XFOIL Version 6.96 Calculated polar for: GOE 429 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -14.750 -1.0715 0.09481 0.09077 0.0150 1.0000 0.0323 -14.500 -1.1002 0.08558 0.08136 0.0090 1.0000 0.0320 -14.250 -1.1262 0.07730 0.07288 0.0035 1.0000 0.0319 -14.000 -1.1492 0.07001 0.06535 -0.0013 1.0000 0.0319 -13.750 -1.1692 0.06368 0.05877 -0.0051 1.0000 0.0319 -13.500 -1.1859 0.05824 0.05306 -0.0081 1.0000 0.0320 -13.250 -1.1999 0.05356 0.04811 -0.0102 1.0000 0.0322 -13.000 -1.2111 0.04966 0.04391 -0.0114 1.0000 0.0324 -12.750 -1.2143 0.04596 0.04007 -0.0113 1.0000 0.0330 -12.500 -1.2109 0.04349 0.03753 -0.0108 1.0000 0.0336 -12.250 -1.2068 0.04145 0.03540 -0.0098 1.0000 0.0344 -12.000 -1.1998 0.03945 0.03326 -0.0089 1.0000 0.0352 -11.750 -1.1906 0.03739 0.03100 -0.0080 1.0000 0.0364 -11.500 -1.1793 0.03544 0.02879 -0.0072 1.0000 0.0378 -11.250 -1.1664 0.03331 0.02648 -0.0063 1.0000 0.0394 -11.000 -1.1492 0.03201 0.02522 -0.0058 1.0000 0.0413 -10.750 -1.1314 0.03069 0.02375 -0.0052 1.0000 0.0437 -10.500 -1.1136 0.02900 0.02185 -0.0044 1.0000 0.0463 -10.250 -1.0942 0.02774 0.02064 -0.0040 1.0000 0.0493 -10.000 -1.0729 0.02679 0.01947 -0.0035 1.0000 0.0538 -9.750 -1.0524 0.02559 0.01835 -0.0031 1.0000 0.0586 -9.500 -1.0304 0.02455 0.01715 -0.0026 1.0000 0.0649 -9.250 -1.0073 0.02383 0.01644 -0.0024 1.0000 0.0709 -9.000 -0.9842 0.02286 0.01539 -0.0021 1.0000 0.0774 -8.750 -0.9596 0.02230 0.01474 -0.0020 1.0000 0.0839 -8.500 -0.9357 0.02129 0.01369 -0.0017 1.0000 0.0899 -8.250 -0.9105 0.02065 0.01301 -0.0016 1.0000 0.0963 -8.000 -0.8858 0.01971 0.01203 -0.0013 1.0000 0.1026 -7.750 -0.8604 0.01904 0.01134 -0.0012 1.0000 0.1097 -7.500 -0.8352 0.01815 0.01045 -0.0011 1.0000 0.1170 -7.250 -0.8092 0.01748 0.00976 -0.0010 1.0000 0.1245 -7.000 -0.7837 0.01661 0.00894 -0.0008 1.0000 0.1319 -6.750 -0.7570 0.01600 0.00830 -0.0007 1.0000 0.1405 -6.500 -0.7309 0.01527 0.00767 -0.0007 1.0000 0.1509 -6.250 -0.7040 0.01465 0.00714 -0.0007 1.0000 0.1648 -6.000 -0.6767 0.01408 0.00664 -0.0007 1.0000 0.1854 -5.750 -0.6497 0.01344 0.00616 -0.0008 1.0000 0.2166 -5.500 -0.6226 0.01285 0.00574 -0.0010 1.0000 0.2513 -5.250 -0.5948 0.01241 0.00540 -0.0012 1.0000 0.2812 -5.000 -0.5667 0.01205 0.00513 -0.0013 1.0000 0.3082 -4.750 -0.5384 0.01172 0.00491 -0.0015 1.0000 0.3326 -4.500 -0.5096 0.01145 0.00469 -0.0018 1.0000 0.3570 -4.250 -0.4810 0.01117 0.00452 -0.0020 1.0000 0.3812 -4.000 -0.4519 0.01094 0.00436 -0.0024 1.0000 0.4064 -3.750 -0.4228 0.01070 0.00423 -0.0028 1.0000 0.4305 -3.500 -0.3934 0.01050 0.00413 -0.0033 1.0000 0.4556 -3.250 -0.3647 0.01032 0.00407 -0.0038 1.0000 0.4803 -3.000 -0.3331 0.01020 0.00405 -0.0051 0.9913 0.5052 -2.750 -0.2903 0.01011 0.00404 -0.0080 0.9679 0.5325 -2.500 -0.2547 0.01008 0.00409 -0.0093 0.9444 0.5561 -2.250 -0.2274 0.01014 0.00419 -0.0086 0.9219 0.5778 -2.000 -0.2034 0.01023 0.00427 -0.0072 0.9006 0.5990 -1.750 -0.1803 0.01031 0.00436 -0.0055 0.8809 0.6174 -1.500 -0.1567 0.01037 0.00441 -0.0040 0.8622 0.6343 -1.250 -0.1320 0.01041 0.00442 -0.0027 0.8447 0.6505 -1.000 -0.1062 0.01044 0.00442 -0.0017 0.8284 0.6661 -0.750 -0.0801 0.01046 0.00441 -0.0009 0.8126 0.6815 -0.500 -0.0536 0.01046 0.00440 -0.0001 0.7967 0.6966 -0.250 -0.0273 0.01045 0.00438 0.0007 0.7806 0.7113 0.000 -0.0011 0.01043 0.00435 0.0016 0.7638 0.7258 0.250 0.0250 0.01041 0.00432 0.0026 0.7464 0.7401 0.500 0.0516 0.01036 0.00428 0.0033 0.7274 0.7543 0.750 0.0781 0.01031 0.00425 0.0041 0.7081 0.7697 1.000 0.1041 0.01026 0.00423 0.0051 0.6886 0.7877 1.250 0.1299 0.01020 0.00419 0.0061 0.6684 0.8065 1.500 0.1558 0.01013 0.00414 0.0070 0.6464 0.8242 1.750 0.1816 0.01003 0.00408 0.0080 0.6196 0.8411 2.000 0.2071 0.00996 0.00401 0.0090 0.5876 0.8580 2.250 0.2317 0.00992 0.00393 0.0102 0.5473 0.8765 2.500 0.2563 0.00997 0.00387 0.0114 0.4957 0.8986 2.750 0.2833 0.01019 0.00388 0.0119 0.4396 0.9265 3.000 0.3186 0.01055 0.00400 0.0104 0.3844 0.9605 3.250 0.3585 0.01097 0.00418 0.0075 0.3365 1.0000 3.500 0.3875 0.01137 0.00436 0.0067 0.3045 1.0000 3.750 0.4166 0.01175 0.00457 0.0061 0.2803 1.0000 4.000 0.4455 0.01213 0.00481 0.0056 0.2620 1.0000 4.250 0.4743 0.01247 0.00507 0.0053 0.2472 1.0000 4.500 0.5030 0.01279 0.00534 0.0050 0.2342 1.0000 4.750 0.5315 0.01311 0.00562 0.0047 0.2226 1.0000 5.000 0.5597 0.01345 0.00590 0.0045 0.2121 1.0000 5.250 0.5882 0.01369 0.00617 0.0044 0.2016 1.0000 5.500 0.6165 0.01392 0.00643 0.0042 0.1901 1.0000 5.750 0.6449 0.01412 0.00664 0.0041 0.1747 1.0000 6.000 0.6731 0.01437 0.00684 0.0039 0.1545 1.0000 6.250 0.7008 0.01477 0.00715 0.0039 0.1241 1.0000 6.500 0.7278 0.01544 0.00764 0.0038 0.0902 1.0000 6.750 0.7541 0.01619 0.00826 0.0039 0.0772 1.0000 7.000 0.7803 0.01693 0.00899 0.0039 0.0715 1.0000 7.250 0.8059 0.01774 0.00980 0.0041 0.0676 1.0000 7.500 0.8301 0.01880 0.01083 0.0043 0.0649 1.0000 7.750 0.8551 0.01966 0.01175 0.0046 0.0634 1.0000 8.000 0.8797 0.02058 0.01275 0.0049 0.0617 1.0000 8.250 0.9038 0.02158 0.01379 0.0053 0.0599 1.0000 8.500 0.9273 0.02269 0.01491 0.0056 0.0581 1.0000 8.750 0.9504 0.02404 0.01625 0.0061 0.0568 1.0000 9.000 0.9729 0.02587 0.01809 0.0066 0.0555 1.0000 9.250 0.9959 0.02744 0.01980 0.0070 0.0546 1.0000 9.500 1.0188 0.02868 0.02123 0.0075 0.0535 1.0000 9.750 1.0407 0.03018 0.02293 0.0080 0.0524 1.0000 10.000 1.0615 0.03192 0.02488 0.0085 0.0515 1.0000 10.250 1.0810 0.03374 0.02690 0.0090 0.0505 1.0000 10.500 1.0999 0.03560 0.02889 0.0095 0.0492 1.0000 10.750 1.1172 0.03771 0.03113 0.0099 0.0481 1.0000 11.000 1.1322 0.04051 0.03407 0.0104 0.0472 1.0000 11.250 1.1421 0.04427 0.03809 0.0109 0.0467 1.0000 11.500 1.1432 0.04915 0.04333 0.0114 0.0462 1.0000 11.750 1.1402 0.05190 0.04644 0.0123 0.0459 1.0000 12.000 1.1316 0.05495 0.04983 0.0131 0.0456 1.0000 12.250 1.1143 0.05844 0.05358 0.0136 0.0455 1.0000 12.500 1.0938 0.06303 0.05840 0.0121 0.0455 1.0000 12.750 1.0709 0.06884 0.06443 0.0089 0.0457 1.0000 13.000 1.0459 0.07594 0.07171 0.0046 0.0459 1.0000