XFOIL Version 6.96 Calculated polar for: MB253515 15.0% smoothed 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 ------ -------- --------- --------- -------- -------- -------- -12.250 -0.4386 0.10042 0.09685 -0.0490 1.0000 0.0172 -12.000 -0.5743 0.06367 0.05982 -0.0712 1.0000 0.0158 -11.750 -0.6016 0.05781 0.05379 -0.0739 1.0000 0.0158 -11.500 -0.6259 0.05334 0.04914 -0.0744 1.0000 0.0157 -11.250 -0.6464 0.05007 0.04574 -0.0733 1.0000 0.0158 -11.000 -0.6619 0.04781 0.04340 -0.0709 1.0000 0.0159 -10.750 -0.6803 0.04584 0.04132 -0.0671 1.0000 0.0160 -10.500 -0.6849 0.04486 0.04032 -0.0643 0.9943 0.0162 -10.250 -0.6742 0.04267 0.03795 -0.0651 0.9775 0.0166 -10.000 -0.6554 0.04086 0.03594 -0.0666 0.9643 0.0173 -9.750 -0.6385 0.03856 0.03337 -0.0676 0.9508 0.0182 -9.500 -0.6236 0.03544 0.02981 -0.0679 0.9374 0.0193 -9.250 -0.6081 0.03207 0.02583 -0.0677 0.9245 0.0205 -9.000 -0.5875 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0.01113 0.00407 -0.0350 0.6328 0.8589 1.000 0.3195 0.01118 0.00413 -0.0348 0.6259 0.8712 1.250 0.3503 0.01125 0.00418 -0.0354 0.6195 0.8814 1.500 0.3810 0.01133 0.00425 -0.0360 0.6128 0.8912 1.750 0.4095 0.01140 0.00430 -0.0362 0.6058 0.9016 2.000 0.4436 0.01149 0.00439 -0.0376 0.5985 0.9085 2.250 0.4732 0.01157 0.00445 -0.0381 0.5909 0.9176 2.500 0.5079 0.01168 0.00456 -0.0397 0.5833 0.9236 2.750 0.5376 0.01177 0.00463 -0.0402 0.5751 0.9322 3.000 0.5732 0.01188 0.00476 -0.0420 0.5660 0.9372 3.250 0.6043 0.01199 0.00484 -0.0429 0.5577 0.9446 3.500 0.6385 0.01210 0.00498 -0.0444 0.5475 0.9498 3.750 0.6726 0.01223 0.00511 -0.0460 0.5372 0.9550 4.000 0.7029 0.01236 0.00523 -0.0468 0.5268 0.9619 4.250 0.7376 0.01250 0.00539 -0.0485 0.5150 0.9664 4.500 0.7674 0.01266 0.00556 -0.0492 0.5027 0.9735 4.750 0.8020 0.01282 0.00573 -0.0510 0.4896 0.9779 5.000 0.8332 0.01300 0.00594 -0.0521 0.4768 0.9842 5.250 0.8669 0.01320 0.00613 -0.0538 0.4631 0.9889 5.500 0.8990 0.01343 0.00637 -0.0552 0.4490 0.9943 5.750 0.9327 0.01366 0.00662 -0.0570 0.4356 0.9992 6.000 0.9497 0.01390 0.00686 -0.0552 0.4246 1.0000 6.250 0.9633 0.01413 0.00711 -0.0528 0.4138 1.0000 6.500 0.9757 0.01440 0.00737 -0.0501 0.4012 1.0000 6.750 0.9853 0.01475 0.00765 -0.0469 0.3842 1.0000 7.000 0.9929 0.01515 0.00795 -0.0434 0.3651 1.0000 7.250 1.0007 0.01556 0.00832 -0.0399 0.3449 1.0000 7.500 1.0082 0.01600 0.00869 -0.0364 0.3266 1.0000 7.750 1.0152 0.01646 0.00910 -0.0329 0.3092 1.0000 8.000 1.0198 0.01693 0.00952 -0.0289 0.2916 1.0000 8.250 1.0225 0.01740 0.00996 -0.0246 0.2703 1.0000 8.500 1.0224 0.01806 0.01051 -0.0201 0.2422 1.0000 8.750 1.0162 0.01912 0.01132 -0.0151 0.1980 1.0000 9.000 0.9939 0.02125 0.01289 -0.0088 0.1160 1.0000 9.250 0.9757 0.02360 0.01485 -0.0038 0.0571 1.0000 9.500 0.9746 0.02518 0.01636 -0.0010 0.0401 1.0000 9.750 0.9771 0.02664 0.01785 0.0013 0.0321 1.0000 10.000 0.9829 0.02795 0.01924 0.0031 0.0279 1.0000 10.250 0.9864 0.02950 0.02085 0.0049 0.0254 1.0000 10.500 0.9892 0.03116 0.02261 0.0065 0.0235 1.0000 10.750 0.9937 0.03278 0.02434 0.0079 0.0221 1.0000 11.000 0.9976 0.03449 0.02614 0.0091 0.0203 1.0000 11.250 0.9993 0.03645 0.02818 0.0102 0.0191 1.0000 11.500 0.9957 0.03895 0.03076 0.0114 0.0181 1.0000 11.750 0.9954 0.04125 0.03315 0.0123 0.0178 1.0000 12.000 0.9954 0.04360 0.03562 0.0131 0.0173 1.0000 12.250 0.9951 0.04607 0.03822 0.0138 0.0167 1.0000 12.500 0.9951 0.04859 0.04084 0.0143 0.0163 1.0000 12.750 0.9952 0.05116 0.04350 0.0147 0.0158 1.0000 13.000 0.9957 0.05373 0.04616 0.0151 0.0154 1.0000 13.250 0.9982 0.05618 0.04868 0.0152 0.0145 1.0000 13.500 0.9995 0.05876 0.05133 0.0154 0.0143 1.0000 13.750 1.0010 0.06140 0.05401 0.0154 0.0136 1.0000 14.000 1.0022 0.06403 0.05670 0.0156 0.0132 1.0000 14.250 1.0036 0.06655 0.05926 0.0160 0.0128 1.0000 14.500 1.0087 0.06873 0.06151 0.0164 0.0125 1.0000 14.750 1.0143 0.07095 0.06386 0.0166 0.0122 1.0000 15.000 1.0205 0.07310 0.06611 0.0169 0.0120 1.0000 15.250 1.0267 0.07526 0.06839 0.0172 0.0117 1.0000 15.500 1.0322 0.07760 0.07085 0.0174 0.0114 1.0000 15.750 1.0372 0.08003 0.07341 0.0175 0.0112 1.0000 16.000 1.0409 0.08270 0.07621 0.0175 0.0110 1.0000 16.250 1.0421 0.08579 0.07944 0.0169 0.0106 1.0000 16.500 1.0423 0.08910 0.08289 0.0161 0.0103 1.0000 16.750 1.0431 0.09237 0.08631 0.0156 0.0103 1.0000 17.000 1.0409 0.09612 0.09019 0.0143 0.0100 1.0000 17.250 1.0381 0.10002 0.09423 0.0130 0.0098 1.0000 17.500 1.0364 0.10375 0.09800 0.0113 0.0094 1.0000 17.750 1.0314 0.10821 0.10267 0.0099 0.0094 1.0000 18.000 1.0276 0.11244 0.10700 0.0081 0.0093 1.0000 18.250 1.0210 0.11725 0.11195 0.0061 0.0091 1.0000 18.500 1.0132 0.12239 0.11724 0.0038 0.0090 1.0000 18.750 1.0039 0.12805 0.12307 0.0010 0.0090 1.0000 19.000 0.9921 0.13435 0.12955 -0.0023 0.0090 1.0000 19.250 0.9794 0.14107 0.13645 -0.0060 0.0090 1.0000