XFOIL Version 6.96 Calculated polar for: GOE 12K AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -15.500 -0.9180 0.03786 0.03514 -0.1439 0.9786 0.0153 -15.250 -0.9273 0.03288 0.02991 -0.1483 0.9765 0.0155 -15.000 -0.9415 0.03015 0.02700 -0.1456 0.9688 0.0156 -14.750 -0.9372 0.02797 0.02468 -0.1450 0.9663 0.0160 -14.500 -0.9395 0.02673 0.02334 -0.1412 0.9595 0.0164 -14.250 -0.9263 0.02536 0.02185 -0.1403 0.9566 0.0168 -14.000 -0.9099 0.02389 0.02023 -0.1400 0.9549 0.0173 -13.750 -0.8891 0.02277 0.01898 -0.1400 0.9539 0.0179 -13.500 -0.8827 0.02194 0.01802 -0.1367 0.9478 0.0182 -13.250 -0.8688 0.02056 0.01650 -0.1355 0.9454 0.0189 -13.000 -0.8485 0.01954 0.01541 -0.1351 0.9440 0.0197 -12.750 -0.8238 0.01875 0.01454 -0.1354 0.9430 0.0204 -12.500 -0.7973 0.01800 0.01368 -0.1359 0.9423 0.0212 -12.250 -0.7693 0.01731 0.01285 -0.1368 0.9416 0.0219 -12.000 -0.7552 0.01661 0.01210 -0.1346 0.9376 0.0230 -11.750 -0.7304 0.01618 0.01164 -0.1345 0.9356 0.0242 -11.500 -0.7035 0.01575 0.01114 -0.1348 0.9342 0.0252 -11.250 -0.6741 0.01535 0.01065 -0.1356 0.9331 0.0263 -11.000 -0.6438 0.01498 0.01029 -0.1367 0.9321 0.0279 -10.750 -0.6101 0.01488 0.01018 -0.1382 0.9314 0.0291 -10.500 -0.5759 0.01470 0.00994 -0.1399 0.9307 0.0304 -10.250 -0.5425 0.01431 0.00947 -0.1416 0.9298 0.0315 -10.000 -0.5067 0.01430 0.00950 -0.1436 0.9291 0.0328 -9.750 -0.4776 0.01432 0.00951 -0.1441 0.9274 0.0337 -9.500 -0.4550 0.01435 0.00952 -0.1431 0.9252 0.0346 -9.250 -0.4287 0.01426 0.00937 -0.1430 0.9231 0.0355 -9.000 -0.3997 0.01418 0.00922 -0.1435 0.9211 0.0363 -8.750 -0.3705 0.01358 0.00852 -0.1443 0.9193 0.0375 -8.500 -0.3352 0.01354 0.00850 -0.1463 0.9179 0.0385 -8.250 -0.2983 0.01351 0.00846 -0.1486 0.9167 0.0394 -8.000 -0.2611 0.01345 0.00837 -0.1510 0.9157 0.0405 -7.750 -0.2242 0.01332 0.00818 -0.1533 0.9147 0.0417 -7.500 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0.2500 0.00869 0.00306 -0.1380 0.8746 0.0584 -2.500 0.2787 0.00855 0.00291 -0.1382 0.8727 0.0594 -2.250 0.3096 0.00843 0.00277 -0.1390 0.8707 0.0602 -2.000 0.3417 0.00837 0.00270 -0.1401 0.8685 0.0610 -1.750 0.3488 0.00830 0.00265 -0.1352 0.8655 0.0614 -1.500 0.3637 0.00815 0.00249 -0.1322 0.8624 0.0630 -1.250 0.3864 0.00801 0.00235 -0.1311 0.8598 0.0655 -1.000 0.4139 0.00790 0.00225 -0.1310 0.8576 0.0682 -0.750 0.4437 0.00781 0.00217 -0.1315 0.8556 0.0704 -0.500 0.4771 0.00776 0.00212 -0.1329 0.8537 0.0740 -0.250 0.4842 0.00766 0.00210 -0.1280 0.8503 0.0840 0.000 0.4918 0.00747 0.00207 -0.1234 0.8465 0.1335 0.250 0.5110 0.00722 0.00202 -0.1214 0.8433 0.1991 0.500 0.5316 0.00678 0.00200 -0.1201 0.8405 0.3583 0.750 0.5468 0.00619 0.00205 -0.1175 0.8370 0.5885 1.000 0.5360 0.00582 0.00214 -0.1085 0.8321 0.7358 1.250 0.7307 0.00582 0.00276 -0.1472 0.8299 0.9658 1.500 0.7545 0.00590 0.00281 -0.1459 0.8196 0.9797 1.750 0.7920 0.00596 0.00284 -0.1479 0.8046 0.9880 2.000 0.8362 0.00604 0.00286 -0.1516 0.7867 0.9947 2.250 0.8752 0.00603 0.00279 -0.1542 0.7696 0.9983 2.500 0.8963 0.00611 0.00277 -0.1527 0.7458 1.0000 2.750 0.8990 0.00627 0.00283 -0.1470 0.7229 1.0000 3.000 0.9011 0.00648 0.00292 -0.1412 0.6967 1.0000 3.250 0.8928 0.00686 0.00310 -0.1331 0.6481 1.0000 3.500 0.8583 0.00780 0.00356 -0.1193 0.5428 1.0000 3.750 0.8389 0.00879 0.00411 -0.1093 0.4548 1.0000 4.000 0.8481 0.00918 0.00437 -0.1054 0.4258 1.0000 4.250 0.8584 0.00956 0.00464 -0.1018 0.3979 1.0000 4.500 0.8702 0.00991 0.00489 -0.0986 0.3729 1.0000 4.750 0.8827 0.01027 0.00514 -0.0955 0.3437 1.0000 5.000 0.8911 0.01081 0.00546 -0.0917 0.2954 1.0000 5.250 0.8943 0.01157 0.00591 -0.0870 0.2328 1.0000 5.500 0.9001 0.01235 0.00639 -0.0829 0.1740 1.0000 5.750 0.9096 0.01303 0.00683 -0.0795 0.1274 1.0000 6.000 0.9229 0.01357 0.00721 -0.0769 0.0997 1.0000 6.250 0.9394 0.01397 0.00754 -0.0749 0.0867 1.0000 6.500 0.9571 0.01432 0.00786 -0.0731 0.0790 1.0000 6.750 0.9744 0.01470 0.00820 -0.0713 0.0733 1.0000 7.000 0.9922 0.01506 0.00855 -0.0695 0.0690 1.0000 7.250 1.0113 0.01535 0.00886 -0.0680 0.0669 1.0000 7.500 1.0298 0.01568 0.00920 -0.0665 0.0647 1.0000 7.750 1.0472 0.01609 0.00958 -0.0647 0.0609 1.0000 8.000 1.0642 0.01651 0.01002 -0.0630 0.0583 1.0000 8.250 1.0835 0.01681 0.01035 -0.0616 0.0570 1.0000 8.500 1.1024 0.01713 0.01068 -0.0602 0.0549 1.0000 8.750 1.1203 0.01752 0.01107 -0.0587 0.0526 1.0000 9.000 1.1359 0.01805 0.01158 -0.0568 0.0488 1.0000 9.250 1.1553 0.01836 0.01192 -0.0555 0.0477 1.0000 9.500 1.1741 0.01869 0.01227 -0.0542 0.0453 1.0000 9.750 1.1911 0.01914 0.01270 -0.0527 0.0424 1.0000 10.000 1.2081 0.01960 0.01317 -0.0511 0.0399 1.0000 10.250 1.2258 0.02001 0.01360 -0.0496 0.0373 1.0000 10.500 1.2417 0.02056 0.01412 -0.0479 0.0341 1.0000 10.750 1.2586 0.02102 0.01461 -0.0464 0.0319 1.0000 11.000 1.2739 0.02160 0.01516 -0.0448 0.0293 1.0000 11.250 1.2886 0.02223 0.01581 -0.0429 0.0272 1.0000 11.500 1.3041 0.02279 0.01640 -0.0413 0.0257 1.0000 11.750 1.3178 0.02349 0.01711 -0.0394 0.0241 1.0000 12.000 1.3311 0.02421 0.01786 -0.0376 0.0228 1.0000 12.250 1.3455 0.02487 0.01857 -0.0358 0.0218 1.0000 12.500 1.3594 0.02556 0.01929 -0.0341 0.0208 1.0000 12.750 1.3708 0.02643 0.02019 -0.0321 0.0198 1.0000 13.000 1.3805 0.02742 0.02123 -0.0299 0.0189 1.0000 13.250 1.3942 0.02813 0.02200 -0.0283 0.0182 1.0000 13.500 1.4060 0.02898 0.02291 -0.0265 0.0177 1.0000 13.750 1.4175 0.02986 0.02385 -0.0247 0.0172 1.0000 14.000 1.4277 0.03086 0.02488 -0.0228 0.0165 1.0000 14.250 1.4337 0.03217 0.02625 -0.0205 0.0159 1.0000 14.500 1.4387 0.03357 0.02773 -0.0182 0.0154 1.0000 14.750 1.4492 0.03458 0.02881 -0.0165 0.0151 1.0000 15.000 1.4596 0.03561 0.02991 -0.0149 0.0147 1.0000 15.250 1.4659 0.03697 0.03136 -0.0130 0.0145 1.0000 15.500 1.4758 0.03808 0.03252 -0.0115 0.0139 1.0000 15.750 1.4818 0.03950 0.03401 -0.0097 0.0137 1.0000 16.000 1.4878 0.04098 0.03554 -0.0080 0.0133 1.0000 16.250 1.4888 0.04291 0.03755 -0.0061 0.0130 1.0000 16.500 1.4848 0.04537 0.04011 -0.0040 0.0127 1.0000 16.750 1.4799 0.04799 0.04284 -0.0020 0.0125 1.0000 17.000 1.4878 0.04946 0.04439 -0.0010 0.0122 1.0000 17.250 1.4893 0.05161 0.04664 0.0003 0.0121 1.0000 17.500 1.4909 0.05380 0.04894 0.0014 0.0119 1.0000 17.750 1.4884 0.05650 0.05174 0.0025 0.0118 1.0000 18.000 1.4877 0.05909 0.05444 0.0033 0.0116 1.0000 18.250 1.4842 0.06206 0.05751 0.0040 0.0114 1.0000 18.500 1.4838 0.06478 0.06032 0.0044 0.0112 1.0000 18.750 1.4769 0.06843 0.06408 0.0046 0.0110 1.0000 19.000 1.4694 0.07229 0.06804 0.0044 0.0109 1.0000 19.250 1.4599 0.07661 0.07249 0.0039 0.0109 1.0000