XFOIL Version 6.96 Calculated polar for: RG 15A-1.8/11.0 AIRFOIL 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 ------ -------- --------- --------- -------- -------- -------- -15.750 -0.8632 0.09280 0.09052 -0.0344 1.0000 0.0041 -15.500 -0.9634 0.07032 0.06782 -0.0473 1.0000 0.0040 -15.250 -1.0194 0.05497 0.05222 -0.0578 1.0000 0.0039 -15.000 -1.0476 0.04595 0.04299 -0.0648 1.0000 0.0039 -14.750 -1.0689 0.03978 0.03663 -0.0687 1.0000 0.0039 -14.500 -1.0732 0.03662 0.03336 -0.0699 1.0000 0.0039 -14.250 -1.0855 0.03311 0.02969 -0.0705 1.0000 0.0039 -14.000 -1.0829 0.03142 0.02791 -0.0699 1.0000 0.0040 -13.750 -1.0920 0.02922 0.02557 -0.0682 1.0000 0.0040 -13.500 -1.0983 0.02784 0.02407 -0.0650 1.0000 0.0040 -13.250 -1.1024 0.02671 0.02284 -0.0612 1.0000 0.0041 -13.000 -1.0967 0.02565 0.02168 -0.0588 1.0000 0.0041 -12.750 -1.0881 0.02470 0.02063 -0.0566 1.0000 0.0042 -12.500 -1.0796 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0.7433 0.1668 -2.500 0.0041 0.00706 0.00126 -0.0616 0.7285 0.1896 -2.250 0.0305 0.00692 0.00118 -0.0614 0.7133 0.2228 -2.000 0.0566 0.00674 0.00110 -0.0611 0.6973 0.2713 -1.750 0.0829 0.00659 0.00104 -0.0609 0.6816 0.3163 -1.500 0.1091 0.00642 0.00098 -0.0606 0.6655 0.3706 -1.000 0.1617 0.00614 0.00091 -0.0601 0.6334 0.4746 -0.750 0.1882 0.00602 0.00089 -0.0599 0.6166 0.5266 -0.500 0.2147 0.00594 0.00090 -0.0596 0.5999 0.5763 -0.250 0.2414 0.00594 0.00092 -0.0594 0.5817 0.6114 0.000 0.2683 0.00598 0.00095 -0.0591 0.5637 0.6352 0.250 0.2953 0.00605 0.00098 -0.0589 0.5449 0.6527 0.500 0.3223 0.00612 0.00102 -0.0587 0.5252 0.6671 0.750 0.3492 0.00622 0.00107 -0.0585 0.5052 0.6795 1.250 0.4030 0.00643 0.00118 -0.0580 0.4651 0.7018 1.500 0.4299 0.00655 0.00124 -0.0578 0.4455 0.7117 1.750 0.4567 0.00667 0.00132 -0.0576 0.4262 0.7221 2.000 0.4834 0.00679 0.00140 -0.0573 0.4062 0.7324 2.250 0.5101 0.00692 0.00148 -0.0571 0.3873 0.7419 2.500 0.5367 0.00706 0.00158 -0.0568 0.3685 0.7520 2.750 0.5632 0.00720 0.00168 -0.0566 0.3501 0.7621 3.000 0.5893 0.00737 0.00180 -0.0563 0.3284 0.7722 3.250 0.6152 0.00756 0.00193 -0.0559 0.3042 0.7829 3.500 0.6410 0.00776 0.00206 -0.0555 0.2826 0.7931 3.750 0.6670 0.00794 0.00220 -0.0552 0.2631 0.8015 4.250 0.7190 0.00830 0.00250 -0.0545 0.2309 0.8191 4.500 0.7447 0.00849 0.00266 -0.0541 0.2153 0.8287 5.000 0.7948 0.00894 0.00304 -0.0532 0.1795 0.8510 5.250 0.8186 0.00924 0.00328 -0.0525 0.1559 0.8638 5.500 0.8424 0.00951 0.00350 -0.0517 0.1372 0.8791 5.750 0.8661 0.00972 0.00372 -0.0509 0.1242 0.8971 6.000 0.8885 0.00993 0.00394 -0.0498 0.1121 0.9200 6.250 0.9119 0.01017 0.00419 -0.0490 0.0984 0.9544 6.500 0.9446 0.01049 0.00447 -0.0503 0.0859 1.0000 6.750 0.9691 0.01080 0.00474 -0.0498 0.0763 1.0000 7.000 0.9935 0.01111 0.00502 -0.0493 0.0676 1.0000 7.250 1.0178 0.01143 0.00532 -0.0488 0.0603 1.0000 7.500 1.0414 0.01180 0.00564 -0.0481 0.0522 1.0000 7.750 1.0653 0.01214 0.00596 -0.0476 0.0451 1.0000 8.000 1.0883 0.01254 0.00633 -0.0469 0.0378 1.0000 8.250 1.1109 0.01297 0.00671 -0.0461 0.0311 1.0000 8.500 1.1338 0.01336 0.00710 -0.0454 0.0274 1.0000 8.750 1.1563 0.01377 0.00750 -0.0446 0.0239 1.0000 9.000 1.1791 0.01413 0.00788 -0.0439 0.0219 1.0000 9.250 1.2009 0.01456 0.00831 -0.0430 0.0196 1.0000 9.500 1.2226 0.01498 0.00875 -0.0422 0.0177 1.0000 9.750 1.2445 0.01537 0.00917 -0.0413 0.0165 1.0000 10.000 1.2653 0.01581 0.00963 -0.0403 0.0148 1.0000 10.250 1.2852 0.01630 0.01013 -0.0392 0.0131 1.0000 10.500 1.3052 0.01676 0.01062 -0.0381 0.0116 1.0000 10.750 1.3233 0.01732 0.01119 -0.0367 0.0099 1.0000 11.000 1.3412 0.01785 0.01175 -0.0353 0.0084 1.0000 11.250 1.3558 0.01845 0.01237 -0.0333 0.0068 1.0000 11.500 1.3694 0.01905 0.01301 -0.0312 0.0058 1.0000 11.750 1.3814 0.01973 0.01373 -0.0289 0.0049 1.0000 12.000 1.3943 0.02037 0.01443 -0.0268 0.0045 1.0000 12.250 1.4061 0.02109 0.01520 -0.0246 0.0041 1.0000 12.500 1.4167 0.02188 0.01604 -0.0225 0.0037 1.0000 12.750 1.4265 0.02274 0.01697 -0.0203 0.0035 1.0000 13.000 1.4351 0.02370 0.01800 -0.0181 0.0033 1.0000 13.250 1.4428 0.02474 0.01912 -0.0160 0.0031 1.0000 13.500 1.4513 0.02577 0.02024 -0.0141 0.0030 1.0000 13.750 1.4584 0.02694 0.02149 -0.0123 0.0030 1.0000 14.000 1.4642 0.02827 0.02290 -0.0106 0.0029 1.0000 14.250 1.4700 0.02965 0.02438 -0.0091 0.0028 1.0000 14.500 1.4735 0.03131 0.02612 -0.0076 0.0027 1.0000 14.750 1.4764 0.03311 0.02802 -0.0064 0.0026 1.0000 15.000 1.4785 0.03508 0.03009 -0.0054 0.0026 1.0000 15.250 1.4791 0.03732 0.03243 -0.0047 0.0025 1.0000 15.500 1.4787 0.03980 0.03501 -0.0042 0.0025 1.0000 15.750 1.4772 0.04253 0.03785 -0.0041 0.0024 1.0000 16.000 1.4734 0.04568 0.04111 -0.0042 0.0023 1.0000 16.250 1.4693 0.04905 0.04459 -0.0047 0.0024 1.0000 16.500 1.4623 0.05299 0.04865 -0.0057 0.0023 1.0000 16.750 1.4550 0.05720 0.05298 -0.0070 0.0023 1.0000 17.000 1.4443 0.06212 0.05804 -0.0089 0.0022 1.0000 17.250 1.4309 0.06774 0.06380 -0.0113 0.0022 1.0000 17.500 1.4157 0.07392 0.07012 -0.0142 0.0022 1.0000 17.750 1.3995 0.08056 0.07690 -0.0175 0.0022 1.0000 18.000 1.3827 0.08755 0.08402 -0.0211 0.0022 1.0000 18.250 1.3605 0.09581 0.09243 -0.0255 0.0022 1.0000 18.500 1.3374 0.10450 0.10128 -0.0303 0.0022 1.0000 18.750 1.3135 0.11364 0.11057 -0.0355 0.0022 1.0000 19.000 1.2890 0.12313 0.12019 -0.0410 0.0022 1.0000 19.250 1.2629 0.13320 0.13041 -0.0469 0.0022 1.0000