XFOIL Version 6.96 Calculated polar for: AH 79-K-143/18 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 ------ -------- --------- --------- -------- -------- -------- -13.500 -0.3825 0.06168 0.05908 -0.0950 0.7886 0.0091 -13.250 -0.4003 0.05295 0.05028 -0.0994 0.7884 0.0091 -13.000 -0.5558 0.05132 0.04838 -0.1111 0.7900 0.0086 -12.750 -0.5600 0.04715 0.04409 -0.1148 0.7893 0.0086 -12.500 -0.6046 0.03944 0.03603 -0.1171 0.7883 0.0085 -12.250 -0.6362 0.03428 0.03051 -0.1156 0.7874 0.0082 -12.000 -0.6188 0.03394 0.03014 -0.1154 0.7867 0.0085 -11.750 -0.6320 0.03093 0.02688 -0.1124 0.7860 0.0085 -11.500 -0.6297 0.02932 0.02513 -0.1101 0.7850 0.0085 -11.250 -0.6428 0.02613 0.02159 -0.1057 0.7837 0.0084 -11.000 -0.6331 0.02520 0.02054 -0.1036 0.7825 0.0086 -10.750 -0.6264 0.02393 0.01911 -0.1009 0.7814 0.0087 -10.500 -0.6191 0.02275 0.01776 -0.0980 0.7802 0.0088 -10.250 -0.6096 0.02163 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0.01154 0.00530 -0.0747 0.7606 0.0242 -5.250 -0.1975 0.01128 0.00502 -0.0742 0.7597 0.0263 -5.000 -0.1731 0.01107 0.00480 -0.0737 0.7587 0.0289 -4.750 -0.1487 0.01089 0.00462 -0.0732 0.7574 0.0326 -4.500 -0.1247 0.01065 0.00443 -0.0726 0.7561 0.0399 -4.250 -0.1014 0.01038 0.00425 -0.0719 0.7546 0.0555 -4.000 -0.0771 0.01016 0.00410 -0.0714 0.7531 0.0719 -3.750 -0.0527 0.00991 0.00394 -0.0709 0.7517 0.0921 -3.500 -0.0278 0.00968 0.00378 -0.0705 0.7502 0.1138 -3.250 -0.0031 0.00942 0.00362 -0.0701 0.7490 0.1419 -3.000 0.0213 0.00910 0.00344 -0.0696 0.7477 0.1825 -2.750 0.0447 0.00871 0.00324 -0.0690 0.7464 0.2446 -2.500 0.0663 0.00819 0.00302 -0.0681 0.7449 0.3352 -2.250 0.0836 0.00755 0.00283 -0.0664 0.7430 0.4727 -2.000 0.0956 0.00675 0.00266 -0.0635 0.7407 0.6444 -1.750 0.1130 0.00631 0.00263 -0.0613 0.7386 0.7548 -1.500 0.1382 0.00628 0.00273 -0.0606 0.7366 0.8056 -1.250 0.1660 0.00631 0.00277 -0.0605 0.7348 0.8222 -1.000 0.1942 0.00634 0.00276 -0.0605 0.7331 0.8345 -0.750 0.2229 0.00643 0.00283 -0.0605 0.7315 0.8427 -0.500 0.2511 0.00646 0.00281 -0.0606 0.7297 0.8494 -0.250 0.2788 0.00656 0.00292 -0.0605 0.7273 0.8537 0.000 0.3062 0.00670 0.00309 -0.0603 0.7247 0.8596 0.250 0.3333 0.00685 0.00323 -0.0600 0.7221 0.8670 0.500 0.3608 0.00704 0.00344 -0.0595 0.7196 0.8719 0.750 0.3883 0.00715 0.00354 -0.0593 0.7172 0.8774 1.000 0.4164 0.00720 0.00354 -0.0594 0.7146 0.8812 1.250 0.4425 0.00715 0.00353 -0.0591 0.7109 0.8826 1.500 0.4695 0.00712 0.00351 -0.0590 0.7072 0.8840 1.750 0.4968 0.00710 0.00347 -0.0588 0.7035 0.8857 2.000 0.5240 0.00710 0.00346 -0.0588 0.6999 0.8875 2.250 0.5505 0.00710 0.00349 -0.0586 0.6947 0.8895 2.500 0.5776 0.00708 0.00346 -0.0586 0.6896 0.8915 2.750 0.6047 0.00709 0.00345 -0.0586 0.6841 0.8936 3.000 0.6322 0.00711 0.00348 -0.0587 0.6777 0.8953 3.250 0.6577 0.00705 0.00340 -0.0584 0.6715 0.8966 3.500 0.6833 0.00703 0.00341 -0.0580 0.6636 0.8978 3.750 0.7085 0.00704 0.00341 -0.0576 0.6560 0.8989 4.000 0.7338 0.00706 0.00344 -0.0572 0.6462 0.9000 4.250 0.7575 0.00712 0.00346 -0.0564 0.6317 0.9012 4.500 0.7791 0.00724 0.00350 -0.0553 0.6118 0.9025 5.000 0.8247 0.00747 0.00368 -0.0536 0.5810 0.9056 5.250 0.8464 0.00763 0.00380 -0.0526 0.5630 0.9073 5.500 0.8613 0.00800 0.00401 -0.0502 0.5250 0.9092 5.750 0.8740 0.00832 0.00419 -0.0475 0.4886 0.9109 6.000 0.8849 0.00866 0.00439 -0.0443 0.4527 0.9123 6.250 0.8969 0.00899 0.00461 -0.0415 0.4241 0.9137 6.500 0.9009 0.00949 0.00492 -0.0371 0.3814 0.9156 6.750 0.9042 0.00985 0.00517 -0.0325 0.3514 0.9179 7.000 0.8998 0.01043 0.00558 -0.0266 0.3116 0.9212 7.250 0.8941 0.01118 0.00613 -0.0208 0.2723 0.9234 7.500 0.8851 0.01208 0.00684 -0.0149 0.2293 0.9258 7.750 0.8795 0.01319 0.00778 -0.0104 0.1904 0.9282 8.000 0.8785 0.01424 0.00864 -0.0066 0.1525 0.9303 8.250 0.8763 0.01545 0.00960 -0.0029 0.1042 0.9324 8.500 0.8784 0.01660 0.01054 0.0001 0.0659 0.9342 8.750 0.8869 0.01752 0.01134 0.0021 0.0444 0.9358 9.000 0.8986 0.01834 0.01209 0.0036 0.0324 0.9369 9.250 0.9117 0.01915 0.01287 0.0048 0.0231 0.9377 9.500 0.9292 0.01989 0.01359 0.0052 0.0195 0.9387 9.750 0.9471 0.02064 0.01435 0.0055 0.0162 0.9396 10.000 0.9641 0.02147 0.01521 0.0058 0.0151 0.9405 10.250 0.9814 0.02231 0.01609 0.0061 0.0141 0.9413 10.500 0.9992 0.02312 0.01694 0.0063 0.0131 0.9421 10.750 1.0138 0.02417 0.01803 0.0067 0.0120 0.9430 11.000 1.0288 0.02522 0.01913 0.0070 0.0118 0.9438 11.250 1.0457 0.02615 0.02012 0.0071 0.0118 0.9446 11.500 1.0544 0.02771 0.02176 0.0079 0.0110 0.9455 11.750 1.0700 0.02876 0.02286 0.0080 0.0107 0.9462 12.000 1.0816 0.03016 0.02433 0.0084 0.0107 0.9470 12.250 1.0939 0.03156 0.02580 0.0086 0.0106 0.9478 12.500 1.1088 0.03278 0.02707 0.0086 0.0100 0.9485 12.750 1.1180 0.03447 0.02885 0.0090 0.0101 0.9493 13.000 1.1312 0.03585 0.03028 0.0090 0.0098 0.9500 13.250 1.1417 0.03754 0.03204 0.0092 0.0096 0.9507 13.500 1.1563 0.03903 0.03357 0.0087 0.0091 0.9514 13.750 1.1679 0.04076 0.03537 0.0084 0.0091 0.9522 14.000 1.1746 0.04295 0.03763 0.0084 0.0089 0.9531 14.250 1.1820 0.04510 0.03986 0.0084 0.0087 0.9540 14.500 1.1810 0.04784 0.04270 0.0092 0.0085 0.9550 14.750 1.1840 0.05018 0.04514 0.0099 0.0084 0.9559 15.000 1.1946 0.05214 0.04720 0.0095 0.0083 0.9570 15.250 1.2034 0.05424 0.04939 0.0092 0.0083 0.9580 15.500 1.2110 0.05649 0.05175 0.0089 0.0082 0.9590 15.750 1.2175 0.05881 0.05416 0.0088 0.0081 0.9600 16.000 1.2213 0.06139 0.05686 0.0089 0.0081 0.9610 16.250 1.2311 0.06385 0.05941 0.0074 0.0079 0.9623 16.500 1.2317 0.06691 0.06262 0.0075 0.0079 0.9633 16.750 1.2351 0.06996 0.06580 0.0066 0.0079 0.9645 17.000 1.2395 0.07321 0.06916 0.0051 0.0077 0.9659 17.250 1.2393 0.07679 0.07289 0.0042 0.0078 0.9673 17.500 1.2404 0.08059 0.07681 0.0025 0.0076 0.9689 17.750 1.2362 0.08495 0.08133 0.0011 0.0076 0.9704 18.000 1.2338 0.08930 0.08582 -0.0008 0.0075 0.9719 18.500 1.2276 0.09875 0.09552 -0.0057 0.0072 0.9762 18.750 1.2171 0.10465 0.10160 -0.0085 0.0072 0.9787 19.000 1.2063 0.11060 0.10771 -0.0113 0.0072 0.9968 19.250 1.1976 0.11656 0.11381 -0.0149 0.0071 0.9961