XFOIL Version 6.96 Calculated polar for: OAF128 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -10.750 -0.7864 0.08688 0.07931 0.0045 1.0000 0.0756 -10.500 -0.8701 0.06649 0.05852 -0.0132 1.0000 0.0732 -10.250 -0.8916 0.05996 0.05171 -0.0177 1.0000 0.0737 -10.000 -0.8965 0.05521 0.04664 -0.0200 1.0000 0.0753 -9.750 -0.8955 0.05072 0.04174 -0.0217 1.0000 0.0773 -9.500 -0.8858 0.04723 0.03792 -0.0226 1.0000 0.0797 -9.250 -0.8683 0.04535 0.03603 -0.0227 1.0000 0.0830 -9.000 -0.8529 0.04247 0.03276 -0.0234 1.0000 0.0875 -8.750 -0.8331 0.04058 0.03085 -0.0236 1.0000 0.0917 -8.500 -0.8130 0.03836 0.02836 -0.0240 1.0000 0.0980 -8.250 -0.7913 0.03676 0.02678 -0.0242 1.0000 0.1045 -8.000 -0.7688 0.03492 0.02479 -0.0245 1.0000 0.1132 -7.750 -0.7453 0.03327 0.02300 -0.0249 1.0000 0.1240 -7.500 -0.7209 0.03189 0.02156 -0.0253 1.0000 0.1365 -7.250 -0.6958 0.03071 0.02036 -0.0257 1.0000 0.1505 -7.000 -0.6699 0.02971 0.01936 -0.0262 1.0000 0.1659 -6.750 -0.6435 0.02882 0.01847 -0.0266 1.0000 0.1826 -6.500 -0.6167 0.02798 0.01762 -0.0270 1.0000 0.2002 -6.250 -0.5895 0.02722 0.01688 -0.0274 1.0000 0.2178 -6.000 -0.5620 0.02654 0.01623 -0.0277 1.0000 0.2349 -5.750 -0.5340 0.02588 0.01556 -0.0280 1.0000 0.2517 -5.500 -0.5057 0.02524 0.01491 -0.0282 1.0000 0.2685 -5.250 -0.4772 0.02465 0.01431 -0.0285 1.0000 0.2853 -5.000 -0.4486 0.02409 0.01374 -0.0288 1.0000 0.3022 -4.750 -0.4198 0.02359 0.01324 -0.0291 1.0000 0.3195 -4.500 -0.3909 0.02311 0.01277 -0.0294 1.0000 0.3369 -4.250 -0.3621 0.02268 0.01236 -0.0297 1.0000 0.3548 -4.000 -0.3332 0.02227 0.01198 -0.0301 1.0000 0.3728 -3.750 -0.3047 0.02191 0.01165 -0.0303 1.0000 0.3911 -3.500 -0.2762 0.02158 0.01138 -0.0306 1.0000 0.4097 -3.250 -0.2481 0.02128 0.01116 -0.0310 1.0000 0.4287 -3.000 -0.2208 0.02103 0.01099 -0.0312 1.0000 0.4478 -2.750 -0.1953 0.02082 0.01089 -0.0314 1.0000 0.4662 -2.500 -0.1524 0.02069 0.01078 -0.0345 0.9617 0.4879 -2.250 -0.1106 0.02055 0.01063 -0.0370 0.9287 0.5082 -2.000 -0.0751 0.02047 0.01053 -0.0380 0.8970 0.5272 -1.750 -0.0450 0.02044 0.01046 -0.0378 0.8672 0.5455 -1.500 -0.0180 0.02043 0.01041 -0.0370 0.8395 0.5634 -1.250 0.0076 0.02042 0.01036 -0.0358 0.8140 0.5820 -1.000 0.0327 0.02040 0.01034 -0.0345 0.7897 0.6021 -0.750 0.0574 0.02039 0.01033 -0.0331 0.7675 0.6238 -0.500 0.0820 0.02037 0.01032 -0.0317 0.7467 0.6474 -0.250 0.1071 0.02036 0.01030 -0.0305 0.7271 0.6723 0.000 0.1312 0.02033 0.01032 -0.0290 0.7086 0.6963 0.250 0.1556 0.02031 0.01033 -0.0275 0.6908 0.7226 0.500 0.1795 0.02028 0.01034 -0.0260 0.6738 0.7520 0.750 0.2027 0.02024 0.01034 -0.0242 0.6575 0.7859 1.000 0.2245 0.02015 0.01030 -0.0221 0.6416 0.8250 1.250 0.2474 0.02001 0.01017 -0.0202 0.6260 0.8746 1.500 0.2794 0.01986 0.01002 -0.0203 0.6086 0.9481 1.750 0.3143 0.01997 0.01000 -0.0219 0.5909 1.0000 2.000 0.3455 0.02027 0.01016 -0.0229 0.5746 1.0000 2.250 0.3761 0.02059 0.01036 -0.0235 0.5592 1.0000 2.500 0.4061 0.02092 0.01058 -0.0239 0.5445 1.0000 2.750 0.4355 0.02125 0.01078 -0.0241 0.5311 1.0000 3.000 0.4651 0.02162 0.01110 -0.0245 0.5161 1.0000 3.250 0.4947 0.02202 0.01147 -0.0248 0.5012 1.0000 3.500 0.5239 0.02242 0.01183 -0.0251 0.4871 1.0000 3.750 0.5527 0.02281 0.01215 -0.0251 0.4734 1.0000 4.000 0.5815 0.02321 0.01252 -0.0251 0.4591 1.0000 4.250 0.6102 0.02366 0.01298 -0.0253 0.4435 1.0000 4.500 0.6386 0.02409 0.01342 -0.0254 0.4277 1.0000 4.750 0.6665 0.02449 0.01380 -0.0253 0.4109 1.0000 5.000 0.6942 0.02486 0.01414 -0.0252 0.3932 1.0000 5.250 0.7216 0.02523 0.01450 -0.0251 0.3750 1.0000 5.500 0.7488 0.02562 0.01489 -0.0250 0.3566 1.0000 5.750 0.7758 0.02606 0.01532 -0.0249 0.3384 1.0000 6.000 0.8025 0.02654 0.01580 -0.0247 0.3202 1.0000 6.250 0.8288 0.02706 0.01631 -0.0246 0.3019 1.0000 6.500 0.8546 0.02765 0.01689 -0.0245 0.2835 1.0000 6.750 0.8799 0.02832 0.01752 -0.0243 0.2652 1.0000 7.000 0.9047 0.02911 0.01829 -0.0241 0.2471 1.0000 7.250 0.9288 0.03003 0.01920 -0.0240 0.2297 1.0000 7.500 0.9522 0.03105 0.02017 -0.0237 0.2142 1.0000 7.750 0.9750 0.03215 0.02124 -0.0235 0.2001 1.0000 8.000 0.9974 0.03341 0.02259 -0.0232 0.1870 1.0000 8.250 1.0192 0.03473 0.02400 -0.0230 0.1759 1.0000 8.500 1.0405 0.03600 0.02522 -0.0226 0.1671 1.0000 8.750 1.0610 0.03744 0.02679 -0.0222 0.1586 1.0000 9.000 1.0810 0.03891 0.02831 -0.0218 0.1517 1.0000 9.250 1.1000 0.04049 0.03002 -0.0213 0.1451 1.0000 9.500 1.1194 0.04197 0.03146 -0.0208 0.1399 1.0000 9.750 1.1349 0.04403 0.03382 -0.0203 0.1343 1.0000 10.000 1.1523 0.04563 0.03545 -0.0198 0.1298 1.0000 10.250 1.1674 0.04767 0.03760 -0.0192 0.1259 1.0000 10.500 1.1762 0.05030 0.04056 -0.0187 0.1219 1.0000 10.750 1.1873 0.05245 0.04284 -0.0180 0.1184 1.0000 11.000 1.2054 0.05400 0.04429 -0.0174 0.1154 1.0000 11.250 1.1993 0.05783 0.04854 -0.0169 0.1130 1.0000 11.500 1.1853 0.06194 0.05299 -0.0164 0.1111 1.0000 11.750 1.1660 0.06693 0.05827 -0.0174 0.1097 1.0000 12.000 1.1386 0.07377 0.06539 -0.0205 0.1086 1.0000 12.250 1.0564 0.09130 0.08334 -0.0325 0.1095 1.0000