XFOIL Version 6.96 Calculated polar for: GOE 15K 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 = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -16.000 -0.7375 0.07494 0.07186 -0.1173 0.9701 0.0221 -15.750 -0.7632 0.06582 0.06253 -0.1247 0.9684 0.0226 -15.500 -0.7934 0.05625 0.05268 -0.1327 0.9669 0.0222 -15.250 -0.7989 0.05095 0.04716 -0.1382 0.9659 0.0226 -15.000 -0.8219 0.04643 0.04245 -0.1381 0.9601 0.0227 -14.750 -0.8344 0.04253 0.03831 -0.1387 0.9573 0.0227 -14.500 -0.8337 0.04009 0.03564 -0.1391 0.9558 0.0235 -14.250 -0.8294 0.03786 0.03323 -0.1391 0.9547 0.0234 -14.000 -0.8478 0.03561 0.03083 -0.1341 0.9484 0.0237 -13.750 -0.8391 0.03459 0.02981 -0.1328 0.9459 0.0245 -13.500 -0.8265 0.03352 0.02868 -0.1321 0.9444 0.0250 -13.250 -0.8125 0.03247 0.02752 -0.1314 0.9432 0.0257 -13.000 -0.7973 0.03150 0.02641 -0.1308 0.9423 0.0266 -12.750 -0.8090 0.03055 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1.500 0.6665 0.01599 0.01196 -0.1259 0.8466 0.9768 1.750 0.7393 0.01504 0.01101 -0.1357 0.8466 0.9783 2.000 0.8054 0.01426 0.01022 -0.1441 0.8453 0.9796 2.250 0.8974 0.01314 0.00905 -0.1584 0.8421 0.9777 2.500 0.9103 0.01313 0.00910 -0.1550 0.8345 0.9870 2.750 0.9723 0.01243 0.00838 -0.1626 0.8278 0.9890 3.000 1.0150 0.01174 0.00773 -0.1659 0.8180 0.9989 3.250 1.0541 0.01137 0.00735 -0.1686 0.8110 0.9999 3.500 1.0471 0.01153 0.00755 -0.1610 0.8038 1.0000 3.750 1.0628 0.01145 0.00748 -0.1584 0.7963 1.0000 4.000 1.0586 0.01160 0.00767 -0.1514 0.7873 1.0000 4.250 1.0697 0.01156 0.00763 -0.1478 0.7768 1.0000 4.500 1.0665 0.01172 0.00782 -0.1411 0.7650 1.0000 4.750 1.0629 0.01188 0.00796 -0.1342 0.7469 1.0000 5.000 1.0557 0.01215 0.00822 -0.1266 0.7217 1.0000 5.250 1.0477 0.01248 0.00827 -0.1188 0.6623 1.0000 5.500 1.0224 0.01341 0.00880 -0.1075 0.5972 1.0000 5.750 0.9944 0.01461 0.00965 -0.0961 0.5273 1.0000 6.000 0.9768 0.01571 0.01048 -0.0872 0.4725 1.0000 6.250 0.9604 0.01695 0.01142 -0.0788 0.4195 1.0000 6.500 0.9584 0.01781 0.01210 -0.0734 0.3819 1.0000 6.750 0.9594 0.01863 0.01275 -0.0687 0.3440 1.0000 7.000 0.9573 0.01964 0.01346 -0.0635 0.2846 1.0000 7.250 0.9585 0.02059 0.01417 -0.0590 0.2364 1.0000 7.500 0.9622 0.02149 0.01483 -0.0551 0.1951 1.0000 7.750 0.9700 0.02223 0.01542 -0.0519 0.1677 1.0000 8.000 0.9802 0.02288 0.01596 -0.0492 0.1444 1.0000 8.250 0.9898 0.02358 0.01653 -0.0464 0.1201 1.0000 8.500 1.0013 0.02422 0.01709 -0.0439 0.1036 1.0000 8.750 1.0127 0.02486 0.01767 -0.0415 0.0913 1.0000 9.000 1.0243 0.02552 0.01827 -0.0391 0.0824 1.0000 9.250 1.0379 0.02608 0.01884 -0.0371 0.0759 1.0000 9.500 1.0486 0.02681 0.01953 -0.0346 0.0691 1.0000 9.750 1.0625 0.02736 0.02012 -0.0327 0.0652 1.0000 10.000 1.0737 0.02809 0.02083 -0.0304 0.0603 1.0000 10.250 1.0864 0.02874 0.02153 -0.0284 0.0561 1.0000 10.500 1.0982 0.02946 0.02223 -0.0263 0.0513 1.0000 10.750 1.1105 0.03016 0.02296 -0.0242 0.0477 1.0000 11.000 1.1222 0.03092 0.02375 -0.0221 0.0450 1.0000 11.250 1.1316 0.03183 0.02464 -0.0198 0.0413 1.0000 11.500 1.1447 0.03251 0.02538 -0.0180 0.0389 1.0000 11.750 1.1559 0.03331 0.02620 -0.0161 0.0370 1.0000 12.000 1.1639 0.03438 0.02727 -0.0137 0.0347 1.0000 12.250 1.1745 0.03527 0.02823 -0.0117 0.0336 1.0000 12.500 1.1863 0.03608 0.02909 -0.0099 0.0318 1.0000 12.750 1.1946 0.03717 0.03020 -0.0077 0.0304 1.0000 13.000 1.2000 0.03849 0.03156 -0.0053 0.0289 1.0000 13.250 1.2097 0.03949 0.03264 -0.0034 0.0282 1.0000 13.500 1.2168 0.04073 0.03395 -0.0013 0.0276 1.0000 13.750 1.2281 0.04163 0.03490 0.0002 0.0264 1.0000 14.000 1.2335 0.04305 0.03635 0.0024 0.0253 1.0000 14.250 1.2367 0.04465 0.03799 0.0046 0.0247 1.0000 14.500 1.2390 0.04640 0.03983 0.0070 0.0239 1.0000 14.750 1.2496 0.04743 0.04096 0.0083 0.0233 1.0000 15.000 1.2560 0.04885 0.04247 0.0100 0.0227 1.0000 15.250 1.2594 0.05056 0.04427 0.0120 0.0224 1.0000 15.500 1.2646 0.05214 0.04589 0.0135 0.0216 1.0000 15.750 1.2684 0.05387 0.04769 0.0151 0.0212 1.0000 16.000 1.2702 0.05584 0.04972 0.0168 0.0208 1.0000 16.250 1.2694 0.05808 0.05202 0.0185 0.0200 1.0000 16.500 1.2727 0.05999 0.05406 0.0198 0.0198 1.0000 16.750 1.2736 0.06220 0.05640 0.0212 0.0193 1.0000 17.000 1.2743 0.06448 0.05880 0.0224 0.0190 1.0000 17.250 1.2762 0.06666 0.06108 0.0234 0.0188 1.0000 17.500 1.2744 0.06932 0.06386 0.0245 0.0186 1.0000 17.750 1.2725 0.07207 0.06671 0.0253 0.0182 1.0000 18.000 1.2721 0.07468 0.06941 0.0258 0.0179 1.0000 18.250 1.2682 0.07776 0.07257 0.0263 0.0175 1.0000 18.500 1.2647 0.08083 0.07566 0.0265 0.0169 1.0000 18.750 1.2613 0.08403 0.07909 0.0269 0.0174 1.0000 19.000 1.2552 0.08751 0.08258 0.0269 0.0168 1.0000 19.250 1.2454 0.09155 0.08676 0.0271 0.0166 1.0000