XFOIL Version 6.94 Calculated polar for: GOE 275 (DAIMLER VI) 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 0.5414 0.01227 0.00504 -0.1011 0.7246 0.0348 0.500 0.5869 0.01193 0.00430 -0.0985 0.6404 0.0379 1.000 0.6313 0.01201 0.00406 -0.0961 0.5690 0.0561 1.500 0.6761 0.01190 0.00366 -0.0935 0.5026 0.0536 2.000 0.7218 0.01198 0.00351 -0.0913 0.4504 0.0546 2.500 0.7697 0.01214 0.00350 -0.0896 0.4162 0.0581 3.000 0.8191 0.01239 0.00358 -0.0882 0.3931 0.0641 3.500 0.8763 0.01111 0.00401 -0.0890 0.3749 1.0000 4.000 0.9264 0.01152 0.00429 -0.0878 0.3606 1.0000 5.500 1.0648 0.01301 0.00522 -0.0825 0.2447 1.0000 6.000 1.1022 0.01438 0.00597 -0.0796 0.1585 1.0000 6.500 1.1402 0.01576 0.00693 -0.0769 0.0889 1.0000 7.000 1.1797 0.01692 0.00800 -0.0742 0.0676 1.0000 8.000 1.2471 0.01994 0.01077 -0.0672 0.0045 1.0000 8.500 1.2830 0.02099 0.01199 -0.0639 0.0045 1.0000 9.000 1.3126 0.02216 0.01336 -0.0595 0.0047 1.0000 9.500 1.3374 0.02356 0.01499 -0.0546 0.0050 1.0000 10.000 1.3569 0.02532 0.01702 -0.0492 0.0052 1.0000 10.500 1.3772 0.02708 0.01901 -0.0444 0.0057 1.0000 11.000 1.3915 0.02935 0.02155 -0.0395 0.0062 1.0000 11.500 1.3969 0.03245 0.02496 -0.0346 0.0066 1.0000 12.000 1.3955 0.03643 0.02923 -0.0304 0.0070 1.0000 12.500 1.3969 0.04073 0.03380 -0.0278 0.0075 1.0000 13.000 1.3841 0.04724 0.04062 -0.0266 0.0080 1.0000 13.500 1.3646 0.05578 0.04944 -0.0278 0.0083 1.0000 14.000 1.3414 0.06588 0.05977 -0.0307 0.0085 1.0000 14.500 1.3330 0.07451 0.06866 -0.0335 0.0091 1.0000 15.000 1.3224 0.08360 0.07798 -0.0364 0.0098 1.0000 15.500 1.3254 0.08948 0.08384 -0.0363 0.0107 1.0000 16.000 1.3593 0.09072 0.08522 -0.0322 0.0131 1.0000 16.500 1.3727 0.09701 0.09206 -0.0317 0.0160 1.0000 17.000 1.3394 0.11164 0.10733 -0.0395 0.0170 1.0000 17.500 1.3256 0.12344 0.11957 -0.0443 0.0190 1.0000 18.000 1.2895 0.13974 0.13626 -0.0552 0.0190 1.0000 18.500 1.2592 0.15569 0.15250 -0.0660 0.0189 1.0000 19.000 1.2323 0.17144 0.16844 -0.0766 0.0186 1.0000 19.500 1.1933 0.19263 0.18986 -0.0922 0.0162 1.0000 20.000 1.1692 0.21019 0.20750 -0.1033 0.0157 1.0000 20.500 0.9214 0.27177 0.26964 -0.1364 0.0265 1.0000 21.000 0.9273 0.28179 0.27968 -0.1403 0.0261 1.0000 21.500 0.9335 0.29199 0.28991 -0.1441 0.0258 1.0000 22.500 0.9446 0.31262 0.31058 -0.1519 0.0228 1.0000 23.000 0.9542 0.32102 0.31901 -0.1545 0.0218 1.0000 23.500 0.9566 0.33292 0.33092 -0.1592 0.0196 1.0000 24.000 0.9680 0.34049 0.33853 -0.1610 0.0185 1.0000 24.500 0.9685 0.35304 0.35108 -0.1663 0.0164 1.0000 25.000 0.9747 0.36287 0.36094 -0.1694 0.0154 1.0000 25.500 0.9797 0.37341 0.37150 -0.1731 0.0134 1.0000 26.000 0.9845 0.38429 0.38240 -0.1765 0.0126 1.0000 26.500 0.9896 0.39446 0.39261 -0.1799 0.0111 1.0000 27.000 0.9945 0.40447 0.40264 -0.1829 0.0105 1.0000 27.500 0.9984 0.41611 0.41431 -0.1866 0.0094 1.0000 28.000 1.0031 0.42525 0.42348 -0.1894 0.0087 1.0000 28.500 1.0061 0.43726 0.43551 -0.1929 0.0084 1.0000 29.000 1.0097 0.44844 0.44673 -0.1962 0.0076 1.0000 29.500 1.0130 0.45841 0.45673 -0.1993 0.0071 1.0000 30.000 1.0160 0.46823 0.46659 -0.2020 0.0068 1.0000 30.500 1.0182 0.48051 0.47889 -0.2054 0.0067 1.0000 31.000 1.0205 0.49190 0.49031 -0.2085 0.0062 1.0000 31.500 1.0225 0.50264 0.50109 -0.2115 0.0059 1.0000 32.000 1.0240 0.51305 0.51153 -0.2145 0.0056 1.0000 32.500 1.0252 0.52334 0.52186 -0.2174 0.0054 1.0000 33.000 1.0260 0.53261 0.53118 -0.2199 0.0052 1.0000 33.500 1.0264 0.54416 0.54275 -0.2229 0.0052 1.0000 34.000 1.0264 0.55471 0.55334 -0.2258 0.0052 1.0000 34.500 1.0264 0.56590 0.56456 -0.2287 0.0052 1.0000 35.000 1.0260 0.57628 0.57498 -0.2315 0.0052 1.0000 35.500 1.0254 0.58711 0.58585 -0.2342 0.0051 1.0000 36.000 1.0243 0.59735 0.59613 -0.2369 0.0051 1.0000 36.500 1.0228 0.60741 0.60623 -0.2395 0.0051 1.0000 37.000 1.0211 0.61738 0.61624 -0.2421 0.0050 1.0000 37.500 1.0190 0.62731 0.62621 -0.2447 0.0050 1.0000 38.000 1.0166 0.63699 0.63593 -0.2472 0.0049 1.0000 38.500 1.0139 0.64672 0.64570 -0.2497 0.0049 1.0000 39.000 1.0108 0.65614 0.65515 -0.2521 0.0048 1.0000 39.500 1.0074 0.66534 0.66439 -0.2545 0.0047 1.0000 40.000 1.0039 0.67476 0.67386 -0.2568 0.0044 1.0000 40.500 0.9999 0.68369 0.68282 -0.2591 0.0042 1.0000 41.000 0.9953 0.69204 0.69121 -0.2614 0.0040 1.0000 41.500 0.9903 0.70012 0.69933 -0.2636 0.0039 1.0000 42.000 0.9862 0.71123 0.71045 -0.2657 0.0038 1.0000 42.500 0.9819 0.72093 0.72019 -0.2676 0.0037 1.0000 43.000 0.9770 0.72995 0.72923 -0.2696 0.0034 1.0000 43.500 0.9716 0.73852 0.73783 -0.2716 0.0030 1.0000 44.000 0.9656 0.74606 0.74540 -0.2736 0.0028 1.0000 44.500 0.9586 0.75246 0.75184 -0.2755 0.0027 1.0000 45.500 0.9471 0.77078 0.77020 -0.2789 0.0026 1.0000 46.000 0.9406 0.77816 0.77761 -0.2806 0.0024 1.0000 46.500 0.9338 0.78537 0.78484 -0.2823 0.0022 1.0000 47.000 0.9266 0.79179 0.79129 -0.2839 0.0020 1.0000 47.500 0.9189 0.79746 0.79700 -0.2855 0.0018 1.0000 48.000 0.9104 0.80180 0.80137 -0.2871 0.0017 1.0000 49.500 0.8862 0.81933 0.81895 -0.2913 0.0016 1.0000 50.000 0.8780 0.82400 0.82365 -0.2926 0.0016 1.0000 50.500 0.8697 0.82889 0.82855 -0.2937 0.0015 1.0000 51.000 0.8608 0.83252 0.83221 -0.2949 0.0014 1.0000 51.500 0.8516 0.83553 0.83525 -0.2961 0.0013 1.0000 52.000 0.8423 0.83852 0.83826 -0.2971 0.0011 1.0000 52.500 0.8325 0.84026 0.84003 -0.2982 0.0010 1.0000 53.000 0.8224 0.84120 0.84098 -0.2993 0.0009 1.0000 53.500 0.8120 0.84202 0.84183 -0.3003 0.0008 1.0000 54.000 0.8011 0.84169 0.84153 -0.3014 0.0008 1.0000 55.000 0.7807 0.84392 0.84378 -0.3029 0.0007 1.0000 55.500 0.7709 0.84428 0.84416 -0.3035 0.0007 1.0000 56.000 0.7602 0.84357 0.84347 -0.3042 0.0006 1.0000 56.500 0.7494 0.84230 0.84222 -0.3048 0.0006 1.0000 57.000 0.7383 0.84043 0.84037 -0.3054 0.0005 1.0000 57.500 0.7269 0.83746 0.83742 -0.3060 0.0005 1.0000 58.000 0.7152 0.83377 0.83374 -0.3065 0.0004 1.0000 60.000 0.6687 0.81836 0.81839 -0.3079 0.0003 1.0000