XFOIL Version 6.96 Calculated polar for: EPPLER 336 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 = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -9.250 -0.4427 0.08757 0.08432 -0.0204 1.0000 0.0245 -9.000 -0.4469 0.08309 0.07988 -0.0233 1.0000 0.0242 -8.750 -0.4618 0.07766 0.07442 -0.0268 1.0000 0.0245 -8.500 -0.4719 0.07404 0.07079 -0.0269 1.0000 0.0243 -8.250 -0.4936 0.07002 0.06668 -0.0254 1.0000 0.0248 -7.750 -0.5190 0.05715 0.05343 -0.0211 0.9401 0.0132 -7.500 -0.4936 0.05344 0.04940 -0.0249 0.8558 0.0129 -7.250 -0.4887 0.05039 0.04605 -0.0232 0.8117 0.0126 -6.750 -0.4893 0.03937 0.03397 -0.0151 0.7636 0.0104 -6.500 -0.4805 0.03674 0.03099 -0.0123 0.7419 0.0103 -6.250 -0.4690 0.03439 0.02828 -0.0098 0.7222 0.0101 -6.000 -0.4563 0.03171 0.02518 -0.0071 0.7048 0.0100 -5.750 -0.4405 0.02938 0.02245 -0.0048 0.6882 0.0099 -5.500 -0.4224 0.02698 0.01960 -0.0027 0.6731 0.0098 -5.250 -0.4011 0.02486 0.01703 -0.0011 0.6587 0.0098 -5.000 -0.3770 0.02296 0.01472 0.0001 0.6454 0.0098 -4.750 -0.3510 0.02139 0.01279 0.0009 0.6330 0.0099 -4.500 -0.3241 0.02008 0.01120 0.0015 0.6211 0.0102 -4.250 -0.2977 0.01908 0.00999 0.0020 0.6091 0.0103 -4.000 -0.2725 0.01816 0.00896 0.0026 0.5978 0.0108 -3.750 -0.2482 0.01751 0.00821 0.0034 0.5868 0.0114 -3.500 -0.2242 0.01690 0.00749 0.0043 0.5759 0.0123 -3.250 -0.2005 0.01641 0.00691 0.0052 0.5653 0.0140 -3.000 -0.1768 0.01602 0.00643 0.0061 0.5556 0.0161 -2.750 -0.1536 0.01557 0.00593 0.0070 0.5460 0.0186 -2.500 -0.1304 0.01516 0.00542 0.0081 0.5373 0.0214 -2.250 -0.1073 0.01480 0.00502 0.0091 0.5284 0.0295 -2.000 -0.0854 0.01432 0.00463 0.0104 0.5203 0.0536 -1.750 -0.0181 0.01204 0.00557 0.0032 0.5095 0.8088 -1.500 -0.0141 0.01245 0.00590 0.0089 0.5024 0.8658 -1.250 0.0224 0.01330 0.00654 0.0085 0.4937 0.8924 -1.000 0.0703 0.01406 0.00712 0.0056 0.4838 0.9111 -0.750 0.1260 0.01468 0.00751 0.0008 0.4736 0.9248 -0.500 0.1544 0.01480 0.00749 0.0008 0.4650 0.9319 -0.250 0.1874 0.01479 0.00733 -0.0003 0.4574 0.9339 0.000 0.2183 0.01478 0.00720 -0.0010 0.4498 0.9362 0.250 0.2468 0.01479 0.00709 -0.0012 0.4427 0.9390 0.500 0.2717 0.01481 0.00702 -0.0007 0.4353 0.9424 0.750 0.2929 0.01486 0.00696 0.0005 0.4291 0.9460 1.000 0.3247 0.01483 0.00687 -0.0005 0.4218 0.9473 1.250 0.3552 0.01484 0.00677 -0.0012 0.4152 0.9489 1.500 0.3846 0.01484 0.00672 -0.0017 0.4093 0.9506 1.750 0.4128 0.01486 0.00669 -0.0019 0.4034 0.9526 2.000 0.4392 0.01491 0.00666 -0.0018 0.3988 0.9548 2.250 0.4636 0.01496 0.00669 -0.0012 0.3940 0.9571 2.500 0.4844 0.01504 0.00675 0.0001 0.3892 0.9599 2.750 0.5142 0.01506 0.00672 -0.0006 0.3847 0.9609 3.000 0.5436 0.01510 0.00673 -0.0011 0.3807 0.9620 3.250 0.5728 0.01513 0.00677 -0.0016 0.3764 0.9633 3.500 0.6005 0.01519 0.00681 -0.0018 0.3719 0.9647 3.750 0.6271 0.01527 0.00686 -0.0018 0.3683 0.9661 4.000 0.6537 0.01536 0.00696 -0.0018 0.3646 0.9678 4.250 0.6788 0.01544 0.00708 -0.0015 0.3605 0.9693 4.500 0.7024 0.01555 0.00718 -0.0009 0.3568 0.9708 4.750 0.7242 0.01571 0.00733 0.0001 0.3535 0.9727 5.000 0.7524 0.01579 0.00746 -0.0002 0.3496 0.9736 5.250 0.7796 0.01589 0.00762 -0.0004 0.3452 0.9744 5.500 0.8062 0.01601 0.00775 -0.0005 0.3412 0.9753 5.750 0.8331 0.01618 0.00789 -0.0006 0.3377 0.9764 6.000 0.8598 0.01631 0.00813 -0.0007 0.3332 0.9777 6.250 0.8848 0.01646 0.00835 -0.0005 0.3285 0.9788 6.500 0.9089 0.01665 0.00855 -0.0001 0.3245 0.9798 6.750 0.9328 0.01685 0.00880 0.0004 0.3201 0.9810 7.000 0.9567 0.01703 0.00911 0.0008 0.3153 0.9824 7.250 0.9791 0.01724 0.00937 0.0015 0.3107 0.9837 7.500 1.0022 0.01749 0.00962 0.0021 0.3062 0.9846 7.750 1.0278 0.01764 0.00996 0.0021 0.3002 0.9854 8.000 1.0527 0.01781 0.01022 0.0022 0.2943 0.9862 8.250 1.0771 0.01801 0.01052 0.0024 0.2881 0.9872 8.500 1.1023 0.01817 0.01083 0.0024 0.2807 0.9884 8.750 1.1267 0.01837 0.01114 0.0026 0.2734 0.9897 9.000 1.1494 0.01857 0.01145 0.0031 0.2655 0.9908 9.250 1.1714 0.01881 0.01181 0.0037 0.2570 0.9919 9.500 1.1920 0.01909 0.01214 0.0045 0.2480 0.9931 9.750 1.2120 0.01944 0.01256 0.0053 0.2377 0.9943 10.000 1.2334 0.01985 0.01305 0.0057 0.2263 0.9954 10.250 1.2539 0.02035 0.01362 0.0062 0.2145 0.9969 10.500 1.2738 0.02095 0.01427 0.0066 0.2015 0.9986 10.750 1.2906 0.02164 0.01501 0.0075 0.1878 1.0000 11.000 1.2956 0.02235 0.01575 0.0107 0.1768 1.0000 11.250 1.2962 0.02315 0.01657 0.0145 0.1661 1.0000 11.500 1.2939 0.02394 0.01740 0.0188 0.1564 1.0000 11.750 1.2814 0.02467 0.01817 0.0247 0.1498 1.0000 12.000 1.2656 0.02549 0.01904 0.0308 0.1440 1.0000 12.250 1.2487 0.02661 0.02020 0.0363 0.1390 1.0000 12.500 1.2353 0.02794 0.02159 0.0405 0.1329 1.0000 12.750 1.2194 0.02982 0.02348 0.0439 0.1273 1.0000 13.000 1.2102 0.03178 0.02551 0.0461 0.1206 1.0000 13.250 1.1983 0.03436 0.02812 0.0475 0.1147 1.0000 13.500 1.1908 0.03691 0.03074 0.0483 0.1084 1.0000 13.750 1.1794 0.04006 0.03392 0.0487 0.1029 1.0000 14.000 1.1712 0.04311 0.03704 0.0488 0.0971 1.0000 14.250 1.1602 0.04659 0.04056 0.0486 0.0923 1.0000 14.500 1.1499 0.05012 0.04416 0.0482 0.0874 1.0000 14.750 1.1396 0.05377 0.04788 0.0476 0.0826 1.0000 15.000 1.1271 0.05778 0.05193 0.0468 0.0790 1.0000 15.250 1.1200 0.06135 0.05558 0.0461 0.0748 1.0000 15.500 1.1108 0.06530 0.05959 0.0450 0.0711 1.0000 15.750 1.0994 0.06968 0.06400 0.0437 0.0676 1.0000 16.000 1.0936 0.07343 0.06785 0.0426 0.0637 1.0000 16.250 1.0851 0.07763 0.07210 0.0412 0.0604 1.0000 16.500 1.0759 0.08202 0.07653 0.0397 0.0575 1.0000 16.750 1.0706 0.08597 0.08058 0.0383 0.0540 1.0000 17.000 1.0622 0.09042 0.08508 0.0366 0.0509 1.0000