XFOIL Version 6.94 Calculated polar for: S4233-136-84 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 0.3557 0.00964 0.00389 -0.0729 0.6899 0.7874 0.500 0.4087 0.00963 0.00394 -0.0721 0.6776 0.8201 1.000 0.4607 0.00964 0.00397 -0.0710 0.6661 0.8554 1.500 0.5113 0.00962 0.00397 -0.0694 0.6540 0.8952 2.000 0.5669 0.00961 0.00403 -0.0690 0.6408 0.9408 2.500 0.6461 0.00968 0.00407 -0.0740 0.6271 0.9796 3.000 0.7195 0.00979 0.00411 -0.0783 0.6130 1.0000 3.500 0.7684 0.01001 0.00424 -0.0773 0.5991 1.0000 4.000 0.8202 0.01023 0.00442 -0.0769 0.5840 1.0000 4.500 0.8725 0.01047 0.00468 -0.0764 0.5680 1.0000 5.000 0.9248 0.01074 0.00497 -0.0760 0.5511 1.0000 5.500 0.9765 0.01104 0.00527 -0.0754 0.5327 1.0000 6.000 1.0273 0.01138 0.00564 -0.0747 0.5127 1.0000 6.500 1.0762 0.01172 0.00606 -0.0737 0.4886 1.0000 7.000 1.1232 0.01218 0.00650 -0.0723 0.4624 1.0000 7.500 1.1662 0.01273 0.00704 -0.0703 0.4284 1.0000 8.000 1.2048 0.01344 0.00774 -0.0677 0.3873 1.0000 8.500 1.2361 0.01446 0.00863 -0.0641 0.3413 1.0000 9.000 1.2552 0.01579 0.00977 -0.0587 0.2869 1.0000 9.500 1.2623 0.01766 0.01140 -0.0520 0.2299 1.0000 10.000 1.2664 0.02016 0.01366 -0.0461 0.1742 1.0000 10.500 1.2660 0.02340 0.01662 -0.0409 0.1190 1.0000 11.000 1.2604 0.02750 0.02043 -0.0363 0.0694 1.0000 11.500 1.2456 0.03286 0.02555 -0.0321 0.0323 1.0000 12.000 1.2431 0.03772 0.03049 -0.0295 0.0240 1.0000 12.500 1.2419 0.04283 0.03581 -0.0277 0.0213 1.0000 13.000 1.2433 0.04806 0.04123 -0.0267 0.0197 1.0000 13.500 1.2423 0.05389 0.04723 -0.0262 0.0185 1.0000 14.000 1.2321 0.06103 0.05451 -0.0260 0.0175 1.0000 14.500 1.2375 0.06664 0.06032 -0.0260 0.0170 1.0000 15.000 1.2444 0.07217 0.06606 -0.0261 0.0164 1.0000 15.500 1.2524 0.07777 0.07186 -0.0264 0.0157 1.0000 16.000 1.2595 0.08367 0.07798 -0.0271 0.0151 1.0000 16.500 1.2643 0.09010 0.08461 -0.0285 0.0145 1.0000 17.000 1.2682 0.09681 0.09154 -0.0299 0.0141 1.0000 17.500 1.2675 0.10447 0.09948 -0.0321 0.0139 1.0000 18.000 1.2601 0.11361 0.10895 -0.0354 0.0137 1.0000 18.500 1.2447 0.12462 0.12034 -0.0406 0.0138 1.0000 19.000 1.2223 0.13752 0.13362 -0.0477 0.0138 1.0000 19.500 1.1874 0.15433 0.15090 -0.0581 0.0141 1.0000 20.000 1.0412 0.20915 0.20649 -0.0918 0.0167 1.0000