XFOIL Version 6.96 Calculated polar for: TH 25816 HALE 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 = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -19.750 -0.3379 0.08237 0.07775 -0.2099 0.9396 0.0130 -19.500 -0.3439 0.07791 0.07316 -0.2126 0.9391 0.0131 -19.250 -0.3472 0.07373 0.06882 -0.2154 0.9387 0.0132 -19.000 -0.3466 0.07008 0.06503 -0.2180 0.9383 0.0132 -18.750 -0.3452 0.06664 0.06145 -0.2204 0.9379 0.0133 -18.500 -0.3407 0.06365 0.05834 -0.2226 0.9376 0.0133 -18.250 -0.3371 0.06060 0.05517 -0.2247 0.9372 0.0135 -18.000 -0.3875 0.06125 0.05585 -0.2110 0.9297 0.0135 -17.750 -0.3877 0.05919 0.05370 -0.2106 0.9280 0.0134 -17.500 -0.3848 0.05687 0.05129 -0.2110 0.9271 0.0136 -17.250 -0.3763 0.05481 0.04917 -0.2121 0.9263 0.0137 -17.000 -0.3663 0.05274 0.04705 -0.2134 0.9257 0.0139 -16.750 -0.3544 0.05083 0.04506 -0.2147 0.9251 0.0139 -16.500 -0.3403 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3.250 0.5094 0.01333 0.00760 -0.0596 0.6644 0.7574 3.500 0.5381 0.01337 0.00764 -0.0604 0.6625 0.7602 3.750 0.5686 0.01339 0.00765 -0.0615 0.6606 0.7632 4.000 0.5769 0.01380 0.00811 -0.0585 0.6574 0.7674 4.250 0.5915 0.01411 0.00844 -0.0567 0.6542 0.7714 4.500 0.6094 0.01436 0.00873 -0.0554 0.6511 0.7741 4.750 0.6327 0.01450 0.00889 -0.0552 0.6486 0.7770 5.000 0.6603 0.01455 0.00894 -0.0559 0.6463 0.7800 5.250 0.6899 0.01457 0.00895 -0.0569 0.6441 0.7831 5.500 0.6935 0.01516 0.00960 -0.0531 0.6398 0.7873 5.750 0.7063 0.01556 0.01005 -0.0510 0.6359 0.7904 6.000 0.7263 0.01579 0.01030 -0.0503 0.6324 0.7933 6.250 0.7531 0.01585 0.01036 -0.0507 0.6296 0.7963 6.500 0.7721 0.01613 0.01066 -0.0499 0.6262 0.7997 6.750 0.7767 0.01681 0.01139 -0.0465 0.6209 0.8036 7.000 0.7934 0.01716 0.01175 -0.0452 0.6167 0.8065 7.250 0.8174 0.01728 0.01189 -0.0452 0.6133 0.8087 7.500 0.8325 0.01770 0.01234 -0.0437 0.6090 0.8114 7.750 0.8381 0.01844 0.01315 -0.0406 0.6030 0.8148 8.000 0.8561 0.01877 0.01347 -0.0396 0.5979 0.8180 8.250 0.8732 0.01915 0.01386 -0.0386 0.5927 0.8213 8.500 0.8795 0.01994 0.01470 -0.0358 0.5859 0.8241 8.750 0.8966 0.02031 0.01508 -0.0347 0.5801 0.8262 9.000 0.9049 0.02106 0.01588 -0.0323 0.5732 0.8286 9.250 0.9154 0.02173 0.01658 -0.0302 0.5652 0.8312 9.500 0.9244 0.02250 0.01736 -0.0280 0.5564 0.8341 9.750 0.9354 0.02319 0.01804 -0.0262 0.5469 0.8370 10.000 0.9418 0.02414 0.01900 -0.0237 0.5361 0.8399 10.250 0.9497 0.02499 0.01983 -0.0215 0.5235 0.8420 10.500 0.9527 0.02607 0.02089 -0.0185 0.5082 0.8440 10.750 0.9565 0.02716 0.02194 -0.0158 0.4920 0.8461 11.000 0.9567 0.02847 0.02320 -0.0127 0.4740 0.8484 11.250 0.9557 0.02988 0.02453 -0.0095 0.4538 0.8509 11.500 0.9561 0.03130 0.02590 -0.0066 0.4367 0.8534 11.750 0.9555 0.03281 0.02734 -0.0037 0.4179 0.8558 12.000 0.9558 0.03435 0.02881 -0.0011 0.4004 0.8578 12.250 0.9542 0.03598 0.03038 0.0017 0.3819 0.8594 12.500 0.9573 0.03738 0.03176 0.0039 0.3676 0.8610 12.750 0.9570 0.03904 0.03337 0.0064 0.3495 0.8627 13.000 0.9592 0.04059 0.03489 0.0084 0.3348 0.8646 13.250 0.9622 0.04213 0.03638 0.0103 0.3193 0.8665 13.500 0.9616 0.04395 0.03814 0.0125 0.3010 0.8684 13.750 0.9670 0.04542 0.03958 0.0139 0.2884 0.8700 14.000 0.9699 0.04712 0.04123 0.0155 0.2738 0.8718 14.250 0.9728 0.04884 0.04289 0.0170 0.2577 0.8734 14.500 0.9789 0.05039 0.04441 0.0181 0.2444 0.8748 14.750 0.9822 0.05208 0.04607 0.0195 0.2298 0.8763 15.000 0.9865 0.05371 0.04766 0.0207 0.2159 0.8776 15.250 0.9919 0.05533 0.04927 0.0218 0.2056 0.8790 15.500 0.9958 0.05707 0.05099 0.0229 0.1930 0.8804 15.750 1.0028 0.05862 0.05252 0.0237 0.1814 0.8819 16.000 1.0083 0.06032 0.05422 0.0245 0.1715 0.8834 16.250 1.0134 0.06208 0.05594 0.0252 0.1613 0.8850 16.500 1.0175 0.06395 0.05777 0.0260 0.1488 0.8864 16.750 1.0253 0.06556 0.05941 0.0264 0.1421 0.8880 17.000 1.0302 0.06744 0.06125 0.0269 0.1328 0.8893 17.250 1.0349 0.06938 0.06316 0.0274 0.1223 0.8904 17.500 1.0420 0.07108 0.06489 0.0277 0.1174 0.8916 17.750 1.0484 0.07282 0.06665 0.0281 0.1104 0.8929 18.000 1.0526 0.07481 0.06864 0.0285 0.1035 0.8940 18.250 1.0587 0.07665 0.07051 0.0288 0.0980 0.8951 18.500 1.0639 0.07860 0.07246 0.0290 0.0929 0.8961 18.750 1.0703 0.08046 0.07437 0.0290 0.0881 0.8972 19.000 1.0764 0.08239 0.07632 0.0290 0.0846 0.8983 19.250 1.0815 0.08442 0.07837 0.0290 0.0804 0.8996