XFOIL Version 6.96 Calculated polar for: GOE 741 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -12.750 -0.8642 0.04386 0.03952 -0.0479 0.6340 0.0257 -12.500 -0.8887 0.04013 0.03553 -0.0456 0.6284 0.0257 -12.250 -0.9011 0.03773 0.03294 -0.0423 0.6218 0.0258 -12.000 -0.9062 0.03578 0.03078 -0.0392 0.6150 0.0260 -11.750 -0.9034 0.03392 0.02871 -0.0369 0.6086 0.0261 -11.500 -0.8963 0.03225 0.02684 -0.0348 0.6019 0.0263 -11.250 -0.8864 0.03071 0.02509 -0.0329 0.5950 0.0264 -11.000 -0.8741 0.02929 0.02346 -0.0311 0.5889 0.0266 -10.750 -0.8594 0.02803 0.02201 -0.0295 0.5824 0.0267 -10.500 -0.8431 0.02686 0.02065 -0.0280 0.5758 0.0269 -10.250 -0.8253 0.02581 0.01941 -0.0267 0.5700 0.0271 -10.000 -0.8062 0.02482 0.01826 -0.0254 0.5646 0.0272 -9.750 -0.7861 0.02393 0.01720 -0.0242 0.5593 0.0273 -9.500 -0.7650 0.02313 0.01624 -0.0232 0.5545 0.0275 -9.250 -0.7430 0.02240 0.01536 -0.0222 0.5504 0.0276 -9.000 -0.7207 0.02165 0.01449 -0.0212 0.5462 0.0278 -8.750 -0.6988 0.02080 0.01355 -0.0202 0.5417 0.0280 -8.500 -0.6757 0.02014 0.01280 -0.0193 0.5373 0.0282 -8.250 -0.6519 0.01958 0.01216 -0.0185 0.5333 0.0284 -8.000 -0.6274 0.01904 0.01157 -0.0178 0.5302 0.0286 -7.750 -0.6026 0.01855 0.01101 -0.0171 0.5270 0.0289 -7.500 -0.5774 0.01809 0.01049 -0.0165 0.5236 0.0292 -7.250 -0.5520 0.01764 0.00997 -0.0158 0.5202 0.0294 -7.000 -0.5265 0.01722 0.00948 -0.0152 0.5168 0.0297 -6.750 -0.5007 0.01683 0.00900 -0.0147 0.5136 0.0300 -6.500 -0.4744 0.01644 0.00857 -0.0141 0.5109 0.0305 -6.250 -0.4480 0.01608 0.00815 -0.0136 0.5083 0.0309 -6.000 -0.4215 0.01574 0.00774 -0.0131 0.5055 0.0313 -5.750 -0.3948 0.01542 0.00736 -0.0127 0.5027 0.0316 -5.500 -0.3686 0.01504 0.00693 -0.0122 0.4998 0.0319 -5.250 -0.3422 0.01469 0.00655 -0.0117 0.4969 0.0324 -5.000 -0.3154 0.01440 0.00623 -0.0113 0.4942 0.0328 -4.750 -0.2882 0.01413 0.00595 -0.0109 0.4921 0.0333 -4.500 -0.2609 0.01387 0.00568 -0.0105 0.4898 0.0339 -4.250 -0.2335 0.01363 0.00542 -0.0102 0.4873 0.0345 -4.000 -0.2061 0.01341 0.00516 -0.0098 0.4846 0.0351 -3.750 -0.1786 0.01322 0.00493 -0.0095 0.4819 0.0358 -3.500 -0.1512 0.01299 0.00468 -0.0092 0.4793 0.0366 -3.250 -0.1238 0.01282 0.00448 -0.0089 0.4768 0.0376 -3.000 -0.0961 0.01265 0.00431 -0.0086 0.4748 0.0389 -2.750 -0.0682 0.01248 0.00415 -0.0083 0.4728 0.0403 -2.500 -0.0404 0.01230 0.00399 -0.0081 0.4704 0.0422 -2.250 -0.0126 0.01215 0.00384 -0.0078 0.4678 0.0444 -2.000 0.0151 0.01200 0.00369 -0.0075 0.4651 0.0472 -1.750 0.0428 0.01187 0.00356 -0.0073 0.4626 0.0512 -1.500 0.0703 0.01175 0.00345 -0.0070 0.4604 0.0570 -1.250 0.0977 0.01164 0.00336 -0.0067 0.4581 0.0658 -1.000 0.1254 0.01151 0.00332 -0.0065 0.4560 0.0784 -0.750 0.1534 0.01143 0.00328 -0.0063 0.4535 0.0893 -0.500 0.1812 0.01134 0.00323 -0.0061 0.4509 0.0979 -0.250 0.2091 0.01128 0.00318 -0.0059 0.4484 0.1046 0.000 0.2368 0.01122 0.00314 -0.0057 0.4459 0.1118 0.250 0.2644 0.01116 0.00309 -0.0055 0.4432 0.1206 0.500 0.2916 0.01110 0.00306 -0.0052 0.4403 0.1354 0.750 0.3188 0.01098 0.00310 -0.0050 0.4372 0.1725 1.000 0.3464 0.01090 0.00312 -0.0048 0.4329 0.1978 1.250 0.3740 0.01086 0.00311 -0.0047 0.4283 0.2153 1.500 0.4016 0.01086 0.00310 -0.0045 0.4246 0.2268 1.750 0.4291 0.01086 0.00312 -0.0043 0.4220 0.2383 2.000 0.4568 0.01083 0.00314 -0.0041 0.4192 0.2497 2.500 0.5115 0.01077 0.00320 -0.0038 0.4124 0.2880 2.750 0.5362 0.01057 0.00323 -0.0032 0.4091 0.3689 3.250 0.5958 0.00932 0.00362 -0.0036 0.4031 0.9337 3.500 0.6331 0.00948 0.00377 -0.0053 0.3994 0.9430 3.750 0.6578 0.00961 0.00389 -0.0045 0.3959 0.9527 4.000 0.7025 0.00983 0.00405 -0.0079 0.3919 0.9573 4.250 0.7384 0.01001 0.00421 -0.0094 0.3883 0.9619 4.500 0.7630 0.01014 0.00434 -0.0087 0.3848 0.9671 4.750 0.8049 0.01031 0.00450 -0.0116 0.3800 0.9696 5.000 0.8429 0.01049 0.00463 -0.0137 0.3750 0.9720 5.250 0.8772 0.01065 0.00477 -0.0151 0.3700 0.9744 5.500 0.9081 0.01080 0.00492 -0.0158 0.3639 0.9770 5.750 0.9346 0.01098 0.00506 -0.0157 0.3583 0.9790 6.000 0.9636 0.01115 0.00523 -0.0160 0.3529 0.9812 6.250 0.9970 0.01131 0.00538 -0.0174 0.3467 0.9822 6.500 1.0277 0.01153 0.00556 -0.0183 0.3411 0.9832 6.750 1.0594 0.01169 0.00574 -0.0193 0.3355 0.9845 7.000 1.0918 0.01192 0.00595 -0.0205 0.3287 0.9863 7.250 1.1225 0.01217 0.00618 -0.0215 0.3219 0.9882 7.500 1.1514 0.01243 0.00644 -0.0221 0.3144 0.9899 7.750 1.1798 0.01274 0.00673 -0.0227 0.3080 0.9919 8.000 1.2098 0.01301 0.00700 -0.0235 0.3013 0.9933 8.250 1.2380 0.01337 0.00733 -0.0243 0.2943 0.9943 8.500 1.2653 0.01366 0.00763 -0.0247 0.2878 0.9953 8.750 1.2913 0.01407 0.00802 -0.0251 0.2804 0.9965 9.000 1.3176 0.01444 0.00840 -0.0255 0.2744 0.9976 9.250 1.3434 0.01487 0.00883 -0.0259 0.2677 0.9988 9.500 1.3685 0.01541 0.00935 -0.0264 0.2610 0.9999 9.750 1.3853 0.01584 0.00981 -0.0251 0.2559 1.0000 10.000 1.3963 0.01642 0.01039 -0.0229 0.2506 1.0000 10.250 1.4029 0.01710 0.01107 -0.0202 0.2462 1.0000 10.500 1.4092 0.01769 0.01170 -0.0174 0.2424 1.0000 10.750 1.3947 0.01869 0.01275 -0.0121 0.2394 1.0000 11.000 1.3894 0.01988 0.01397 -0.0087 0.2362 1.0000 11.250 1.3875 0.02124 0.01535 -0.0063 0.2328 1.0000 11.500 1.3894 0.02257 0.01670 -0.0044 0.2300 1.0000 11.750 1.3962 0.02369 0.01788 -0.0030 0.2275 1.0000 12.000 1.4016 0.02500 0.01923 -0.0017 0.2243 1.0000 12.250 1.4048 0.02654 0.02081 -0.0004 0.2209 1.0000 12.500 1.4064 0.02829 0.02257 0.0007 0.2176 1.0000 12.750 1.4081 0.03008 0.02438 0.0017 0.2150 1.0000 13.000 1.4159 0.03144 0.02581 0.0024 0.2125 1.0000 13.250 1.4218 0.03299 0.02742 0.0031 0.2096 1.0000 13.500 1.4248 0.03482 0.02930 0.0038 0.2062 1.0000 13.750 1.4247 0.03697 0.03147 0.0044 0.2025 1.0000 14.000 1.4257 0.03905 0.03357 0.0050 0.1994 1.0000 14.250 1.4321 0.04073 0.03532 0.0053 0.1964 1.0000 14.500 1.4364 0.04267 0.03731 0.0056 0.1924 1.0000 14.750 1.4331 0.04539 0.04004 0.0058 0.1869 1.0000 15.000 1.4349 0.04766 0.04236 0.0060 0.1820 1.0000 15.250 1.4342 0.05024 0.04495 0.0060 0.1752 1.0000 15.500 1.4310 0.05311 0.04784 0.0060 0.1693 1.0000 15.750 1.4266 0.05616 0.05090 0.0059 0.1610 1.0000 16.000 1.4222 0.05927 0.05402 0.0057 0.1538 1.0000 16.250 1.4126 0.06301 0.05774 0.0054 0.1456 1.0000 16.500 1.4052 0.06656 0.06130 0.0051 0.1380 1.0000 16.750 1.3977 0.07020 0.06494 0.0046 0.1326 1.0000 17.000 1.3865 0.07431 0.06905 0.0041 0.1252 1.0000 17.250 1.3819 0.07770 0.07246 0.0036 0.1212 1.0000 17.500 1.3764 0.08126 0.07605 0.0030 0.1163 1.0000 17.750 1.3714 0.08476 0.07958 0.0023 0.1127 1.0000 18.000 1.3667 0.08831 0.08316 0.0016 0.1090 1.0000 18.250 1.3640 0.09161 0.08651 0.0010 0.1049 1.0000 18.500 1.3565 0.09560 0.09053 0.0000 0.1009 1.0000 18.750 1.3546 0.09885 0.09383 -0.0007 0.0973 1.0000 19.000 1.3492 0.10264 0.09766 -0.0017 0.0918 1.0000 19.250 1.3436 0.10648 0.10153 -0.0028 0.0862 1.0000