XFOIL Version 6.96 Calculated polar for: SIKORSKY DBLN-526 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 = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -19.000 -1.0371 0.08624 0.08154 -0.1178 0.9790 0.0358 -18.750 -1.0482 0.08177 0.07688 -0.1186 0.9776 0.0357 -18.500 -1.0584 0.07743 0.07231 -0.1192 0.9768 0.0356 -18.250 -1.0646 0.07419 0.06893 -0.1184 0.9721 0.0362 -18.000 -1.0656 0.07113 0.06569 -0.1192 0.9700 0.0369 -17.750 -1.0655 0.06827 0.06264 -0.1199 0.9690 0.0372 -17.500 -1.0722 0.06504 0.05922 -0.1177 0.9634 0.0373 -17.250 -1.0678 0.06293 0.05697 -0.1174 0.9620 0.0374 -17.000 -1.0529 0.06127 0.05536 -0.1180 0.9612 0.0384 -16.750 -1.0413 0.05945 0.05346 -0.1183 0.9606 0.0387 -16.500 -1.0453 0.05773 0.05168 -0.1146 0.9551 0.0390 -16.250 -1.0368 0.05627 0.05015 -0.1138 0.9535 0.0395 -16.000 -1.0241 0.05478 0.04855 -0.1136 0.9525 0.0396 -15.750 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0.02561 0.01767 -0.0612 0.8671 0.0783 -6.250 -0.3873 0.02483 0.01693 -0.0617 0.8660 0.0831 -6.000 -0.3598 0.02415 0.01630 -0.0622 0.8651 0.0917 -5.500 -0.3017 0.02272 0.01513 -0.0639 0.8638 0.1355 -5.250 -0.2729 0.02208 0.01460 -0.0647 0.8633 0.1620 -5.000 -0.2422 0.02143 0.01416 -0.0660 0.8628 0.1978 -4.750 -0.2398 0.02182 0.01460 -0.0608 0.8544 0.2154 -4.500 -0.2106 0.02153 0.01432 -0.0616 0.8527 0.2344 -4.250 -0.1789 0.02117 0.01393 -0.0630 0.8515 0.2447 -4.000 -0.1469 0.02061 0.01340 -0.0645 0.8505 0.2577 -3.750 -0.1132 0.02014 0.01292 -0.0665 0.8497 0.2649 -3.500 -0.0831 0.01937 0.01237 -0.0676 0.8490 0.2963 -3.250 -0.0556 0.01834 0.01185 -0.0684 0.8481 0.4306 -2.500 0.0056 0.01672 0.01140 -0.0650 0.8389 0.7047 -2.250 0.0390 0.01657 0.01120 -0.0668 0.8367 0.7294 -2.000 0.0752 0.01631 0.01092 -0.0693 0.8352 0.7457 -1.750 0.1122 0.01603 0.01061 -0.0720 0.8339 0.7574 -1.500 0.1472 0.01565 0.01032 -0.0742 0.8326 0.7742 -1.250 0.1852 0.01536 0.01004 -0.0771 0.8315 0.7818 -1.000 0.2239 0.01499 0.00982 -0.0801 0.8304 0.8027 -0.750 0.2661 0.01470 0.00959 -0.0841 0.8294 0.8176 -0.500 0.2705 0.01543 0.01040 -0.0790 0.8217 0.8352 -0.250 0.3042 0.01548 0.01048 -0.0810 0.8189 0.8486 0.000 0.3485 0.01568 0.01073 -0.0854 0.8171 0.8625 0.250 0.4045 0.01614 0.01122 -0.0927 0.8157 0.8748 0.500 0.4573 0.01632 0.01140 -0.0992 0.8142 0.8817 0.750 0.5070 0.01629 0.01134 -0.1051 0.8129 0.8862 1.000 0.5595 0.01638 0.01141 -0.1116 0.8116 0.8937 1.250 0.5537 0.01726 0.01233 -0.1039 0.8044 0.9040 1.500 0.5717 0.01741 0.01247 -0.1021 0.8002 0.9182 1.750 0.5977 0.01736 0.01239 -0.1021 0.7970 0.9286 2.000 0.6458 0.01727 0.01226 -0.1076 0.7946 0.9305 2.250 0.6936 0.01715 0.01211 -0.1132 0.7928 0.9323 2.500 0.6754 0.01826 0.01325 -0.1024 0.7815 0.9421 2.750 0.7107 0.01842 0.01341 -0.1049 0.7791 0.9441 3.000 0.7371 0.01855 0.01353 -0.1052 0.7773 0.9510 3.250 0.7852 0.01834 0.01328 -0.1108 0.7743 0.9516 3.500 0.7969 0.01917 0.01416 -0.1076 0.7677 0.9541 3.750 0.8177 0.01965 0.01465 -0.1066 0.7627 0.9582 4.000 0.8495 0.01993 0.01492 -0.1082 0.7592 0.9622 4.250 0.8950 0.01977 0.01473 -0.1131 0.7556 0.9630 4.500 0.9175 0.02026 0.01526 -0.1127 0.7507 0.9652 4.750 0.9195 0.02094 0.01593 -0.1071 0.7409 0.9706 5.000 0.9629 0.02096 0.01595 -0.1116 0.7376 0.9714 5.250 0.9897 0.02120 0.01619 -0.1122 0.7315 0.9725 5.500 1.0045 0.02190 0.01689 -0.1099 0.7209 0.9757 5.750 1.0461 0.02186 0.01680 -0.1138 0.7153 0.9787 6.000 1.0586 0.02261 0.01762 -0.1112 0.7082 0.9801 6.250 1.0834 0.02285 0.01780 -0.1113 0.6965 0.9814 6.500 1.1032 0.02331 0.01831 -0.1103 0.6913 0.9837 6.750 1.1220 0.02412 0.01910 -0.1091 0.6768 0.9868 7.000 1.1383 0.02465 0.01967 -0.1074 0.6677 0.9878 7.250 1.1592 0.02532 0.02031 -0.1068 0.6542 0.9903 7.500 1.1669 0.02637 0.02131 -0.1033 0.6342 0.9926 7.750 1.1824 0.02691 0.02188 -0.1015 0.6197 0.9932 8.000 1.1911 0.02842 0.02320 -0.0986 0.5847 0.9951 8.250 1.2003 0.02918 0.02389 -0.0955 0.5709 0.9956 8.500 1.2247 0.03028 0.02491 -0.0962 0.5534 0.9978 8.750 1.2196 0.03136 0.02585 -0.0901 0.5343 0.9978 9.000 1.2513 0.03174 0.02628 -0.0924 0.5277 0.9985 9.250 1.2704 0.03268 0.02715 -0.0920 0.5135 0.9992 9.500 1.2860 0.03327 0.02778 -0.0905 0.5056 0.9994 9.750 1.2967 0.03424 0.02869 -0.0882 0.4929 0.9997 10.000 1.3115 0.03503 0.02954 -0.0868 0.4798 1.0000 10.250 1.3167 0.03594 0.03043 -0.0833 0.4696 1.0000 10.500 1.3180 0.03712 0.03158 -0.0790 0.4512 1.0000 10.750 1.3191 0.03836 0.03279 -0.0748 0.4306 1.0000 11.000 1.3051 0.04052 0.03478 -0.0681 0.3899 1.0000 11.250 1.2765 0.04368 0.03762 -0.0593 0.3390 1.0000 11.500 1.2682 0.04569 0.03949 -0.0540 0.3138 1.0000 11.750 1.2638 0.04751 0.04121 -0.0497 0.2918 1.0000 12.000 1.2604 0.04931 0.04288 -0.0456 0.2641 1.0000 12.250 1.2613 0.05088 0.04438 -0.0422 0.2476 1.0000 12.750 1.2668 0.05381 0.04724 -0.0364 0.2239 1.0000 13.250 1.2769 0.05651 0.04995 -0.0315 0.2088 1.0000 13.500 1.2801 0.05803 0.05143 -0.0290 0.2002 1.0000 13.750 1.2855 0.05940 0.05281 -0.0268 0.1923 1.0000 14.000 1.2900 0.06084 0.05425 -0.0245 0.1821 1.0000 14.250 1.2964 0.06216 0.05559 -0.0226 0.1743 1.0000 14.500 1.2995 0.06377 0.05719 -0.0203 0.1642 1.0000 14.750 1.2985 0.06574 0.05905 -0.0176 0.1428 1.0000 15.000 1.2965 0.06782 0.06105 -0.0150 0.1260 1.0000 15.500 1.2884 0.07244 0.06550 -0.0095 0.0984 1.0000 15.750 1.2890 0.07439 0.06746 -0.0073 0.0933 1.0000 16.000 1.2882 0.07647 0.06953 -0.0052 0.0872 1.0000 16.250 1.2873 0.07863 0.07171 -0.0031 0.0836 1.0000 16.500 1.2912 0.08033 0.07348 -0.0015 0.0809 1.0000 16.750 1.2890 0.08265 0.07580 0.0004 0.0771 1.0000 17.000 1.2872 0.08492 0.07811 0.0023 0.0746 1.0000 17.250 1.2941 0.08637 0.07963 0.0033 0.0717 1.0000 17.500 1.2925 0.08869 0.08199 0.0049 0.0688 1.0000 17.750 1.2904 0.09107 0.08438 0.0065 0.0665 1.0000 18.000 1.2952 0.09277 0.08616 0.0075 0.0643 1.0000 18.250 1.2981 0.09466 0.08809 0.0085 0.0617 1.0000 18.500 1.2993 0.09677 0.09023 0.0095 0.0601 1.0000 18.750 1.2968 0.09929 0.09278 0.0107 0.0581 1.0000