XFOIL Version 6.96 Calculated polar for: Glenn Martin 3 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -16.250 -0.9380 0.03800 0.03490 -0.1360 0.9735 0.0096 -16.000 -0.9515 0.03504 0.03177 -0.1345 0.9717 0.0099 -15.750 -0.9515 0.03311 0.02970 -0.1329 0.9706 0.0098 -15.500 -0.9470 0.03144 0.02789 -0.1313 0.9697 0.0101 -15.250 -0.9391 0.02994 0.02625 -0.1298 0.9691 0.0102 -15.000 -0.9514 0.02892 0.02514 -0.1232 0.9645 0.0103 -14.750 -0.9485 0.02777 0.02387 -0.1197 0.9625 0.0104 -14.500 -0.9394 0.02674 0.02272 -0.1171 0.9612 0.0105 -14.250 -0.9259 0.02588 0.02175 -0.1151 0.9602 0.0106 -14.000 -0.9123 0.02492 0.02070 -0.1130 0.9594 0.0109 -13.750 -0.9198 0.02425 0.01996 -0.1063 0.9545 0.0112 -13.500 -0.9100 0.02354 0.01917 -0.1031 0.9519 0.0112 -13.250 -0.8949 0.02282 0.01837 -0.1008 0.9504 0.0114 -13.000 -0.8775 0.02211 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0.0294 -3.000 0.0371 0.01022 0.00342 -0.0492 0.6418 0.0297 -2.750 0.0520 0.01033 0.00339 -0.0462 0.6101 0.0301 -2.500 0.0631 0.01056 0.00339 -0.0425 0.5578 0.0307 -2.250 0.0774 0.01077 0.00340 -0.0395 0.5050 0.0316 -2.000 0.0927 0.01101 0.00342 -0.0369 0.4548 0.0322 -1.500 0.1375 0.01114 0.00336 -0.0345 0.4148 0.0337 -1.250 0.1625 0.01112 0.00332 -0.0338 0.4040 0.0355 -1.000 0.1858 0.01117 0.00331 -0.0328 0.3925 0.0357 -0.750 0.2105 0.01117 0.00328 -0.0322 0.3832 0.0386 -0.500 0.2345 0.01119 0.00328 -0.0313 0.3749 0.0407 -0.250 0.2583 0.01121 0.00329 -0.0305 0.3614 0.0484 0.000 0.2824 0.01123 0.00330 -0.0297 0.3517 0.0593 0.250 0.3065 0.01124 0.00332 -0.0290 0.3424 0.0757 0.500 0.3329 0.01117 0.00337 -0.0289 0.3281 0.1322 0.750 0.3560 0.01124 0.00342 -0.0280 0.3177 0.1450 1.000 0.3785 0.01133 0.00348 -0.0270 0.3041 0.1583 1.250 0.4004 0.01146 0.00355 -0.0259 0.2897 0.1664 1.500 0.4227 0.01157 0.00364 -0.0248 0.2738 0.1829 1.750 0.4457 0.01167 0.00373 -0.0240 0.2631 0.1961 2.000 0.4857 0.01121 0.00393 -0.0275 0.2487 0.4595 2.500 0.6855 0.01223 0.00617 -0.0613 0.2187 0.9762 2.750 0.7534 0.01278 0.00660 -0.0706 0.2086 0.9838 3.000 0.7725 0.01298 0.00678 -0.0689 0.2058 0.9847 3.250 0.8280 0.01307 0.00682 -0.0755 0.2008 0.9880 3.500 0.8553 0.01321 0.00692 -0.0758 0.1976 0.9889 3.750 0.8898 0.01339 0.00704 -0.0777 0.1934 0.9914 4.250 0.9718 0.01348 0.00709 -0.0844 0.1877 0.9975 4.500 1.0126 0.01344 0.00703 -0.0878 0.1852 0.9999 4.750 1.0335 0.01360 0.00717 -0.0867 0.1834 1.0000 5.000 1.0530 0.01379 0.00734 -0.0853 0.1808 1.0000 5.250 1.0721 0.01399 0.00753 -0.0838 0.1783 1.0000 5.500 1.0906 0.01422 0.00775 -0.0822 0.1754 1.0000 5.750 1.1103 0.01439 0.00793 -0.0809 0.1742 1.0000 6.000 1.1299 0.01458 0.00813 -0.0795 0.1736 1.0000 6.250 1.1495 0.01477 0.00833 -0.0782 0.1719 1.0000 6.500 1.1690 0.01498 0.00855 -0.0769 0.1712 1.0000 6.750 1.1883 0.01520 0.00877 -0.0756 0.1691 1.0000 7.000 1.2071 0.01543 0.00901 -0.0742 0.1680 1.0000 7.250 1.2254 0.01569 0.00927 -0.0728 0.1663 1.0000 7.500 1.2440 0.01595 0.00954 -0.0714 0.1651 1.0000 7.750 1.2623 0.01622 0.00983 -0.0700 0.1636 1.0000 8.000 1.2805 0.01651 0.01013 -0.0686 0.1622 1.0000 8.250 1.2981 0.01682 0.01046 -0.0671 0.1606 1.0000 8.500 1.3165 0.01709 0.01076 -0.0658 0.1600 1.0000 8.750 1.3347 0.01737 0.01108 -0.0645 0.1594 1.0000 9.000 1.3531 0.01765 0.01140 -0.0632 0.1590 1.0000 9.250 1.3714 0.01794 0.01172 -0.0620 0.1579 1.0000 9.500 1.3890 0.01826 0.01207 -0.0607 0.1566 1.0000 9.750 1.4065 0.01859 0.01240 -0.0594 0.1530 1.0000 10.000 1.4236 0.01895 0.01277 -0.0581 0.1511 1.0000 10.250 1.4393 0.01940 0.01321 -0.0565 0.1479 1.0000 10.500 1.4550 0.01982 0.01367 -0.0550 0.1464 1.0000 10.750 1.4732 0.02013 0.01401 -0.0540 0.1441 1.0000 11.000 1.4901 0.02051 0.01442 -0.0527 0.1409 1.0000 11.250 1.5065 0.02092 0.01489 -0.0514 0.1411 1.0000 11.500 1.5205 0.02146 0.01541 -0.0499 0.1359 1.0000 11.750 1.5361 0.02193 0.01592 -0.0485 0.1347 1.0000 12.000 1.5510 0.02245 0.01647 -0.0471 0.1330 1.0000 12.250 1.5662 0.02294 0.01699 -0.0458 0.1286 1.0000 12.500 1.5803 0.02351 0.01758 -0.0444 0.1257 1.0000 12.750 1.5933 0.02416 0.01824 -0.0429 0.1222 1.0000 13.000 1.6059 0.02483 0.01893 -0.0414 0.1169 1.0000 13.250 1.6150 0.02573 0.01979 -0.0395 0.1081 1.0000 13.500 1.6103 0.02754 0.02143 -0.0359 0.0860 1.0000 13.750 1.6206 0.02841 0.02235 -0.0343 0.0833 1.0000 14.000 1.6207 0.03000 0.02390 -0.0316 0.0726 1.0000 14.250 1.5785 0.03473 0.02836 -0.0246 0.0329 1.0000 14.500 1.5637 0.03772 0.03134 -0.0212 0.0197 1.0000 14.750 1.5655 0.03949 0.03316 -0.0195 0.0177 1.0000 15.000 1.5653 0.04150 0.03523 -0.0178 0.0158 1.0000 15.250 1.5601 0.04405 0.03783 -0.0160 0.0130 1.0000 15.500 1.5624 0.04599 0.03986 -0.0150 0.0127 1.0000 15.750 1.5618 0.04828 0.04223 -0.0138 0.0120 1.0000 16.000 1.5558 0.05124 0.04526 -0.0127 0.0109 1.0000 16.250 1.5547 0.05374 0.04785 -0.0121 0.0108 1.0000 16.500 1.5500 0.05679 0.05099 -0.0115 0.0103 0.9999 16.750 1.5446 0.06002 0.05432 -0.0112 0.0101 0.9999 17.000 1.5370 0.06367 0.05808 -0.0111 0.0098 0.9999 17.250 1.5264 0.06782 0.06233 -0.0113 0.0092 0.9999 17.500 1.5146 0.07225 0.06688 -0.0118 0.0091 0.9999 17.750 1.4945 0.07804 0.07279 -0.0128 0.0083 0.9998 18.000 1.4776 0.08361 0.07850 -0.0140 0.0084 0.9998 18.250 1.4602 0.08934 0.08438 -0.0154 0.0087 0.9998 18.500 1.4377 0.09584 0.09102 -0.0171 0.0088 0.9998 18.750 1.4090 0.10341 0.09874 -0.0192 0.0085 0.9998 19.000 1.3823 0.11077 0.10624 -0.0213 0.0085 0.9998