XFOIL Version 6.96 Calculated polar for: GOE 795 smoothed 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -10.250 -0.4816 0.10107 0.09868 -0.0229 1.0000 0.0075 -10.000 -0.4852 0.09630 0.09393 -0.0245 1.0000 0.0076 -8.500 -0.6750 0.03224 0.02924 -0.0481 0.9978 0.0073 -8.250 -0.6610 0.02551 0.02172 -0.0501 0.9939 0.0075 -8.000 -0.6386 0.02302 0.01884 -0.0505 0.9906 0.0079 -7.750 -0.6139 0.02085 0.01629 -0.0510 0.9873 0.0082 -7.500 -0.5867 0.01909 0.01419 -0.0517 0.9847 0.0084 -7.250 -0.5584 0.01767 0.01247 -0.0524 0.9824 0.0086 -7.000 -0.5363 0.01600 0.01052 -0.0517 0.9776 0.0090 -6.750 -0.5082 0.01502 0.00939 -0.0521 0.9743 0.0094 -6.500 -0.4776 0.01436 0.00863 -0.0530 0.9719 0.0101 -6.250 -0.4477 0.01372 0.00788 -0.0536 0.9692 0.0107 -6.000 -0.4220 0.01313 0.00719 -0.0532 0.9638 0.0114 -5.750 -0.3923 0.01253 0.00646 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0.7586 0.00913 0.00290 -0.0628 0.2808 1.0000 4.500 0.7788 0.00955 0.00314 -0.0614 0.2398 1.0000 4.750 0.7980 0.01006 0.00343 -0.0598 0.1904 1.0000 5.000 0.8166 0.01063 0.00379 -0.0581 0.1442 1.0000 5.250 0.8364 0.01111 0.00412 -0.0567 0.1126 1.0000 5.500 0.8567 0.01155 0.00444 -0.0553 0.0887 1.0000 5.750 0.8773 0.01196 0.00478 -0.0540 0.0696 1.0000 6.000 0.8975 0.01242 0.00514 -0.0526 0.0514 1.0000 6.250 0.9178 0.01286 0.00554 -0.0512 0.0374 1.0000 6.500 0.9380 0.01331 0.00596 -0.0498 0.0272 1.0000 6.750 0.9582 0.01377 0.00641 -0.0484 0.0208 1.0000 7.000 0.9781 0.01424 0.00689 -0.0469 0.0170 1.0000 7.250 0.9981 0.01472 0.00742 -0.0455 0.0147 1.0000 7.500 1.0181 0.01518 0.00793 -0.0441 0.0130 1.0000 7.750 1.0371 0.01572 0.00852 -0.0425 0.0114 1.0000 8.000 1.0541 0.01644 0.00931 -0.0406 0.0103 1.0000 8.250 1.0728 0.01699 0.00994 -0.0390 0.0099 1.0000 8.500 1.0908 0.01757 0.01061 -0.0373 0.0094 1.0000 8.750 1.1081 0.01820 0.01132 -0.0355 0.0089 1.0000 9.000 1.1263 0.01873 0.01190 -0.0340 0.0081 1.0000 9.250 1.1425 0.01942 0.01266 -0.0321 0.0077 1.0000 9.500 1.1569 0.02023 0.01356 -0.0300 0.0072 1.0000 9.750 1.1669 0.02136 0.01479 -0.0272 0.0067 1.0000 10.000 1.1814 0.02209 0.01563 -0.0251 0.0065 1.0000 10.250 1.1913 0.02302 0.01667 -0.0223 0.0063 1.0000 10.500 1.2009 0.02391 0.01768 -0.0195 0.0061 1.0000 10.750 1.2098 0.02490 0.01879 -0.0167 0.0059 1.0000 11.000 1.2179 0.02600 0.02001 -0.0140 0.0056 1.0000 11.250 1.2262 0.02708 0.02121 -0.0115 0.0054 1.0000 11.500 1.2344 0.02819 0.02244 -0.0091 0.0052 1.0000 11.750 1.2404 0.02951 0.02388 -0.0067 0.0050 1.0000 12.000 1.2459 0.03089 0.02540 -0.0045 0.0049 1.0000 12.250 1.2505 0.03237 0.02701 -0.0025 0.0048 1.0000 12.500 1.2535 0.03405 0.02882 -0.0006 0.0046 1.0000 12.750 1.2528 0.03619 0.03111 0.0013 0.0045 1.0000 13.000 1.2506 0.03857 0.03364 0.0028 0.0044 1.0000 13.250 1.2451 0.04148 0.03673 0.0041 0.0044 1.0000 13.500 1.2317 0.04547 0.04092 0.0048 0.0042 1.0000 13.750 1.2253 0.04888 0.04452 0.0049 0.0042 1.0000 14.000 1.2181 0.05266 0.04850 0.0045 0.0041 1.0000 14.250 1.2068 0.05721 0.05322 0.0034 0.0041 1.0000 14.500 1.2038 0.06089 0.05704 0.0020 0.0041 1.0000 14.750 1.1804 0.06800 0.06438 -0.0009 0.0041 1.0000 15.000 1.1670 0.07405 0.07061 -0.0039 0.0040 1.0000 15.250 1.1530 0.08056 0.07727 -0.0074 0.0041 1.0000 15.500 1.1320 0.08881 0.08569 -0.0119 0.0041 1.0000 15.750 1.1166 0.09633 0.09333 -0.0161 0.0041 1.0000 16.000 1.0948 0.10553 0.10268 -0.0211 0.0040 1.0000 16.250 1.0567 0.11862 0.11592 -0.0280 0.0042 1.0000