XFOIL Version 6.96 Calculated polar for: SA7036 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 ------ -------- --------- --------- -------- -------- -------- -10.000 -0.4067 0.10136 0.09969 -0.0250 1.0000 0.0036 -9.750 -0.4079 0.09668 0.09504 -0.0267 1.0000 0.0034 -8.750 -0.5787 0.02232 0.01924 -0.0759 0.9648 0.0027 -8.500 -0.5610 0.01980 0.01634 -0.0756 0.9573 0.0027 -8.250 -0.5469 0.01642 0.01239 -0.0746 0.9489 0.0029 -8.000 -0.5241 0.01542 0.01122 -0.0741 0.9431 0.0031 -7.750 -0.4998 0.01471 0.01038 -0.0737 0.9372 0.0032 -7.500 -0.4749 0.01418 0.00974 -0.0733 0.9315 0.0034 -7.250 -0.4497 0.01364 0.00910 -0.0729 0.9262 0.0036 -7.000 -0.4244 0.01304 0.00839 -0.0726 0.9200 0.0038 -6.500 -0.3732 0.01191 0.00703 -0.0719 0.9076 0.0042 -6.250 -0.3476 0.01137 0.00638 -0.0715 0.9009 0.0044 -6.000 -0.3212 0.01091 0.00580 -0.0712 0.8939 0.0046 -5.750 -0.2948 0.01052 0.00532 -0.0709 0.8868 0.0048 -5.500 -0.2684 0.00996 0.00467 -0.0707 0.8794 0.0052 -5.000 -0.2142 0.00952 0.00416 -0.0704 0.8632 0.0062 -4.750 -0.1871 0.00931 0.00389 -0.0702 0.8531 0.0070 -4.500 -0.1599 0.00911 0.00360 -0.0700 0.8420 0.0075 -4.250 -0.1329 0.00880 0.00320 -0.0698 0.8307 0.0080 -4.000 -0.1058 0.00846 0.00280 -0.0696 0.8194 0.0090 -3.750 -0.0783 0.00826 0.00254 -0.0694 0.8076 0.0098 -3.500 -0.0508 0.00811 0.00232 -0.0693 0.7947 0.0108 -3.250 -0.0233 0.00799 0.00212 -0.0692 0.7802 0.0115 -3.000 0.0041 0.00786 0.00189 -0.0690 0.7645 0.0119 -2.750 0.0315 0.00772 0.00165 -0.0688 0.7474 0.0130 -2.500 0.0590 0.00762 0.00147 -0.0687 0.7297 0.0150 -2.250 0.0865 0.00755 0.00133 -0.0685 0.7115 0.0181 -2.000 0.1138 0.00740 0.00120 -0.0684 0.6937 0.0414 -1.500 0.1685 0.00714 0.00102 -0.0683 0.6596 0.1075 -1.250 0.1959 0.00702 0.00095 -0.0682 0.6422 0.1460 -1.000 0.2232 0.00689 0.00090 -0.0682 0.6244 0.1976 -0.750 0.2501 0.00663 0.00087 -0.0682 0.6065 0.2947 -0.500 0.2769 0.00639 0.00086 -0.0682 0.5884 0.3968 -0.250 0.3040 0.00626 0.00086 -0.0682 0.5695 0.4678 0.000 0.3311 0.00617 0.00088 -0.0681 0.5514 0.5322 0.250 0.3582 0.00613 0.00091 -0.0680 0.5336 0.5874 0.500 0.3855 0.00610 0.00094 -0.0679 0.5169 0.6339 0.750 0.4126 0.00608 0.00098 -0.0678 0.5001 0.6812 1.000 0.4392 0.00607 0.00104 -0.0675 0.4816 0.7320 1.250 0.4655 0.00608 0.00111 -0.0672 0.4617 0.7792 1.500 0.4911 0.00608 0.00118 -0.0666 0.4407 0.8302 1.750 0.5148 0.00607 0.00126 -0.0656 0.4231 0.8872 2.000 0.5378 0.00610 0.00133 -0.0643 0.4074 0.9432 2.250 0.5712 0.00620 0.00139 -0.0655 0.3891 0.9829 2.500 0.6034 0.00634 0.00146 -0.0666 0.3732 1.0000 2.750 0.6302 0.00651 0.00154 -0.0664 0.3567 1.0000 3.000 0.6569 0.00668 0.00165 -0.0662 0.3397 1.0000 3.500 0.7100 0.00708 0.00188 -0.0659 0.3021 1.0000 3.750 0.7365 0.00730 0.00201 -0.0657 0.2837 1.0000 4.250 0.7895 0.00771 0.00230 -0.0653 0.2534 1.0000 4.500 0.8159 0.00793 0.00245 -0.0651 0.2382 1.0000 4.750 0.8422 0.00816 0.00262 -0.0649 0.2223 1.0000 5.000 0.8684 0.00839 0.00281 -0.0647 0.2079 1.0000 5.250 0.8942 0.00866 0.00301 -0.0645 0.1906 1.0000 5.500 0.9197 0.00897 0.00323 -0.0642 0.1721 1.0000 5.750 0.9453 0.00926 0.00346 -0.0639 0.1569 1.0000 6.000 0.9707 0.00957 0.00370 -0.0636 0.1418 1.0000 6.250 0.9961 0.00986 0.00396 -0.0633 0.1295 1.0000 6.500 1.0210 0.01022 0.00425 -0.0629 0.1126 1.0000 6.750 1.0456 0.01058 0.00455 -0.0625 0.0975 1.0000 7.000 1.0701 0.01097 0.00487 -0.0621 0.0840 1.0000 7.250 1.0938 0.01142 0.00525 -0.0615 0.0685 1.0000 7.500 1.1171 0.01190 0.00565 -0.0610 0.0538 1.0000 7.750 1.1407 0.01233 0.00604 -0.0604 0.0436 1.0000 8.000 1.1642 0.01278 0.00645 -0.0599 0.0350 1.0000 8.250 1.1871 0.01325 0.00689 -0.0593 0.0272 1.0000 8.500 1.2098 0.01373 0.00735 -0.0586 0.0208 1.0000 8.750 1.2320 0.01425 0.00785 -0.0579 0.0153 1.0000 9.000 1.2536 0.01480 0.00839 -0.0571 0.0109 1.0000 9.250 1.2755 0.01530 0.00890 -0.0563 0.0081 1.0000 9.500 1.2958 0.01593 0.00952 -0.0554 0.0046 1.0000 9.750 1.3159 0.01656 0.01017 -0.0543 0.0027 1.0000 10.000 1.3360 0.01714 0.01080 -0.0533 0.0021 1.0000 10.250 1.3554 0.01775 0.01147 -0.0522 0.0018 1.0000 10.500 1.3741 0.01838 0.01218 -0.0510 0.0016 1.0000 10.750 1.3926 0.01899 0.01285 -0.0498 0.0015 1.0000 11.000 1.4100 0.01964 0.01357 -0.0484 0.0014 1.0000 11.250 1.4264 0.02030 0.01431 -0.0470 0.0013 1.0000 11.500 1.4393 0.02101 0.01510 -0.0449 0.0012 1.0000 11.750 1.4506 0.02174 0.01590 -0.0426 0.0012 1.0000 12.000 1.4597 0.02263 0.01688 -0.0401 0.0010 1.0000 12.250 1.4694 0.02350 0.01784 -0.0379 0.0011 1.0000 12.500 1.4765 0.02458 0.01901 -0.0355 0.0010 1.0000 12.750 1.4836 0.02571 0.02023 -0.0334 0.0009 1.0000 13.000 1.4874 0.02712 0.02177 -0.0311 0.0008 1.0000 13.250 1.4910 0.02862 0.02338 -0.0290 0.0008 1.0000 13.500 1.4889 0.03067 0.02558 -0.0268 0.0008 1.0000 13.750 1.4908 0.03252 0.02753 -0.0253 0.0008 1.0000 14.000 1.4817 0.03552 0.03070 -0.0236 0.0007 1.0000 14.250 1.4790 0.03814 0.03346 -0.0227 0.0007 1.0000 14.500 1.4766 0.04092 0.03636 -0.0223 0.0007 1.0000 14.750 1.4727 0.04409 0.03965 -0.0222 0.0007 1.0000 15.000 1.4661 0.04780 0.04349 -0.0227 0.0007 1.0000 15.250 1.4594 0.05181 0.04764 -0.0236 0.0007 1.0000 15.500 1.4492 0.05655 0.05252 -0.0251 0.0007 1.0000 15.750 1.4386 0.06167 0.05778 -0.0270 0.0007 1.0000 16.000 1.4274 0.06719 0.06344 -0.0294 0.0007 1.0000 16.250 1.4111 0.07388 0.07028 -0.0326 0.0007 1.0000 16.500 1.3919 0.08146 0.07802 -0.0364 0.0007 1.0000 16.750 1.3740 0.08906 0.08576 -0.0403 0.0007 1.0000 17.000 1.3548 0.09724 0.09408 -0.0447 0.0007 1.0000 17.250 1.3330 0.10618 0.10317 -0.0495 0.0007 1.0000 17.500 1.3098 0.11571 0.11284 -0.0548 0.0007 1.0000