XFOIL Version 6.96 Calculated polar for: Fage & Collins 1 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -8.750 -0.4175 0.08916 0.08687 -0.0238 1.0000 0.0224 -8.500 -0.4268 0.08674 0.08450 -0.0233 1.0000 0.0231 -8.250 -0.4460 0.08540 0.08323 -0.0200 1.0000 0.0230 -8.000 -0.4383 0.07865 0.07644 -0.0332 0.9956 0.0237 -7.750 -0.4148 0.07139 0.06904 -0.0438 0.9910 0.0238 -7.500 -0.3985 0.06517 0.06274 -0.0487 0.9875 0.0240 -7.250 -0.3812 0.06161 0.05916 -0.0508 0.9856 0.0242 -7.000 -0.3637 0.05848 0.05600 -0.0527 0.9825 0.0245 -6.750 -0.3452 0.05545 0.05292 -0.0546 0.9785 0.0248 -6.500 -0.3216 0.05204 0.04942 -0.0576 0.9758 0.0254 -6.250 -0.2949 0.04836 0.04562 -0.0610 0.9739 0.0263 -6.000 -0.2771 0.04498 0.04208 -0.0616 0.9679 0.0274 -5.750 -0.2431 0.04052 0.03698 -0.0636 0.9640 0.0289 -5.500 -0.2209 0.03536 0.03169 -0.0655 0.9621 0.0294 -5.250 -0.2039 0.03322 0.02951 -0.0647 0.9560 0.0297 -5.000 -0.1771 0.03114 0.02735 -0.0659 0.9528 0.0302 -4.750 -0.1471 0.02916 0.02525 -0.0673 0.9507 0.0311 -4.500 -0.1153 0.02706 0.02296 -0.0686 0.9492 0.0326 -4.250 -0.0900 0.02687 0.02228 -0.0663 0.9426 0.0350 -4.000 -0.0663 0.02271 0.01795 -0.0668 0.9397 0.0361 -3.750 -0.0341 0.02105 0.01623 -0.0682 0.9378 0.0371 -3.500 0.0014 0.01967 0.01475 -0.0701 0.9362 0.0387 -3.250 0.0296 0.01945 0.01429 -0.0694 0.9308 0.0421 -3.000 0.0600 0.01721 0.01184 -0.0703 0.9273 0.0447 -2.750 0.0979 0.01615 0.01076 -0.0728 0.9247 0.0476 -2.250 0.1685 0.01436 0.00877 -0.0760 0.9153 0.0583 -2.000 0.2065 0.01354 0.00785 -0.0783 0.9095 0.0684 -1.750 0.2381 0.01295 0.00721 -0.0793 0.9021 0.0814 -1.000 0.3360 0.01058 0.00447 -0.0799 0.8784 0.0501 -0.750 0.3595 0.00999 0.00384 -0.0786 0.8685 0.0465 -0.500 0.3873 0.00975 0.00352 -0.0781 0.8596 0.0439 -0.250 0.4110 0.00967 0.00345 -0.0769 0.8490 0.0429 0.000 0.4316 0.00918 0.00297 -0.0751 0.8369 0.0419 0.250 0.4534 0.00889 0.00267 -0.0735 0.8224 0.0416 0.500 0.4752 0.00867 0.00242 -0.0719 0.8052 0.0418 0.750 0.4974 0.00851 0.00220 -0.0703 0.7839 0.0421 1.000 0.5193 0.00843 0.00203 -0.0687 0.7556 0.0426 1.250 0.5398 0.00844 0.00190 -0.0669 0.7175 0.0431 1.500 0.5585 0.00854 0.00179 -0.0646 0.6741 0.0455 1.750 0.5757 0.00875 0.00178 -0.0621 0.6253 0.0477 2.000 0.5927 0.00900 0.00182 -0.0597 0.5796 0.0498 2.250 0.6110 0.00923 0.00190 -0.0575 0.5433 0.0588 2.500 0.7588 0.00811 0.00268 -0.0861 0.4764 1.0000 2.750 0.7790 0.00835 0.00279 -0.0845 0.4492 1.0000 3.000 0.7994 0.00858 0.00291 -0.0829 0.4232 1.0000 3.250 0.8194 0.00885 0.00305 -0.0813 0.3951 1.0000 3.500 0.8388 0.00916 0.00321 -0.0795 0.3611 1.0000 3.750 0.8575 0.00952 0.00338 -0.0777 0.3245 1.0000 4.000 0.8766 0.00989 0.00358 -0.0760 0.2900 1.0000 4.250 0.8959 0.01026 0.00380 -0.0743 0.2573 1.0000 4.750 0.9356 0.01097 0.00429 -0.0712 0.2147 1.0000 5.250 0.9770 0.01156 0.00481 -0.0685 0.1937 1.0000 5.500 0.9974 0.01188 0.00511 -0.0670 0.1849 1.0000 5.750 1.0180 0.01218 0.00538 -0.0657 0.1755 1.0000 6.000 1.0391 0.01245 0.00565 -0.0644 0.1670 1.0000 6.250 1.0587 0.01281 0.00598 -0.0629 0.1582 1.0000 6.500 1.0807 0.01300 0.00621 -0.0619 0.1500 1.0000 6.750 1.1011 0.01331 0.00651 -0.0605 0.1409 1.0000 7.000 1.1218 0.01360 0.00678 -0.0593 0.1297 1.0000 7.250 1.1423 0.01390 0.00705 -0.0580 0.1159 1.0000 7.500 1.1613 0.01430 0.00739 -0.0564 0.0981 1.0000 7.750 1.1785 0.01484 0.00783 -0.0546 0.0819 1.0000 8.000 1.1952 0.01539 0.00833 -0.0528 0.0699 1.0000 8.250 1.2116 0.01596 0.00887 -0.0508 0.0588 1.0000 8.500 1.2268 0.01662 0.00948 -0.0487 0.0471 1.0000 8.750 1.2401 0.01741 0.01022 -0.0462 0.0358 1.0000 9.000 1.2522 0.01820 0.01098 -0.0435 0.0298 1.0000 9.250 1.2652 0.01879 0.01163 -0.0409 0.0268 1.0000 9.500 1.2758 0.01951 0.01236 -0.0379 0.0245 1.0000 9.750 1.2845 0.02032 0.01326 -0.0347 0.0230 1.0000 10.000 1.2964 0.02097 0.01399 -0.0321 0.0219 1.0000 10.250 1.3068 0.02172 0.01482 -0.0293 0.0207 1.0000 10.500 1.3152 0.02261 0.01576 -0.0264 0.0198 1.0000 10.750 1.3165 0.02395 0.01718 -0.0226 0.0189 1.0000 11.000 1.3225 0.02504 0.01838 -0.0196 0.0185 1.0000 11.250 1.3325 0.02591 0.01935 -0.0173 0.0179 1.0000 11.500 1.3403 0.02693 0.02046 -0.0149 0.0173 1.0000 11.750 1.3443 0.02827 0.02191 -0.0121 0.0169 1.0000 12.000 1.3510 0.02943 0.02315 -0.0100 0.0164 1.0000 12.250 1.3538 0.03095 0.02476 -0.0076 0.0160 1.0000 12.500 1.3548 0.03267 0.02656 -0.0053 0.0155 1.0000 12.750 1.3503 0.03497 0.02897 -0.0028 0.0151 1.0000 13.000 1.3457 0.03748 0.03159 -0.0006 0.0149 1.0000 13.250 1.3448 0.03971 0.03397 0.0010 0.0146 1.0000 13.500 1.3455 0.04189 0.03628 0.0022 0.0144 1.0000 13.750 1.3443 0.04435 0.03888 0.0032 0.0143 1.0000 14.000 1.3430 0.04695 0.04162 0.0038 0.0140 1.0000 14.250 1.3391 0.05000 0.04482 0.0042 0.0138 1.0000 14.500 1.3338 0.05337 0.04833 0.0044 0.0138 1.0000 14.750 1.3280 0.05698 0.05209 0.0040 0.0136 1.0000 15.000 1.3215 0.06089 0.05614 0.0032 0.0134 1.0000 15.250 1.3144 0.06504 0.06045 0.0021 0.0133 1.0000 15.500 1.3048 0.06979 0.06534 0.0006 0.0132 1.0000 15.750 1.2966 0.07452 0.07019 -0.0013 0.0130 1.0000 16.000 1.2845 0.07994 0.07577 -0.0034 0.0129 1.0000 16.250 1.2711 0.08577 0.08177 -0.0058 0.0130 1.0000 16.500 1.2605 0.09137 0.08748 -0.0085 0.0128 1.0000 16.750 1.2486 0.09728 0.09351 -0.0115 0.0127 1.0000 17.000 1.2334 0.10395 0.10032 -0.0147 0.0126 1.0000 17.250 1.2124 0.11195 0.10851 -0.0186 0.0128 1.0000 17.500 1.2044 0.11762 0.11425 -0.0218 0.0125 1.0000 17.750 1.1777 0.12733 0.12417 -0.0269 0.0127 1.0000 18.000 1.1598 0.13557 0.13254 -0.0315 0.0127 1.0000 18.250 1.1424 0.14400 0.14111 -0.0363 0.0127 1.0000 18.500 1.0957 0.16064 0.15801 -0.0458 0.0131 1.0000