XFOIL Version 6.94 Calculated polar for: NACA 63(2)-615 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.080 Re = 0.300 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- 0.000 0.4895 0.01097 0.00519 -0.1110 0.6836 0.6681 0.500 0.5452 0.01107 0.00528 -0.1109 0.6724 0.6828 1.000 0.6028 0.01129 0.00539 -0.1113 0.6588 0.6946 1.500 0.6586 0.01142 0.00558 -0.1116 0.6470 0.7084 2.000 0.7118 0.01150 0.00577 -0.1112 0.6381 0.7227 2.500 0.7664 0.01162 0.00591 -0.1110 0.6270 0.7369 3.000 0.8224 0.01180 0.00602 -0.1111 0.6137 0.7482 3.500 0.8749 0.01220 0.00651 -0.1106 0.5997 0.7679 4.000 0.9251 0.01223 0.00669 -0.1095 0.5906 0.7836 4.500 0.9775 0.01229 0.00679 -0.1089 0.5763 0.7970 5.000 1.0274 0.01240 0.00680 -0.1076 0.5501 0.8158 5.500 1.0666 0.01210 0.00659 -0.1040 0.5230 0.8344 6.000 1.1054 0.01230 0.00670 -0.1006 0.4871 0.8532 6.500 1.1314 0.01251 0.00718 -0.0946 0.4569 0.8800 7.000 1.1562 0.01281 0.00757 -0.0888 0.4236 0.9065 7.500 1.1523 0.01305 0.00774 -0.0776 0.3892 0.9779 8.000 1.1743 0.01443 0.00885 -0.0735 0.3207 1.0000 8.500 1.1701 0.01649 0.01057 -0.0654 0.2551 1.0000 9.000 1.1607 0.01900 0.01277 -0.0576 0.1926 1.0000 9.500 1.1531 0.02186 0.01538 -0.0509 0.1400 1.0000 10.000 1.1448 0.02518 0.01855 -0.0450 0.0920 1.0000 10.500 1.1309 0.02923 0.02232 -0.0396 0.0565 1.0000 11.000 1.1216 0.03355 0.02654 -0.0353 0.0327 1.0000 11.500 1.1037 0.03912 0.03239 -0.0311 0.0240 1.0000 12.000 1.0942 0.04453 0.03814 -0.0280 0.0218 1.0000 12.500 1.1037 0.04876 0.04259 -0.0260 0.0208 1.0000 13.000 1.1201 0.05235 0.04633 -0.0253 0.0203 1.0000 13.500 1.1375 0.05599 0.05010 -0.0248 0.0195 1.0000 14.000 1.1536 0.05996 0.05424 -0.0245 0.0186 1.0000 14.500 1.1646 0.06466 0.05912 -0.0246 0.0176 1.0000 15.000 1.1737 0.06988 0.06456 -0.0250 0.0169 1.0000 15.500 1.1792 0.07600 0.07107 -0.0258 0.0167 1.0000 16.000 1.1737 0.08400 0.07939 -0.0277 0.0166 1.0000 16.500 1.1639 0.09298 0.08872 -0.0305 0.0164 1.0000 17.000 1.1428 0.10415 0.10024 -0.0351 0.0164 1.0000 17.500 1.1133 0.11744 0.11388 -0.0416 0.0164 1.0000 18.000 1.0722 0.13407 0.13089 -0.0508 0.0166 1.0000 19.000 0.9233 0.19363 0.19086 -0.0831 0.0179 1.0000 19.500 0.9129 0.20724 0.20443 -0.0893 0.0182 1.0000 20.000 0.9120 0.21707 0.21423 -0.0940 0.0183 1.0000 20.500 0.9150 0.22565 0.22279 -0.0982 0.0183 1.0000 21.000 0.9204 0.23359 0.23070 -0.1021 0.0182 1.0000 21.500 0.9274 0.24105 0.23816 -0.1057 0.0178 1.0000 22.000 0.9352 0.24827 0.24536 -0.1093 0.0168 1.0000 22.500 0.9428 0.25546 0.25253 -0.1129 0.0152 1.0000 23.000 0.9508 0.26218 0.25924 -0.1164 0.0132 1.0000 23.500 0.9574 0.26992 0.26704 -0.1198 0.0126 1.0000