.06807 -0.0572 1.0000 0.0069 -15.750 -0.9098 0.06764 0.06338 -0.0585 1.0000 0.0069 -15.500 -0.9180 0.06356 0.05915 -0.0593 1.0000 0.0070 -15.250 -0.9234 0.06004 0.05550 -0.0597 1.0000 0.0071 -15.000 -0.9257 0.05654 0.05183 -0.0605 0.9996 0.0072 -14.750 -0.9203 0.05306 0.04819 -0.0624 0.9957 0.0073 -14.500 -0.9159 0.05009 0.04506 -0.0632 0.9389 0.0074 -14.250 -0.8671 0.04542 0.04001 -0.0755 0.9066 0.0077 -14.000 -0.8386 0.04275 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0.5653 -3.750 -0.1742 0.00915 0.00331 -0.0498 0.6844 0.5879 -3.500 -0.1447 0.00923 0.00336 -0.0502 0.6829 0.6007 -3.250 -0.1155 0.00929 0.00342 -0.0505 0.6816 0.6105 -3.000 -0.0861 0.00936 0.00343 -0.0509 0.6801 0.6198 -2.750 -0.0569 0.00941 0.00350 -0.0512 0.6783 0.6248 -2.500 -0.0274 0.00944 0.00350 -0.0516 0.6765 0.6286 -2.250 0.0021 0.00946 0.00348 -0.0520 0.6746 0.6321 -2.000 0.0316 0.00948 0.00343 -0.0525 0.6727 0.6352 -1.750 0.0611 0.00948 0.00341 -0.0529 0.6708 0.6376 -1.500 0.0905 0.00950 0.00341 -0.0533 0.6690 0.6399 -1.250 0.1200 0.00954 0.00343 -0.0537 0.6671 0.6425 -1.000 0.1494 0.00957 0.00344 -0.0542 0.6649 0.6448 -0.750 0.1783 0.00955 0.00343 -0.0545 0.6618 0.6469 -0.500 0.2071 0.00952 0.00338 -0.0548 0.6580 0.6487 -0.250 0.2361 0.00950 0.00333 -0.0551 0.6544 0.6504 0.000 0.2654 0.00949 0.00328 -0.0555 0.6515 0.6521 0.250 0.2947 0.00950 0.00326 -0.0559 0.6488 0.6536 0.500 0.3234 0.00947 0.00327 -0.0562 0.6455 0.6548 0.750 0.3521 0.00944 0.00328 -0.0565 0.6417 0.6561 1.000 0.3809 0.00943 0.00327 -0.0568 0.6378 0.6576 1.250 0.4096 0.00942 0.00326 -0.0570 0.6341 0.6590 1.500 0.4381 0.00941 0.00326 -0.0573 0.6290 0.6603 1.750 0.4660 0.00936 0.00323 -0.0573 0.6204 0.6617 2.000 0.4938 0.00933 0.00320 -0.0574 0.6115 0.6632 2.250 0.5218 0.00933 0.00319 -0.0575 0.6029 0.6649 2.500 0.5500 0.00934 0.00320 -0.0577 0.5946 0.6664 2.750 0.5776 0.00935 0.00320 -0.0577 0.5852 0.6678 3.000 0.6051 0.00938 0.00321 -0.0578 0.5721 0.6690 3.250 0.6314 0.00945 0.00322 -0.0576 0.5549 0.6702 3.500 0.6567 0.00954 0.00326 -0.0571 0.5351 0.6715 3.750 0.6812 0.00969 0.00335 -0.0566 0.5120 0.6729 4.000 0.7042 0.00993 0.00349 -0.0558 0.4853 0.6743 4.250 0.7264 0.01024 0.00368 -0.0548 0.4557 0.6756 4.500 0.7487 0.01054 0.00389 -0.0540 0.4279 0.6769 4.750 0.7709 0.01087 0.00412 -0.0531 0.4030 0.6783 5.000 0.7927 0.01120 0.00437 -0.0521 0.3771 0.6797 5.250 0.8137 0.01157 0.00463 -0.0511 0.3518 0.6811 5.500 0.8344 0.01196 0.00491 -0.0500 0.3260 0.6827 5.750 0.8549 0.01235 0.00520 -0.0489 0.3026 0.6844 6.000 0.8759 0.01270 0.00548 -0.0479 0.2824 0.6859 6.250 0.8962 0.01308 0.00578 -0.0467 0.2624 0.6871 6.500 0.9160 0.01343 0.00609 -0.0455 0.2448 0.6884 6.750 0.9356 0.01379 0.00641 -0.0443 0.2292 0.6898 7.000 0.9543 0.01417 0.00675 -0.0429 0.2138 0.6912 7.250 0.9708 0.01455 0.00709 -0.0410 0.1998 0.6926 7.500 0.9866 0.01494 0.00745 -0.0391 0.1882 0.6941 7.750 1.0034 0.01535 0.00784 -0.0374 0.1779 0.6956 8.000 1.0221 0.01574 0.00824 -0.0361 0.1694 0.6973 8.250 1.0393 0.01622 0.00870 -0.0347 0.1609 0.6991 8.500 1.0580 0.01664 0.00914 -0.0335 0.1535 0.7010 8.750 1.0744 0.01718 0.00965 -0.0320 0.1459 0.7027 9.250 1.1074 0.01824 0.01074 -0.0292 0.1317 0.7057 9.500 1.1246 0.01875 0.01131 -0.0281 0.1255 0.7073 9.750 1.1391 0.01944 0.01199 -0.0266 0.1185 0.7090 10.000 1.1549 0.02008 0.01268 -0.0255 0.1119 0.7108 10.250 1.1681 0.02092 0.01351 -0.0241 0.1046 0.7127 10.500 1.1829 0.02171 0.01434 -0.0231 0.0981 0.7146 10.750 1.1955 0.02270 0.01533 -0.0220 0.0917 0.7166 11.000 1.2094 0.02366 0.01631 -0.0212 0.0857 0.7185 11.250 1.2214 0.02480 0.01745 -0.0202 0.0802 0.7204 11.500 1.2350 0.02584 0.01854 -0.0195 0.0755 0.7225 11.750 1.2462 0.02707 0.01980 -0.0187 0.0707 0.7247 12.000 1.2591 0.02819 0.02098 -0.0180 0.0669 0.7272 12.250 1.2704 0.02944 0.02227 -0.0173 0.0628 0.7298 12.500 1.2808 0.03077 0.02364 -0.0165 0.0593 0.7323 12.750 1.2921 0.03203 0.02495 -0.0158 0.0561 0.7348 13.000 1.3012 0.03347 0.02641 -0.0150 0.0529 0.7373 13.250 1.3107 0.03488 0.02789 -0.0143 0.0504 0.7399 13.500 1.3203 0.03630 0.02938 -0.0136 0.0480 0.7429 13.750 1.3283 0.03784 0.03098 -0.0129 0.0457 0.7462 14.000 1.3347 0.03954 0.03274 -0.0121 0.0437 0.7497 14.250 1.3433 0.04108 0.03436 -0.0115 0.0420 0.7534 14.500 1.3504 0.04278 0.03615 -0.0109 0.0402 0.7574 14.750 1.3561 0.04462 0.03807 -0.0103 0.0386 0.7624 15.000 1.3601 0.04667 0.04019 -0.0098 0.0371 0.7681 15.250 1.3669 0.04853 0.04217 -0.0094 0.0360 0.7752 15.500 1.3729 0.05051 0.04428 -0.0092 0.0347 0.7850 15.750 1.3772 0.05271 0.04661 -0.0089 0.0336 0.7986 16.000 1.3801 0.05500 0.04907 -0.0087 0.0325 0.8238 16.500 1.3610 0.05884 0.05331 -0.0027 0.0310 1.0000 16.750 1.3644 0.06138 0.05595 -0.0029 0.0302 1.0000 17.000 1.3666 0.06410 0.05875 -0.0031 0.0292 1.0000 17.250 1.3667 0.06710 0.06183 -0.0035 0.0283 1.0000 17.500 1.3653 0.07035 0.06515 -0.0040 0.0275 1.0000 17.750 1.3621 0.07390 0.06878 -0.0047 0.0268 1.0000 18.000 1.3576 0.07770 0.07267 -0.0055 0.0262 1.0000 18.250 1.3555 0.08125 0.07633 -0.0063 0.0256 1.0000 18.500 1.3517 0.08506 0.08025 -0.0074 0.0251 1.0000 18.750 1.3465 0.08910 0.08440 -0.0085 0.0245 1.0000 19.000 1.3401 0.09340 0.08880 -0.0099 0.0240 1.0000 19.250 1.3325 0.09794 0.09344 -0.0115 0.0235 1.0000