XFOIL Version 6.94 Calculated polar for: GOE 55 AIRFOIL 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 0.1838 0.01235 0.00344 -0.0284 0.4014 0.0782 0.500 0.2424 0.01188 0.00315 -0.0287 0.3831 0.1489 1.000 0.2909 0.00955 0.00302 -0.0269 0.3599 1.0000 1.500 0.3485 0.00979 0.00306 -0.0267 0.3414 1.0000 2.000 0.4059 0.01007 0.00319 -0.0265 0.3267 1.0000 2.500 0.4632 0.01028 0.00328 -0.0263 0.3076 1.0000 3.000 0.5205 0.01044 0.00342 -0.0261 0.2867 1.0000 3.500 0.5779 0.01057 0.00352 -0.0259 0.2536 1.0000 4.000 0.6342 0.01131 0.00377 -0.0259 0.1474 1.0000 4.500 0.6898 0.01273 0.00464 -0.0261 0.0586 1.0000 5.000 0.7461 0.01362 0.00556 -0.0259 0.0494 1.0000 5.500 0.8012 0.01467 0.00659 -0.0258 0.0387 1.0000 6.000 0.8558 0.01585 0.00784 -0.0257 0.0334 1.0000 6.500 0.9104 0.01677 0.00892 -0.0255 0.0308 1.0000 7.000 0.9632 0.01812 0.01029 -0.0254 0.0245 1.0000 7.500 1.0176 0.01863 0.01090 -0.0251 0.0230 1.0000 8.000 1.0712 0.01939 0.01179 -0.0247 0.0208 1.0000 8.500 1.1251 0.01977 0.01218 -0.0244 0.0152 1.0000 9.000 1.1758 0.02122 0.01362 -0.0240 0.0051 1.0000 9.500 1.2243 0.02306 0.01565 -0.0234 0.0040 1.0000 10.000 1.2700 0.02527 0.01817 -0.0226 0.0037 1.0000 10.500 1.3135 0.02765 0.02094 -0.0217 0.0035 1.0000 11.000 1.3536 0.03028 0.02396 -0.0207 0.0034 1.0000 11.500 1.3883 0.03345 0.02756 -0.0196 0.0034 1.0000 12.000 1.4138 0.03745 0.03205 -0.0185 0.0033 1.0000 12.500 1.4224 0.04296 0.03806 -0.0178 0.0033 1.0000 13.000 1.3939 0.05624 0.05189 -0.0281 0.0033 1.0000 13.500 1.3417 0.07570 0.07170 -0.0422 0.0034 1.0000 14.000 1.2788 0.09512 0.09137 -0.0532 0.0035 1.0000 14.500 1.2011 0.11935 0.11588 -0.0662 0.0036 1.0000 15.000 1.0399 0.17330 0.17023 -0.0952 0.0049 1.0000 15.500 1.0368 0.18608 0.18307 -0.1023 0.0050 1.0000 16.000 1.0444 0.19534 0.19237 -0.1076 0.0048 1.0000 16.500 1.0543 0.20393 0.20100 -0.1127 0.0047 1.0000 17.000 1.0651 0.21239 0.20951 -0.1178 0.0047 1.0000 17.500 1.0759 0.22114 0.21830 -0.1231 0.0047 1.0000 18.000 1.0855 0.23104 0.22823 -0.1292 0.0048 1.0000 18.500 1.0949 0.24191 0.23910 -0.1356 0.0050 1.0000 19.000 1.1064 0.25211 0.24927 -0.1417 0.0053 1.0000 19.500 1.1199 0.26103 0.25823 -0.1472 0.0056 1.0000 20.000 0.7965 0.24242 0.23987 -0.0973 0.0069 1.0000 20.500 0.7970 0.25094 0.24838 -0.0998 0.0083 1.0000 21.000 0.8016 0.25723 0.25468 -0.1018 0.0094 1.0000 21.500 0.8040 0.26695 0.26442 -0.1032 0.0160 1.0000 22.000 0.8081 0.27395 0.27143 -0.1056 0.0160 1.0000 22.500 0.8118 0.28081 0.27830 -0.1082 0.0159 1.0000 23.000 0.8155 0.28756 0.28510 -0.1110 0.0156 1.0000 23.500 0.8201 0.29448 0.29204 -0.1138 0.0147 1.0000 24.000 0.8250 0.30130 0.29888 -0.1162 0.0135 1.0000 24.500 0.8297 0.30794 0.30554 -0.1186 0.0126 1.0000 25.000 0.8344 0.31445 0.31207 -0.1209 0.0118 1.0000 25.500 0.8390 0.32081 0.31845 -0.1232 0.0112 1.0000 26.000 0.8436 0.32699 0.32465 -0.1254 0.0107 1.0000 26.500 0.8486 0.33348 0.33119 -0.1271 0.0103 1.0000 27.000 0.8536 0.34279 0.34052 -0.1286 0.0100 1.0000 27.500 0.8561 0.34953 0.34728 -0.1313 0.0100 1.0000 28.000 0.8584 0.35618 0.35395 -0.1340 0.0100 1.0000 28.500 0.8608 0.36286 0.36065 -0.1367 0.0099 1.0000 29.000 0.8633 0.36954 0.36736 -0.1394 0.0099 1.0000 29.500 0.8658 0.37625 0.37410 -0.1421 0.0098 1.0000 30.000 0.8684 0.38301 0.38090 -0.1448 0.0096 1.0000 30.500 0.8711 0.38991 0.38783 -0.1473 0.0094 1.0000 31.000 0.8735 0.39679 0.39474 -0.1498 0.0089 1.0000 31.500 0.8755 0.40359 0.40158 -0.1523 0.0085 1.0000 32.000 0.8771 0.41028 0.40829 -0.1547 0.0081 1.0000 32.500 0.8785 0.41692 0.41498 -0.1571 0.0077 1.0000 33.000 0.8796 0.42352 0.42161 -0.1596 0.0074 1.0000 33.500 0.8805 0.43002 0.42814 -0.1620 0.0071 1.0000 34.000 0.8811 0.43642 0.43458 -0.1645 0.0068 1.0000 34.500 0.8815 0.44272 0.44093 -0.1669 0.0065 1.0000 35.000 0.8815 0.44888 0.44712 -0.1694 0.0063 1.0000 35.500 0.8813 0.45501 0.45328 -0.1718 0.0062 1.0000 36.000 0.8807 0.46102 0.45933 -0.1742 0.0060 1.0000 36.500 0.8798 0.46697 0.46533 -0.1766 0.0058 1.0000 37.000 0.8786 0.47349 0.47189 -0.1787 0.0057 1.0000