XFOIL Version 6.96 Calculated polar for: GOE 738 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -10.500 -0.5976 0.07812 0.07315 -0.0333 1.0000 0.1174 -10.250 -0.5846 0.07540 0.07048 -0.0334 1.0000 0.1184 -10.000 -0.7575 0.05676 0.05096 -0.0367 1.0000 0.1042 -9.750 -0.7665 0.05261 0.04653 -0.0356 1.0000 0.1043 -9.500 -0.7721 0.04898 0.04255 -0.0343 1.0000 0.1045 -9.250 -0.7724 0.04611 0.03961 -0.0326 1.0000 0.1052 -9.000 -0.7718 0.04415 0.03756 -0.0306 0.9931 0.1060 -8.750 -0.7342 0.04125 0.03452 -0.0345 0.9804 0.1079 -8.500 -0.7007 0.03834 0.03129 -0.0375 0.9675 0.1101 -8.250 -0.6706 0.03575 0.02826 -0.0397 0.9541 0.1134 -8.000 -0.6457 0.03349 0.02539 -0.0403 0.9403 0.1164 -7.750 -0.6164 0.03157 0.02339 -0.0413 0.9275 0.1193 -7.500 -0.5897 0.03053 0.02228 -0.0413 0.9146 0.1232 -7.250 -0.5681 0.02952 0.02097 -0.0402 0.9023 0.1279 -7.000 -0.5471 0.02836 0.01965 -0.0390 0.8898 0.1321 -6.750 -0.5241 0.02764 0.01893 -0.0382 0.8780 0.1371 -6.500 -0.5038 0.02702 0.01803 -0.0365 0.8677 0.1434 -6.250 -0.4807 0.02614 0.01725 -0.0357 0.8566 0.1497 -6.000 -0.4591 0.02563 0.01658 -0.0344 0.8465 0.1576 -5.750 -0.4366 0.02491 0.01592 -0.0333 0.8370 0.1661 -5.500 -0.4143 0.02438 0.01527 -0.0322 0.8270 0.1771 -5.250 -0.3924 0.02384 0.01480 -0.0308 0.8184 0.1897 -5.000 -0.3696 0.02328 0.01432 -0.0300 0.8087 0.2051 -4.750 -0.3485 0.02276 0.01384 -0.0285 0.8007 0.2245 -4.500 -0.3264 0.02228 0.01347 -0.0275 0.7914 0.2475 -4.250 -0.3057 0.02182 0.01315 -0.0260 0.7834 0.2722 -4.000 -0.2840 0.02153 0.01292 -0.0249 0.7747 0.2998 -3.750 -0.2627 0.02111 0.01271 -0.0236 0.7669 0.3278 -3.500 -0.2416 0.02079 0.01255 -0.0222 0.7598 0.3607 -3.250 -0.2210 0.02043 0.01246 -0.0209 0.7510 0.4019 -3.000 -0.2021 0.01998 0.01232 -0.0186 0.7451 0.4582 -2.750 -0.1838 0.01975 0.01255 -0.0169 0.7359 0.5355 -2.500 -0.1647 0.01954 0.01274 -0.0142 0.7296 0.6246 -2.250 -0.1427 0.01967 0.01314 -0.0119 0.7231 0.7007 -2.000 -0.1172 0.01999 0.01360 -0.0104 0.7148 0.7590 -1.750 -0.0874 0.02022 0.01380 -0.0089 0.7093 0.8025 -1.500 -0.0516 0.02080 0.01437 -0.0095 0.7015 0.8353 -1.250 -0.0140 0.02124 0.01474 -0.0101 0.6947 0.8633 -1.000 0.0308 0.02157 0.01492 -0.0115 0.6897 0.8847 -0.750 0.0811 0.02227 0.01556 -0.0153 0.6807 0.9026 -0.500 0.1422 0.02261 0.01576 -0.0203 0.6745 0.9152 -0.250 0.1963 0.02284 0.01583 -0.0242 0.6689 0.9306 0.000 0.2517 0.02328 0.01625 -0.0295 0.6594 0.9483 0.250 0.3082 0.02306 0.01586 -0.0337 0.6528 0.9674 0.500 0.3693 0.02280 0.01554 -0.0401 0.6405 0.9832 0.750 0.4259 0.02195 0.01448 -0.0449 0.6332 0.9978 1.000 0.4502 0.02207 0.01464 -0.0456 0.6229 1.0000 1.250 0.4675 0.02191 0.01439 -0.0441 0.6171 1.0000 1.500 0.4852 0.02208 0.01455 -0.0431 0.6096 1.0000 1.750 0.5032 0.02212 0.01457 -0.0419 0.6020 1.0000 2.000 0.5218 0.02191 0.01424 -0.0402 0.5970 1.0000 2.250 0.5394 0.02234 0.01474 -0.0394 0.5877 1.0000 2.500 0.5582 0.02226 0.01460 -0.0379 0.5815 1.0000 2.750 0.5767 0.02238 0.01468 -0.0364 0.5749 1.0000 3.000 0.5945 0.02260 0.01492 -0.0351 0.5660 1.0000 3.250 0.6154 0.02232 0.01452 -0.0332 0.5607 1.0000 3.500 0.6318 0.02281 0.01509 -0.0320 0.5502 1.0000 3.750 0.6532 0.02255 0.01473 -0.0302 0.5439 1.0000 4.000 0.6704 0.02296 0.01520 -0.0288 0.5341 1.0000 4.250 0.6921 0.02282 0.01498 -0.0272 0.5269 1.0000 4.500 0.7105 0.02314 0.01533 -0.0258 0.5174 1.0000 4.750 0.7326 0.02305 0.01517 -0.0243 0.5094 1.0000 5.000 0.7515 0.02334 0.01549 -0.0228 0.4992 1.0000 5.250 0.7753 0.02314 0.01520 -0.0214 0.4908 1.0000 5.500 0.7935 0.02353 0.01563 -0.0199 0.4794 1.0000 5.750 0.8195 0.02327 0.01524 -0.0187 0.4719 1.0000 6.000 0.8363 0.02387 0.01593 -0.0172 0.4599 1.0000 6.250 0.8629 0.02370 0.01560 -0.0161 0.4523 1.0000 6.500 0.8805 0.02412 0.01612 -0.0146 0.4401 1.0000 6.750 0.9011 0.02433 0.01631 -0.0132 0.4292 1.0000 7.000 0.9268 0.02414 0.01598 -0.0122 0.4199 1.0000 7.250 0.9435 0.02469 0.01663 -0.0106 0.4085 1.0000 7.500 0.9718 0.02459 0.01633 -0.0099 0.4011 1.0000 7.750 0.9852 0.02536 0.01729 -0.0082 0.3902 1.0000 8.000 1.0094 0.02546 0.01731 -0.0072 0.3816 1.0000 8.250 1.0275 0.02582 0.01771 -0.0057 0.3712 1.0000 8.500 1.0464 0.02614 0.01804 -0.0043 0.3612 1.0000 8.750 1.0712 0.02604 0.01781 -0.0033 0.3513 1.0000 9.000 1.0838 0.02664 0.01855 -0.0014 0.3404 1.0000 9.250 1.1051 0.02683 0.01865 -0.0002 0.3310 1.0000 9.500 1.1212 0.02728 0.01914 0.0014 0.3209 1.0000 9.750 1.1363 0.02786 0.01977 0.0031 0.3115 1.0000 10.000 1.1583 0.02808 0.01987 0.0042 0.3017 1.0000 10.250 1.1660 0.02894 0.02087 0.0065 0.2915 1.0000 10.500 1.1827 0.02946 0.02134 0.0080 0.2813 1.0000 10.750 1.1963 0.03004 0.02188 0.0098 0.2703 1.0000 11.000 1.2007 0.03103 0.02296 0.0124 0.2595 1.0000 11.250 1.2123 0.03182 0.02366 0.0143 0.2484 1.0000 11.500 1.2230 0.03261 0.02435 0.0162 0.2369 1.0000 11.750 1.2145 0.03396 0.02584 0.0200 0.2275 1.0000 12.000 1.2221 0.03501 0.02679 0.0220 0.2170 1.0000 12.250 1.2195 0.03639 0.02820 0.0244 0.2073 1.0000 12.500 1.2168 0.03810 0.02995 0.0263 0.1983 1.0000 12.750 1.2315 0.03904 0.03067 0.0274 0.1884 1.0000 13.000 1.2160 0.04156 0.03346 0.0292 0.1817 1.0000 13.250 1.2338 0.04238 0.03407 0.0301 0.1736 1.0000 13.500 1.2194 0.04526 0.03722 0.0313 0.1682 1.0000 13.750 1.2279 0.04672 0.03864 0.0320 0.1623 1.0000 14.000 1.2346 0.04862 0.04056 0.0328 0.1574 1.0000 14.250 1.2269 0.05155 0.04369 0.0333 0.1536 1.0000 14.500 1.2355 0.05323 0.04537 0.0338 0.1494 1.0000 14.750 1.2562 0.05428 0.04632 0.0345 0.1452 1.0000 15.000 1.2383 0.05830 0.05062 0.0344 0.1430 1.0000 15.250 1.2220 0.06246 0.05501 0.0340 0.1408 1.0000 15.500 1.2082 0.06664 0.05937 0.0334 0.1388 1.0000 15.750 1.2018 0.07022 0.06306 0.0329 0.1367 1.0000 16.000 1.2491 0.06887 0.06148 0.0347 0.1328 1.0000 16.250 1.2071 0.07609 0.06903 0.0326 0.1323 1.0000 16.500 1.1449 0.08686 0.08013 0.0281 0.1325 1.0000