XFOIL Version 6.96 Calculated polar for: FX 63-147 AIRFOIL 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 ------ -------- --------- --------- -------- -------- -------- -10.500 -0.3677 0.10546 0.10057 -0.0485 1.0001 0.0283 -10.250 -0.3632 0.10313 0.09825 -0.0476 1.0001 0.0268 -9.750 -0.3925 0.08746 0.08273 -0.0552 1.0001 0.0225 -9.500 -0.3974 0.08409 0.07942 -0.0556 1.0001 0.0223 -9.250 -0.4085 0.07994 0.07533 -0.0568 1.0001 0.0220 -9.000 -0.4255 0.07598 0.07140 -0.0573 1.0001 0.0218 -8.750 -0.4470 0.07272 0.06817 -0.0565 1.0001 0.0216 -8.500 -0.4726 0.07029 0.06576 -0.0539 1.0001 0.0215 -8.000 -0.4819 0.06117 0.05631 -0.0602 0.9844 0.0207 -7.750 -0.4751 0.05572 0.05053 -0.0636 0.9731 0.0201 -7.500 -0.4680 0.05050 0.04488 -0.0652 0.9613 0.0193 -7.000 -0.4429 0.04130 0.03443 -0.0658 0.9384 0.0179 -6.750 -0.4186 0.03820 0.03096 -0.0670 0.9307 0.0178 -6.500 -0.3950 0.03546 0.02784 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3.250 0.6419 0.01953 0.01026 -0.0548 0.5698 0.9057 3.500 0.6678 0.01962 0.01030 -0.0548 0.5641 0.9099 3.750 0.6877 0.01969 0.01046 -0.0536 0.5567 0.9136 4.000 0.7129 0.01975 0.01050 -0.0533 0.5506 0.9169 4.250 0.7341 0.01986 0.01066 -0.0524 0.5436 0.9208 4.500 0.7578 0.01998 0.01080 -0.0520 0.5368 0.9243 4.750 0.7803 0.02006 0.01094 -0.0513 0.5301 0.9275 5.000 0.8012 0.02015 0.01109 -0.0503 0.5226 0.9312 5.250 0.8251 0.02027 0.01122 -0.0499 0.5161 0.9346 5.500 0.8449 0.02044 0.01151 -0.0489 0.5086 0.9385 5.750 0.8708 0.02053 0.01161 -0.0488 0.5029 0.9414 6.000 0.8887 0.02070 0.01194 -0.0474 0.4952 0.9453 6.250 0.9131 0.02086 0.01214 -0.0471 0.4891 0.9487 6.500 0.9336 0.02109 0.01249 -0.0462 0.4823 0.9523 6.750 0.9561 0.02123 0.01272 -0.0456 0.4750 0.9553 7.000 0.9770 0.02142 0.01303 -0.0448 0.4676 0.9589 7.250 0.9979 0.02159 0.01329 -0.0440 0.4593 0.9627 7.500 1.0167 0.02177 0.01360 -0.0428 0.4502 0.9665 7.750 1.0369 0.02184 0.01374 -0.0418 0.4396 0.9701 8.000 1.0530 0.02196 0.01394 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0.9999 13.750 1.1596 0.06898 0.06220 -0.0309 0.0602 0.9999 14.000 1.1515 0.07357 0.06682 -0.0323 0.0563 0.9999 14.250 1.1476 0.07768 0.07108 -0.0335 0.0525 0.9999 14.500 1.1444 0.08172 0.07527 -0.0348 0.0488 0.9999 14.750 1.1398 0.08608 0.07972 -0.0363 0.0460 0.9999 15.000 1.1364 0.09021 0.08394 -0.0376 0.0436 0.9999 15.250 1.1368 0.09393 0.08781 -0.0389 0.0410 0.9999