XFOIL Version 6.96 Calculated polar for: FX 84-W-150 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -11.000 -0.2346 0.09459 0.08947 -0.0841 0.9522 0.0410 -10.750 -0.2341 0.08826 0.08313 -0.0894 0.9456 0.0413 -10.500 -0.2386 0.08161 0.07648 -0.0945 0.9371 0.0414 -10.250 -0.2519 0.07268 0.06755 -0.1016 0.9290 0.0413 -10.000 -0.2977 0.05851 0.05325 -0.1139 0.9148 0.0407 -9.750 -0.3339 0.05238 0.04688 -0.1170 0.9001 0.0403 -9.500 -0.3622 0.04853 0.04274 -0.1157 0.8876 0.0403 -9.250 -0.3782 0.04464 0.03845 -0.1144 0.8787 0.0407 -9.000 -0.3866 0.04123 0.03457 -0.1126 0.8697 0.0412 -8.750 -0.3886 0.03787 0.03059 -0.1108 0.8629 0.0423 -8.500 -0.3766 0.03647 0.02905 -0.1096 0.8558 0.0436 -8.250 -0.3590 0.03538 0.02782 -0.1088 0.8507 0.0452 -8.000 -0.3445 0.03390 0.02609 -0.1077 0.8447 0.0469 -7.750 -0.3298 0.03208 0.02387 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0.3108 1.0000 11.750 1.2668 0.04021 0.03270 -0.0413 0.2875 1.0000 12.000 1.2641 0.04250 0.03490 -0.0397 0.2641 1.0000 12.250 1.2596 0.04510 0.03742 -0.0383 0.2396 1.0000 12.500 1.2542 0.04795 0.04017 -0.0372 0.2161 1.0000 12.750 1.2472 0.05109 0.04320 -0.0362 0.1937 1.0000 13.000 1.2410 0.05436 0.04639 -0.0355 0.1718 1.0000 13.250 1.2340 0.05783 0.04979 -0.0349 0.1515 1.0000 13.500 1.2275 0.06140 0.05328 -0.0346 0.1339 1.0000 13.750 1.2218 0.06501 0.05684 -0.0344 0.1183 1.0000 14.000 1.2167 0.06865 0.06045 -0.0344 0.1056 1.0000 14.250 1.2118 0.07236 0.06412 -0.0345 0.0956 1.0000 14.500 1.2097 0.07580 0.06760 -0.0347 0.0870 1.0000 14.750 1.2077 0.07931 0.07114 -0.0350 0.0801 1.0000 15.000 1.2057 0.08286 0.07472 -0.0354 0.0745 1.0000 15.250 1.2057 0.08618 0.07809 -0.0358 0.0696 1.0000 15.500 1.2061 0.08950 0.08147 -0.0362 0.0652 1.0000 15.750 1.2055 0.09293 0.08489 -0.0368 0.0618 1.0000 16.000 1.2095 0.09578 0.08787 -0.0372 0.0582 1.0000