XFOIL Version 6.96 Calculated polar for: LOCKHEED C-141 BL113.6 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -12.500 -0.6924 0.07736 0.07311 -0.0686 1.0000 0.0464 -12.250 -0.7054 0.07239 0.06813 -0.0694 1.0000 0.0461 -12.000 -0.7283 0.06756 0.06325 -0.0701 1.0000 0.0457 -11.750 -0.7552 0.06346 0.05907 -0.0692 1.0000 0.0454 -11.500 -0.7840 0.06025 0.05577 -0.0663 1.0000 0.0451 -11.250 -0.8146 0.05787 0.05330 -0.0613 1.0000 0.0449 -11.000 -0.8463 0.05618 0.05153 -0.0544 1.0000 0.0447 -10.750 -0.8745 0.05387 0.04908 -0.0480 1.0000 0.0445 -10.500 -0.8986 0.05105 0.04605 -0.0421 1.0000 0.0443 -10.250 -0.9183 0.04801 0.04274 -0.0366 1.0000 0.0443 -10.000 -0.9325 0.04485 0.03926 -0.0315 1.0000 0.0443 -9.750 -0.9412 0.04177 0.03582 -0.0269 1.0000 0.0444 -9.500 -0.9445 0.03893 0.03258 -0.0227 1.0000 0.0448 -9.250 -0.9427 0.03640 0.02964 -0.0191 1.0000 0.0455 -9.000 -0.9374 0.03443 0.02722 -0.0157 1.0000 0.0462 -8.750 -0.9256 0.03213 0.02479 -0.0138 1.0000 0.0476 -8.500 -0.9101 0.03121 0.02385 -0.0122 1.0000 0.0491 -8.250 -0.8942 0.03017 0.02270 -0.0104 1.0000 0.0508 -8.000 -0.8783 0.02885 0.02111 -0.0085 1.0000 0.0526 -7.750 -0.8617 0.02781 0.01972 -0.0066 1.0000 0.0542 -7.500 -0.8422 0.02613 0.01806 -0.0056 1.0000 0.0564 -7.250 -0.8234 0.02549 0.01739 -0.0043 1.0000 0.0589 -7.000 -0.8039 0.02479 0.01652 -0.0029 1.0000 0.0618 -6.750 -0.7837 0.02365 0.01526 -0.0018 1.0000 0.0645 -6.500 -0.7638 0.02296 0.01462 -0.0007 1.0000 0.0676 -6.250 -0.7435 0.02244 0.01402 0.0005 1.0000 0.0713 -6.000 -0.7228 0.02164 0.01312 0.0016 1.0000 0.0748 -5.750 -0.7026 0.02102 0.01257 0.0026 1.0000 0.0790 -5.500 -0.6810 0.02061 0.01209 0.0036 0.9999 0.0837 -5.250 -0.6482 0.01989 0.01142 0.0021 0.9973 0.0898 -5.000 -0.6134 0.01964 0.01110 0.0004 0.9947 0.0973 -4.750 -0.5820 0.01902 0.01059 -0.0009 0.9917 0.1060 -4.500 -0.5503 0.01856 0.01018 -0.0021 0.9882 0.1170 -4.250 -0.5166 0.01817 0.00987 -0.0037 0.9853 0.1323 -4.000 -0.4830 0.01782 0.00961 -0.0054 0.9823 0.1550 -3.750 -0.4549 0.01726 0.00928 -0.0059 0.9779 0.1900 -3.500 -0.4239 0.01652 0.00901 -0.0074 0.9745 0.2704 -3.250 -0.3936 0.01541 0.00892 -0.0089 0.9721 0.4660 -3.000 -0.3698 0.01490 0.00905 -0.0081 0.9674 0.6096 -2.750 -0.3411 0.01483 0.00923 -0.0081 0.9627 0.6861 -2.500 -0.3066 0.01494 0.00944 -0.0092 0.9592 0.7369 -2.250 -0.2774 0.01503 0.00961 -0.0092 0.9548 0.7728 -2.000 -0.2511 0.01509 0.00974 -0.0085 0.9488 0.8023 -1.750 -0.2174 0.01525 0.00995 -0.0093 0.9451 0.8298 -1.500 -0.1819 0.01548 0.01019 -0.0104 0.9420 0.8548 -1.250 -0.1629 0.01555 0.01028 -0.0083 0.9340 0.8764 -1.000 -0.1281 0.01577 0.01051 -0.0091 0.9301 0.8959 -0.750 -0.0882 0.01606 0.01078 -0.0109 0.9277 0.9138 -0.500 -0.0610 0.01637 0.01109 -0.0103 0.9206 0.9336 -0.250 -0.0106 0.01685 0.01155 -0.0142 0.9181 0.9502 0.000 0.0415 0.01707 0.01175 -0.0191 0.9158 0.9584 0.250 0.0978 0.01718 0.01184 -0.0251 0.9141 0.9613 0.500 0.1532 0.01720 0.01185 -0.0308 0.9126 0.9646 0.750 0.1938 0.01724 0.01190 -0.0338 0.9065 0.9716 1.000 0.2457 0.01715 0.01183 -0.0388 0.9023 0.9745 1.250 0.3072 0.01668 0.01139 -0.0453 0.8989 0.9751 1.500 0.3686 0.01567 0.01041 -0.0509 0.8903 0.9748 1.750 0.4230 0.01483 0.00960 -0.0554 0.8829 0.9764 2.000 0.4676 0.01426 0.00908 -0.0582 0.8739 0.9807 2.250 0.5140 0.01358 0.00845 -0.0613 0.8652 0.9841 2.500 0.5566 0.01303 0.00796 -0.0639 0.8515 0.9882 2.750 0.5968 0.01252 0.00750 -0.0660 0.8350 0.9933 3.000 0.6384 0.01200 0.00701 -0.0683 0.8129 0.9974 3.250 0.6700 0.01161 0.00663 -0.0688 0.7820 1.0000 3.500 0.6908 0.01136 0.00628 -0.0670 0.7406 1.0000 3.750 0.7127 0.01130 0.00596 -0.0653 0.6814 1.0000 4.000 0.7275 0.01160 0.00587 -0.0625 0.6004 1.0000 4.250 0.7332 0.01226 0.00598 -0.0581 0.4940 1.0000 4.500 0.7318 0.01321 0.00628 -0.0527 0.3774 1.0000 4.750 0.7319 0.01415 0.00668 -0.0478 0.2851 1.0000 5.000 0.7359 0.01495 0.00710 -0.0436 0.2254 1.0000 5.250 0.7433 0.01560 0.00751 -0.0399 0.1871 1.0000 5.500 0.7511 0.01624 0.00794 -0.0363 0.1622 1.0000 5.750 0.7613 0.01678 0.00839 -0.0330 0.1438 1.0000 6.000 0.7716 0.01736 0.00887 -0.0298 0.1298 1.0000 6.250 0.7825 0.01795 0.00937 -0.0267 0.1186 1.0000 6.500 0.7961 0.01844 0.00987 -0.0240 0.1092 1.0000 6.750 0.8083 0.01914 0.01050 -0.0212 0.1015 1.0000 7.000 0.8230 0.01965 0.01101 -0.0188 0.0946 1.0000 7.250 0.8378 0.02046 0.01177 -0.0165 0.0887 1.0000 7.500 0.8542 0.02100 0.01234 -0.0145 0.0831 1.0000 7.750 0.8727 0.02205 0.01328 -0.0131 0.0781 1.0000 8.000 0.8905 0.02259 0.01394 -0.0113 0.0738 1.0000 8.250 0.9088 0.02331 0.01461 -0.0098 0.0699 1.0000 8.500 0.9320 0.02449 0.01582 -0.0093 0.0661 1.0000 8.750 0.9509 0.02521 0.01663 -0.0078 0.0627 1.0000 9.000 0.9711 0.02608 0.01745 -0.0068 0.0598 1.0000 9.250 0.9971 0.02767 0.01912 -0.0068 0.0571 1.0000 9.500 1.0161 0.02865 0.02028 -0.0054 0.0547 1.0000 9.750 1.0342 0.02958 0.02127 -0.0041 0.0524 1.0000 10.000 1.0582 0.03106 0.02268 -0.0040 0.0502 1.0000 10.250 1.0755 0.03278 0.02467 -0.0026 0.0488 1.0000 10.500 1.0897 0.03437 0.02654 -0.0006 0.0474 1.0000 10.750 1.1033 0.03608 0.02848 0.0014 0.0462 1.0000 11.000 1.1167 0.03759 0.03013 0.0032 0.0450 1.0000 11.250 1.1295 0.03896 0.03158 0.0049 0.0439 1.0000 11.500 1.1459 0.04124 0.03388 0.0056 0.0428 1.0000 11.750 1.1434 0.04366 0.03663 0.0095 0.0422 1.0000 12.000 1.1352 0.04578 0.03910 0.0141 0.0418 1.0000 12.250 1.1253 0.04840 0.04204 0.0183 0.0415 1.0000 12.500 1.1117 0.05134 0.04528 0.0223 0.0413 1.0000 12.750 1.0948 0.05459 0.04883 0.0259 0.0412 1.0000 13.000 1.0747 0.05822 0.05274 0.0290 0.0412 1.0000 13.250 1.0521 0.06229 0.05706 0.0313 0.0413 1.0000 13.500 1.0274 0.06690 0.06191 0.0326 0.0414 1.0000 13.750 1.0015 0.07211 0.06733 0.0326 0.0416 1.0000 14.000 0.9743 0.07810 0.07350 0.0314 0.0418 1.0000 14.250 0.9476 0.08482 0.08038 0.0289 0.0421 1.0000 14.500 0.9237 0.09212 0.08779 0.0256 0.0424 1.0000