XFOIL Version 6.94 Calculated polar for: CURTISS CR-1 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 0.4738 0.01202 0.00468 -0.0974 0.7288 0.2157 0.500 0.5225 0.01177 0.00457 -0.0956 0.7153 0.2441 1.500 0.6232 0.01122 0.00416 -0.0924 0.6826 0.3229 2.000 0.8098 0.00973 0.00428 -0.1201 0.6610 1.0000 2.500 0.8535 0.00981 0.00428 -0.1172 0.6406 1.0000 3.000 0.8965 0.00993 0.00427 -0.1142 0.6158 1.0000 3.500 0.9365 0.01010 0.00437 -0.1106 0.5834 1.0000 4.000 0.9738 0.01044 0.00451 -0.1065 0.5441 1.0000 4.500 1.0068 0.01099 0.00481 -0.1016 0.4992 1.0000 5.000 1.0364 0.01168 0.00526 -0.0963 0.4553 1.0000 5.500 1.0637 0.01246 0.00581 -0.0906 0.4166 1.0000 6.000 1.0892 0.01326 0.00645 -0.0847 0.3822 1.0000 6.500 1.1096 0.01407 0.00711 -0.0779 0.3527 1.0000 7.000 1.1283 0.01486 0.00781 -0.0708 0.3263 1.0000 7.500 1.1500 0.01576 0.00862 -0.0647 0.3037 1.0000 8.000 1.1740 0.01675 0.00955 -0.0594 0.2843 1.0000 8.500 1.1990 0.01787 0.01059 -0.0545 0.2682 1.0000 9.000 1.2271 0.01894 0.01167 -0.0504 0.2552 1.0000 9.500 1.2572 0.02006 0.01284 -0.0468 0.2445 1.0000 10.000 1.2834 0.02139 0.01412 -0.0429 0.2325 1.0000 10.500 1.3125 0.02255 0.01542 -0.0397 0.2222 1.0000 11.000 1.3380 0.02411 0.01692 -0.0362 0.2117 1.0000 11.500 1.3657 0.02543 0.01846 -0.0333 0.2033 1.0000 12.000 1.3877 0.02726 0.02027 -0.0300 0.1932 1.0000 12.500 1.4125 0.02892 0.02216 -0.0273 0.1842 1.0000 13.000 1.4309 0.03113 0.02443 -0.0244 0.1739 1.0000 13.500 1.4470 0.03365 0.02705 -0.0218 0.1610 1.0000 14.000 1.4609 0.03654 0.03006 -0.0195 0.1436 1.0000 15.000 1.4206 0.04956 0.04257 -0.0142 0.0459 1.0000 15.500 1.3927 0.05789 0.05092 -0.0130 0.0336 1.0000 16.000 1.3720 0.06621 0.05945 -0.0131 0.0303 1.0000 16.500 1.3521 0.07508 0.06858 -0.0142 0.0281 1.0000 17.000 1.3247 0.08554 0.07928 -0.0165 0.0268 1.0000 17.500 1.2947 0.09696 0.09095 -0.0198 0.0260 1.0000 18.000 1.2700 0.10784 0.10207 -0.0232 0.0252 1.0000 18.500 1.2472 0.11865 0.11307 -0.0270 0.0243 1.0000 19.000 1.2309 0.12832 0.12284 -0.0305 0.0235 1.0000 19.500 1.2267 0.13560 0.13015 -0.0330 0.0227 1.0000 20.000 1.2282 0.14216 0.13684 -0.0355 0.0216 1.0000 20.500 1.2355 0.14730 0.14200 -0.0372 0.0205 1.0000 21.000 1.2499 0.15066 0.14534 -0.0378 0.0194 1.0000 21.500 1.2555 0.15650 0.15135 -0.0405 0.0185 1.0000 22.000 1.2646 0.16137 0.15633 -0.0426 0.0178 1.0000 22.500 1.2838 0.16354 0.15848 -0.0428 0.0170 1.0000 23.000 1.2893 0.16898 0.16410 -0.0455 0.0166 1.0000 23.500 1.2830 0.17760 0.17302 -0.0510 0.0163 1.0000 24.000 1.2754 0.18662 0.18233 -0.0569 0.0162 1.0000 24.500 1.2606 0.19773 0.19376 -0.0646 0.0161 1.0000 25.000 1.2368 0.21183 0.20820 -0.0746 0.0162 1.0000 25.500 1.2022 0.23004 0.22675 -0.0874 0.0165 1.0000 26.000 0.8405 0.30071 0.29841 -0.1161 0.0265 1.0000 26.500 0.8401 0.31268 0.31040 -0.1212 0.0242 1.0000 27.000 0.8513 0.31805 0.31582 -0.1236 0.0230 1.0000 27.500 0.8509 0.33044 0.32822 -0.1286 0.0212 1.0000 28.000 0.8582 0.33750 0.33532 -0.1317 0.0201 1.0000 28.500 0.8611 0.34829 0.34613 -0.1357 0.0187 1.0000 29.000 0.8671 0.35598 0.35386 -0.1390 0.0173 1.0000 29.500 0.8758 0.36222 0.36013 -0.1414 0.0168 1.0000 30.000 0.8750 0.37522 0.37315 -0.1462 0.0155 1.0000 30.500 0.8800 0.38297 0.38094 -0.1493 0.0145 1.0000 31.000 0.8862 0.38991 0.38792 -0.1519 0.0141 1.0000 31.500 0.8865 0.40251 0.40054 -0.1562 0.0132 1.0000 32.000 0.8900 0.41119 0.40925 -0.1595 0.0124 1.0000 32.500 0.8936 0.41892 0.41702 -0.1625 0.0119 1.0000 33.500 0.8980 0.43841 0.43657 -0.1691 0.0109 1.0000 34.000 0.9002 0.44716 0.44535 -0.1723 0.0102 1.0000 34.500 0.9022 0.45529 0.45352 -0.1753 0.0098 1.0000 35.000 0.9047 0.46197 0.46024 -0.1780 0.0094 1.0000 35.500 0.9048 0.47257 0.47087 -0.1813 0.0093 1.0000 36.000 0.9056 0.48285 0.48118 -0.1844 0.0086 1.0000 36.500 0.9061 0.49120 0.48957 -0.1874 0.0083 1.0000 37.000 0.9064 0.49937 0.49777 -0.1903 0.0078 1.0000 37.500 0.9064 0.50684 0.50527 -0.1932 0.0075 1.0000 38.500 0.9051 0.52366 0.52216 -0.1988 0.0072 1.0000 39.000 0.9042 0.53287 0.53140 -0.2016 0.0068 1.0000 39.500 0.9029 0.54094 0.53951 -0.2043 0.0064 1.0000 40.000 0.9014 0.54862 0.54722 -0.2070 0.0060 1.0000 40.500 0.8993 0.55556 0.55420 -0.2096 0.0056 1.0000 41.000 0.8970 0.56203 0.56070 -0.2122 0.0055 1.0000 42.000 0.8914 0.57765 0.57638 -0.2173 0.0053 1.0000 42.500 0.8885 0.58553 0.58429 -0.2197 0.0051 1.0000 43.000 0.8852 0.59249 0.59129 -0.2221 0.0048 1.0000 43.500 0.8815 0.59899 0.59782 -0.2245 0.0044 1.0000 44.000 0.8775 0.60499 0.60385 -0.2269 0.0041 1.0000 44.500 0.8730 0.61032 0.60922 -0.2292 0.0039 1.0000 45.000 0.8681 0.61493 0.61387 -0.2314 0.0038 1.0000 46.000 0.8585 0.62820 0.62719 -0.2357 0.0036 1.0000 46.500 0.8534 0.63400 0.63303 -0.2378 0.0035 1.0000 47.000 0.8480 0.63929 0.63835 -0.2398 0.0031 1.0000 47.500 0.8421 0.64370 0.64279 -0.2418 0.0029 1.0000 48.000 0.8359 0.64772 0.64684 -0.2437 0.0027 1.0000 48.500 0.8293 0.65092 0.65007 -0.2457 0.0025 1.0000 50.000 0.8090 0.66263 0.66186 -0.2510 0.0023 1.0000 50.500 0.8020 0.66615 0.66541 -0.2526 0.0022 1.0000 51.000 0.7947 0.66892 0.66821 -0.2542 0.0019 1.0000 51.500 0.7871 0.67111 0.67043 -0.2559 0.0017 1.0000 52.000 0.7791 0.67254 0.67189 -0.2574 0.0015 1.0000 52.500 0.7707 0.67328 0.67266 -0.2590 0.0013 1.0000 54.000 0.7455 0.67740 0.67684 -0.2630 0.0012 1.0000 54.500 0.7371 0.67828 0.67775 -0.2642 0.0011 1.0000 55.000 0.7282 0.67830 0.67779 -0.2654 0.0009 1.0000 55.500 0.7191 0.67785 0.67737 -0.2665 0.0008 1.0000 56.000 0.7097 0.67669 0.67623 -0.2676 0.0006 1.0000 56.500 0.7001 0.67481 0.67438 -0.2687 0.0005 1.0000 57.000 0.6900 0.67216 0.67175 -0.2698 0.0005 1.0000 57.500 0.6807 0.67195 0.67156 -0.2706 0.0004 1.0000 58.000 0.6711 0.67020 0.66983 -0.2714 0.0003 1.0000 58.500 0.6611 0.66731 0.66696 -0.2722 0.0003 1.0000 59.000 0.6507 0.66359 0.66326 -0.2730 0.0002 1.0000 60.000 0.6304 0.65761 0.65731 -0.2742 0.0001 1.0000