XFOIL Version 6.94 Calculated polar for: OAF095 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.080 Re = 0.450 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- 0.000 0.5301 0.00824 0.00258 -0.1281 0.7749 0.4159 0.500 0.5884 0.00823 0.00263 -0.1281 0.7555 0.4491 1.000 0.6466 0.00823 0.00271 -0.1282 0.7360 0.4853 1.500 0.7042 0.00826 0.00279 -0.1281 0.7103 0.5284 2.000 0.7622 0.00821 0.00293 -0.1282 0.6833 0.5920 2.500 0.8170 0.00785 0.00316 -0.1275 0.6515 0.8019 3.000 0.8663 0.00776 0.00316 -0.1254 0.6167 1.0000 3.500 0.9231 0.00812 0.00339 -0.1253 0.5732 1.0000 4.000 0.9785 0.00866 0.00369 -0.1250 0.5128 1.0000 4.500 1.0311 0.00965 0.00421 -0.1244 0.4038 1.0000 5.000 1.0775 0.01168 0.00529 -0.1235 0.2284 1.0000 5.500 1.1245 0.01344 0.00643 -0.1225 0.1207 1.0000 6.000 1.1722 0.01492 0.00759 -0.1213 0.0729 1.0000 6.500 1.2203 0.01620 0.00877 -0.1200 0.0546 1.0000 7.000 1.2670 0.01750 0.01006 -0.1185 0.0445 1.0000 7.500 1.3115 0.01891 0.01149 -0.1166 0.0382 1.0000 8.000 1.3537 0.02042 0.01305 -0.1144 0.0334 1.0000 8.500 1.3928 0.02210 0.01482 -0.1118 0.0300 1.0000 9.000 1.4274 0.02407 0.01688 -0.1085 0.0274 1.0000 9.500 1.4595 0.02600 0.01886 -0.1051 0.0250 1.0000 10.000 1.4869 0.02811 0.02120 -0.1008 0.0232 1.0000 10.500 1.5076 0.03034 0.02353 -0.0959 0.0218 1.0000 11.000 1.5252 0.03345 0.02683 -0.0912 0.0207 1.0000 11.500 1.5428 0.03651 0.03017 -0.0869 0.0196 1.0000 12.000 1.5577 0.03984 0.03371 -0.0830 0.0188 1.0000 12.500 1.5694 0.04421 0.03819 -0.0793 0.0179 1.0000 13.000 1.5693 0.04904 0.04350 -0.0758 0.0173 1.0000 13.500 1.5647 0.05488 0.04975 -0.0731 0.0167 1.0000 14.000 1.5554 0.06161 0.05684 -0.0714 0.0162 1.0000 14.500 1.5411 0.06935 0.06490 -0.0709 0.0159 1.0000 15.000 1.5199 0.07865 0.07454 -0.0721 0.0156 1.0000 15.500 1.4930 0.08978 0.08602 -0.0752 0.0155 1.0000 16.000 1.4589 0.10346 0.10008 -0.0811 0.0154 1.0000 16.500 1.4108 0.12191 0.11898 -0.0916 0.0154 1.0000 17.000 0.8508 0.20177 0.19987 -0.1122 0.0288 1.0000 17.500 0.8352 0.21380 0.21189 -0.1181 0.0267 1.0000 18.000 0.8408 0.21941 0.21751 -0.1198 0.0253 1.0000 19.000 0.8413 0.23505 0.23317 -0.1257 0.0226 1.0000 19.500 0.8475 0.24062 0.23876 -0.1273 0.0217 1.0000 20.000 0.8559 0.24626 0.24441 -0.1282 0.0211 1.0000 20.500 0.8517 0.25587 0.25403 -0.1328 0.0190 1.0000 21.000 0.8584 0.26128 0.25946 -0.1343 0.0182 1.0000 21.500 0.8608 0.26907 0.26726 -0.1368 0.0177 1.0000 22.000 0.8630 0.27722 0.27542 -0.1397 0.0159 1.0000 22.500 0.8697 0.28249 0.28071 -0.1412 0.0151 1.0000 23.000 0.8710 0.29135 0.28958 -0.1441 0.0146 1.0000 23.500 0.8748 0.29886 0.29711 -0.1465 0.0130 1.0000 24.000 0.8800 0.30465 0.30291 -0.1483 0.0123 1.0000 24.500 0.8844 0.31161 0.30989 -0.1501 0.0121 1.0000 25.000 0.8859 0.32102 0.31931 -0.1533 0.0111 1.0000 25.500 0.8897 0.32798 0.32628 -0.1554 0.0103 1.0000 26.000 0.8937 0.33428 0.33261 -0.1574 0.0098 1.0000 27.000 0.8996 0.34941 0.34776 -0.1619 0.0094 1.0000 27.500 0.9025 0.35760 0.35597 -0.1643 0.0085 1.0000 28.000 0.9055 0.36451 0.36291 -0.1664 0.0078 1.0000 28.500 0.9083 0.37084 0.36926 -0.1685 0.0074 1.0000 29.500 0.9123 0.38687 0.38532 -0.1729 0.0070 1.0000 30.000 0.9145 0.39470 0.39317 -0.1751 0.0064 1.0000 30.500 0.9163 0.40186 0.40035 -0.1772 0.0059 1.0000 31.000 0.9179 0.40868 0.40719 -0.1794 0.0056 1.0000 31.500 0.9191 0.41511 0.41365 -0.1815 0.0053 1.0000 32.500 0.9205 0.42952 0.42810 -0.1856 0.0052 1.0000 33.000 0.9213 0.43777 0.43637 -0.1879 0.0050 1.0000 33.500 0.9220 0.44536 0.44398 -0.1899 0.0046 1.0000 34.000 0.9221 0.45237 0.45101 -0.1920 0.0041 1.0000 34.500 0.9220 0.45901 0.45768 -0.1941 0.0038 1.0000 35.000 0.9214 0.46516 0.46386 -0.1962 0.0036 1.0000 35.500 0.9202 0.47097 0.46970 -0.1981 0.0034 1.0000 36.500 0.9181 0.48573 0.48449 -0.2023 0.0034 1.0000 37.000 0.9170 0.49284 0.49162 -0.2044 0.0033 1.0000 37.500 0.9157 0.49970 0.49850 -0.2064 0.0033 1.0000 38.000 0.9140 0.50627 0.50511 -0.2083 0.0030 1.0000 38.500 0.9119 0.51248 0.51134 -0.2103 0.0027 1.0000 39.000 0.9096 0.51846 0.51734 -0.2123 0.0025 1.0000 39.500 0.9068 0.52412 0.52303 -0.2143 0.0023 1.0000 40.000 0.9038 0.52941 0.52835 -0.2163 0.0021 1.0000 40.500 0.9000 0.53420 0.53316 -0.2183 0.0020 1.0000 41.500 0.8930 0.54623 0.54523 -0.2220 0.0019 1.0000 42.000 0.8895 0.55213 0.55116 -0.2239 0.0019 1.0000 42.500 0.8857 0.55764 0.55669 -0.2257 0.0019 1.0000 43.000 0.8817 0.56292 0.56200 -0.2275 0.0018 1.0000 43.500 0.8773 0.56787 0.56697 -0.2293 0.0017 1.0000 44.000 0.8726 0.57250 0.57163 -0.2311 0.0015 1.0000 44.500 0.8677 0.57691 0.57607 -0.2329 0.0013 1.0000 45.000 0.8624 0.58096 0.58013 -0.2347 0.0012 1.0000 45.500 0.8569 0.58463 0.58383 -0.2365 0.0010 1.0000 46.000 0.8510 0.58790 0.58713 -0.2383 0.0010 1.0000 46.500 0.8443 0.59062 0.58987 -0.2401 0.0009 1.0000 48.000 0.8263 0.60222 0.60154 -0.2450 0.0009 1.0000 48.500 0.8200 0.60547 0.60482 -0.2465 0.0008 1.0000 49.000 0.8134 0.60841 0.60778 -0.2481 0.0008 1.0000 49.500 0.8066 0.61107 0.61046 -0.2496 0.0008 1.0000 50.000 0.7995 0.61342 0.61284 -0.2511 0.0007 1.0000 50.500 0.7922 0.61541 0.61485 -0.2526 0.0006 1.0000 51.000 0.7846 0.61704 0.61650 -0.2542 0.0005 1.0000 51.500 0.7769 0.61829 0.61778 -0.2557 0.0004 1.0000 52.000 0.7689 0.61913 0.61863 -0.2572 0.0003 1.0000 52.500 0.7606 0.61957 0.61910 -0.2588 0.0003 1.0000 53.000 0.7517 0.61947 0.61903 -0.2603 0.0003 1.0000 54.000 0.7358 0.62240 0.62199 -0.2628 0.0002 1.0000 54.500 0.7274 0.62288 0.62249 -0.2641 0.0002 1.0000 55.000 0.7187 0.62284 0.62247 -0.2654 0.0001 1.0000 55.500 0.7097 0.62223 0.62188 -0.2667 0.0001 1.0000 57.000 0.6824 0.62027 0.61998 -0.2703 0.0001 1.0000 57.500 0.6731 0.61921 0.61893 -0.2715 0.0000 1.0000 58.000 0.6636 0.61780 0.61755 -0.2726 0.0000 1.0000 58.500 0.6540 0.61594 0.61571 -0.2738 0.0000 1.0000 59.000 0.6441 0.61349 0.61327 -0.2750 0.0000 1.0000