XFOIL Version 6.94 Calculated polar for: GOE 701 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 0.5176 0.01160 0.00430 -0.1072 0.7256 0.2067 0.500 0.5670 0.01131 0.00407 -0.1055 0.7071 0.2371 1.000 0.6166 0.01099 0.00391 -0.1039 0.6895 0.2980 2.000 0.8289 0.00975 0.00429 -0.1249 0.6499 1.0000 2.500 0.8703 0.00993 0.00436 -0.1217 0.6296 1.0000 3.000 0.9108 0.01015 0.00448 -0.1183 0.6083 1.0000 3.500 0.9493 0.01040 0.00463 -0.1145 0.5844 1.0000 4.000 0.9745 0.01078 0.00473 -0.1079 0.5349 1.0000 4.500 0.9979 0.01132 0.00499 -0.1011 0.4850 1.0000 5.000 1.0091 0.01217 0.00542 -0.0922 0.4154 1.0000 5.500 1.0160 0.01306 0.00596 -0.0825 0.3543 1.0000 6.000 1.0305 0.01402 0.00665 -0.0748 0.3072 1.0000 6.500 1.0498 0.01506 0.00747 -0.0684 0.2679 1.0000 7.000 1.0654 0.01644 0.00851 -0.0619 0.2215 1.0000 7.500 1.0922 0.01749 0.00945 -0.0574 0.1966 1.0000 8.000 1.1175 0.01871 0.01053 -0.0529 0.1690 1.0000 8.500 1.1295 0.02077 0.01219 -0.0472 0.1103 1.0000 9.000 1.1326 0.02364 0.01466 -0.0411 0.0445 1.0000 9.500 1.1479 0.02597 0.01693 -0.0367 0.0241 1.0000 10.000 1.1664 0.02823 0.01917 -0.0332 0.0052 1.0000 10.500 1.1887 0.03035 0.02139 -0.0303 0.0042 1.0000 11.000 1.2101 0.03263 0.02382 -0.0276 0.0040 1.0000 11.500 1.2293 0.03520 0.02655 -0.0251 0.0039 1.0000 12.000 1.2460 0.03811 0.02964 -0.0228 0.0038 1.0000 12.500 1.2595 0.04146 0.03319 -0.0206 0.0038 1.0000 13.000 1.2705 0.04523 0.03717 -0.0188 0.0038 1.0000 13.500 1.2769 0.04967 0.04183 -0.0174 0.0038 1.0000 14.000 1.2782 0.05496 0.04736 -0.0164 0.0038 1.0000 14.500 1.2763 0.06091 0.05356 -0.0159 0.0038 1.0000 15.000 1.2701 0.06776 0.06065 -0.0162 0.0039 1.0000 15.500 1.2571 0.07591 0.06907 -0.0173 0.0039 1.0000 16.000 1.2408 0.08493 0.07835 -0.0191 0.0039 1.0000 16.500 1.2219 0.09474 0.08842 -0.0217 0.0039 1.0000 17.000 1.1975 0.10587 0.09980 -0.0252 0.0040 1.0000 17.500 1.1762 0.11679 0.11096 -0.0291 0.0040 1.0000 18.000 1.1560 0.12783 0.12221 -0.0334 0.0040 1.0000 18.500 1.1422 0.13787 0.13241 -0.0376 0.0040 1.0000 19.000 1.1326 0.14715 0.14182 -0.0417 0.0041 1.0000 19.500 1.1298 0.15509 0.14985 -0.0454 0.0041 1.0000 20.000 1.1323 0.16216 0.15703 -0.0488 0.0042 1.0000 20.500 1.1380 0.16858 0.16355 -0.0520 0.0042 1.0000 21.000 1.1440 0.17488 0.16997 -0.0553 0.0043 1.0000 21.500 1.1518 0.18075 0.17595 -0.0585 0.0044 1.0000 22.000 1.1618 0.18599 0.18135 -0.0613 0.0046 1.0000 22.500 1.1686 0.19205 0.18756 -0.0649 0.0048 1.0000 23.000 1.1736 0.19860 0.19429 -0.0689 0.0050 1.0000 23.500 1.1748 0.20625 0.20214 -0.0739 0.0051 1.0000 24.000 1.1723 0.21505 0.21117 -0.0797 0.0053 1.0000 24.500 1.1650 0.22557 0.22190 -0.0869 0.0054 1.0000 25.000 1.1545 0.23767 0.23422 -0.0951 0.0056 1.0000 25.500 0.8410 0.30882 0.30659 -0.1241 0.0178 1.0000 26.000 0.8517 0.31554 0.31334 -0.1265 0.0174 1.0000 26.500 0.8508 0.32865 0.32645 -0.1317 0.0163 1.0000 27.000 0.8568 0.33737 0.33520 -0.1352 0.0153 1.0000 27.500 0.8639 0.34493 0.34279 -0.1383 0.0146 1.0000 28.000 0.8711 0.35296 0.35085 -0.1411 0.0143 1.0000 28.500 0.8726 0.36480 0.36271 -0.1456 0.0132 1.0000 29.000 0.8779 0.37331 0.37125 -0.1488 0.0123 1.0000 29.500 0.8838 0.38060 0.37858 -0.1518 0.0118 1.0000 30.000 0.8884 0.38963 0.38763 -0.1549 0.0116 1.0000 30.500 0.8908 0.40076 0.39878 -0.1588 0.0110 1.0000 31.000 0.8947 0.40960 0.40765 -0.1620 0.0104 1.0000 31.500 0.8984 0.41806 0.41614 -0.1652 0.0099 1.0000 32.000 0.9021 0.42563 0.42375 -0.1681 0.0095 1.0000 32.500 0.9064 0.43317 0.43131 -0.1708 0.0094 1.0000 33.000 0.9072 0.44385 0.44203 -0.1745 0.0093 1.0000 33.500 0.9092 0.45348 0.45169 -0.1777 0.0090 1.0000 34.000 0.9112 0.46245 0.46069 -0.1808 0.0087 1.0000 34.500 0.9128 0.47094 0.46921 -0.1838 0.0084 1.0000 35.000 0.9141 0.47928 0.47759 -0.1868 0.0081 1.0000 35.500 0.9151 0.48735 0.48569 -0.1898 0.0081 1.0000 36.000 0.9158 0.49537 0.49375 -0.1927 0.0078 1.0000 36.500 0.9161 0.50309 0.50150 -0.1955 0.0077 1.0000 37.000 0.9161 0.51070 0.50914 -0.1984 0.0076 1.0000 37.500 0.9157 0.51800 0.51648 -0.2012 0.0075 1.0000 38.000 0.9152 0.52504 0.52356 -0.2039 0.0074 1.0000 40.000 0.9088 0.55490 0.55355 -0.2147 0.0073 1.0000 40.500 0.9065 0.56190 0.56059 -0.2174 0.0073 1.0000 41.000 0.9039 0.56917 0.56789 -0.2200 0.0073 1.0000 41.500 0.9011 0.57630 0.57506 -0.2225 0.0072 1.0000 42.000 0.8981 0.58335 0.58215 -0.2250 0.0070 1.0000 42.500 0.8948 0.59001 0.58885 -0.2274 0.0067 1.0000 43.000 0.8910 0.59616 0.59503 -0.2298 0.0063 1.0000 43.500 0.8870 0.60201 0.60091 -0.2321 0.0060 1.0000 44.000 0.8826 0.60722 0.60615 -0.2344 0.0058 1.0000 44.500 0.8778 0.61170 0.61068 -0.2366 0.0056 1.0000 45.500 0.8683 0.62569 0.62472 -0.2409 0.0054 1.0000 46.000 0.8632 0.63129 0.63035 -0.2429 0.0051 1.0000 46.500 0.8577 0.63636 0.63545 -0.2450 0.0047 1.0000 47.000 0.8518 0.64047 0.63959 -0.2470 0.0044 1.0000 47.500 0.8454 0.64362 0.64278 -0.2490 0.0042 1.0000 48.500 0.8325 0.65277 0.65198 -0.2527 0.0040 1.0000 49.000 0.8263 0.65794 0.65718 -0.2543 0.0039 1.0000 49.500 0.8195 0.66176 0.66103 -0.2560 0.0035 1.0000 50.000 0.8122 0.66441 0.66371 -0.2577 0.0032 1.0000 50.500 0.8046 0.66652 0.66585 -0.2593 0.0030 1.0000 51.000 0.7966 0.66762 0.66698 -0.2610 0.0028 1.0000 52.000 0.7809 0.67334 0.67274 -0.2639 0.0027 1.0000 52.500 0.7731 0.67586 0.67529 -0.2652 0.0026 1.0000 53.000 0.7649 0.67743 0.67689 -0.2665 0.0025 1.0000 53.500 0.7564 0.67828 0.67776 -0.2678 0.0022 1.0000 54.000 0.7476 0.67842 0.67792 -0.2690 0.0020 1.0000 54.500 0.7384 0.67761 0.67714 -0.2703 0.0018 1.0000 55.000 0.7288 0.67609 0.67564 -0.2716 0.0017 1.0000 56.500 0.7009 0.67514 0.67475 -0.2745 0.0016 1.0000 57.000 0.6915 0.67427 0.67390 -0.2753 0.0016 1.0000 57.500 0.6818 0.67247 0.67212 -0.2761 0.0015 1.0000 58.000 0.6720 0.67032 0.66999 -0.2769 0.0014 1.0000 58.500 0.6619 0.66751 0.66720 -0.2776 0.0013 1.0000 59.000 0.6516 0.66419 0.66391 -0.2783 0.0011 1.0000 59.500 0.6412 0.66041 0.66014 -0.2790 0.0010 1.0000 60.000 0.6307 0.65599 0.65573 -0.2796 0.0009 1.0000