XFOIL Version 6.96 Calculated polar for: NACA 642-015A AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -13.500 -0.8384 0.08370 0.07950 -0.0373 1.0000 0.0452 -13.250 -0.8593 0.07763 0.07333 -0.0394 1.0000 0.0445 -13.000 -0.8833 0.07183 0.06738 -0.0411 1.0000 0.0438 -12.750 -0.9096 0.06630 0.06164 -0.0419 1.0000 0.0429 -12.500 -1.0038 0.05676 0.05120 -0.0386 1.0000 0.0394 -12.250 -1.0205 0.05441 0.04855 -0.0354 1.0000 0.0390 -12.000 -1.0290 0.05232 0.04622 -0.0321 1.0000 0.0388 -11.750 -1.0299 0.04975 0.04339 -0.0297 1.0000 0.0387 -11.500 -1.0272 0.04641 0.03979 -0.0277 1.0000 0.0386 -11.250 -1.0232 0.04367 0.03677 -0.0255 1.0000 0.0386 -11.000 -1.0162 0.04102 0.03384 -0.0235 1.0000 0.0387 -10.750 -1.0008 0.03759 0.03017 -0.0228 1.0000 0.0391 -10.500 -0.9804 0.03515 0.02765 -0.0225 1.0000 0.0400 -10.250 -0.9627 0.03369 0.02612 -0.0217 1.0000 0.0411 -10.000 -0.9438 0.03229 0.02464 -0.0208 1.0000 0.0423 -9.750 -0.9239 0.03079 0.02299 -0.0199 1.0000 0.0434 -9.500 -0.9024 0.02930 0.02134 -0.0192 1.0000 0.0445 -9.250 -0.8812 0.02805 0.01992 -0.0183 1.0000 0.0456 -9.000 -0.8559 0.02639 0.01819 -0.0181 1.0000 0.0471 -8.750 -0.8351 0.02515 0.01704 -0.0174 1.0000 0.0492 -8.500 -0.8184 0.02433 0.01622 -0.0159 1.0000 0.0516 -8.250 -0.8025 0.02356 0.01538 -0.0141 1.0000 0.0541 -8.000 -0.7899 0.02243 0.01427 -0.0118 1.0000 0.0566 -7.750 -0.7829 0.02163 0.01354 -0.0086 1.0000 0.0592 -7.500 -0.7787 0.02108 0.01300 -0.0048 1.0000 0.0622 -7.250 -0.7777 0.02076 0.01262 -0.0003 1.0000 0.0652 -7.000 -0.7855 0.02010 0.01203 0.0052 1.0000 0.0683 -6.750 -0.7513 0.01911 0.01104 0.0028 0.9945 0.0783 -6.500 -0.7182 0.01788 0.00993 0.0005 0.9870 0.0946 -6.250 -0.6863 0.01656 0.00886 -0.0017 0.9796 0.1321 -6.000 -0.6631 0.01438 0.00759 -0.0030 0.9710 0.2740 -5.750 -0.6440 0.01290 0.00709 -0.0027 0.9603 0.4593 -5.500 -0.6085 0.01271 0.00703 -0.0043 0.9541 0.5252 -5.250 -0.5774 0.01267 0.00699 -0.0049 0.9446 0.5582 -5.000 -0.5434 0.01267 0.00695 -0.0060 0.9377 0.5833 -4.750 -0.5138 0.01271 0.00697 -0.0060 0.9281 0.6024 -4.500 -0.4837 0.01276 0.00697 -0.0062 0.9197 0.6189 -4.250 -0.4551 0.01279 0.00694 -0.0060 0.9105 0.6328 -4.000 -0.4286 0.01284 0.00692 -0.0054 0.9008 0.6460 -3.750 -0.4013 0.01296 0.00701 -0.0048 0.8925 0.6613 -3.500 -0.3762 0.01315 0.00719 -0.0038 0.8824 0.6757 -3.250 -0.3475 0.01323 0.00727 -0.0034 0.8749 0.6854 -3.000 -0.3229 0.01322 0.00718 -0.0026 0.8644 0.6948 -2.750 -0.2947 0.01323 0.00716 -0.0023 0.8572 0.7020 -2.500 -0.2700 0.01317 0.00702 -0.0018 0.8473 0.7101 -2.250 -0.2417 0.01313 0.00695 -0.0016 0.8401 0.7154 -2.000 -0.2159 0.01308 0.00684 -0.0013 0.8306 0.7221 -1.750 -0.1888 0.01300 0.00668 -0.0011 0.8235 0.7280 -1.500 -0.1619 0.01297 0.00666 -0.0009 0.8146 0.7334 -1.250 -0.1350 0.01291 0.00650 -0.0007 0.8083 0.7406 -1.000 -0.1083 0.01288 0.00650 -0.0006 0.7996 0.7459 -0.750 -0.0806 0.01285 0.00642 -0.0004 0.7930 0.7518 -0.500 -0.0548 0.01282 0.00636 -0.0002 0.7850 0.7592 -0.250 -0.0268 0.01281 0.00637 -0.0001 0.7784 0.7647 0.000 0.0000 0.01282 0.00636 0.0000 0.7721 0.7721 0.250 0.0268 0.01281 0.00637 0.0001 0.7647 0.7784 0.500 0.0548 0.01282 0.00636 0.0002 0.7592 0.7850 0.750 0.0806 0.01285 0.00642 0.0004 0.7518 0.7930 1.000 0.1083 0.01288 0.00650 0.0006 0.7459 0.7996 1.250 0.1350 0.01291 0.00650 0.0007 0.7406 0.8083 1.500 0.1619 0.01297 0.00666 0.0009 0.7334 0.8146 1.750 0.1888 0.01300 0.00668 0.0011 0.7280 0.8235 2.000 0.2159 0.01308 0.00684 0.0013 0.7221 0.8306 2.250 0.2417 0.01313 0.00695 0.0016 0.7154 0.8401 2.500 0.2700 0.01317 0.00702 0.0018 0.7101 0.8473 2.750 0.2947 0.01323 0.00716 0.0023 0.7020 0.8572 3.000 0.3229 0.01322 0.00718 0.0026 0.6948 0.8644 3.250 0.3475 0.01323 0.00727 0.0034 0.6854 0.8749 3.500 0.3762 0.01315 0.00719 0.0038 0.6758 0.8824 3.750 0.4014 0.01296 0.00701 0.0048 0.6613 0.8925 4.000 0.4287 0.01284 0.00692 0.0054 0.6460 0.9008 4.250 0.4551 0.01279 0.00694 0.0060 0.6328 0.9105 4.500 0.4837 0.01276 0.00697 0.0062 0.6189 0.9197 4.750 0.5138 0.01271 0.00697 0.0060 0.6023 0.9281 5.000 0.5433 0.01267 0.00695 0.0060 0.5833 0.9377 5.250 0.5775 0.01267 0.00699 0.0049 0.5582 0.9446 5.500 0.6084 0.01270 0.00703 0.0043 0.5252 0.9542 5.750 0.6440 0.01290 0.00709 0.0027 0.4595 0.9603 6.000 0.6632 0.01438 0.00759 0.0030 0.2741 0.9711 6.250 0.6863 0.01656 0.00886 0.0017 0.1321 0.9796 6.500 0.7183 0.01787 0.00993 -0.0005 0.0946 0.9870 6.750 0.7514 0.01911 0.01104 -0.0028 0.0782 0.9946 7.000 0.7853 0.02009 0.01203 -0.0052 0.0684 1.0000 7.250 0.7776 0.02076 0.01261 0.0004 0.0652 1.0000 7.500 0.7786 0.02108 0.01300 0.0048 0.0622 1.0000 7.750 0.7829 0.02163 0.01354 0.0086 0.0592 1.0000 8.000 0.7899 0.02242 0.01426 0.0118 0.0566 1.0000 8.250 0.8026 0.02356 0.01537 0.0141 0.0541 1.0000 8.500 0.8185 0.02433 0.01622 0.0159 0.0517 1.0000 8.750 0.8353 0.02515 0.01704 0.0174 0.0492 1.0000 9.000 0.8561 0.02639 0.01819 0.0181 0.0471 1.0000 9.250 0.8814 0.02805 0.01992 0.0182 0.0456 1.0000 9.500 0.9026 0.02930 0.02134 0.0191 0.0445 1.0000 9.750 0.9241 0.03079 0.02299 0.0199 0.0434 1.0000 10.000 0.9440 0.03230 0.02464 0.0207 0.0423 1.0000 10.250 0.9630 0.03368 0.02612 0.0216 0.0411 1.0000 10.500 0.9806 0.03515 0.02766 0.0225 0.0400 1.0000 10.750 1.0011 0.03759 0.03017 0.0227 0.0391 1.0000 11.000 1.0165 0.04103 0.03385 0.0235 0.0387 1.0000 11.250 1.0235 0.04368 0.03678 0.0255 0.0386 1.0000 11.500 1.0276 0.04643 0.03982 0.0276 0.0386 1.0000 11.750 1.0303 0.04978 0.04342 0.0296 0.0387 1.0000 12.000 1.0294 0.05234 0.04624 0.0320 0.0388 1.0000 12.250 1.0210 0.05443 0.04857 0.0353 0.0390 1.0000 12.500 1.0039 0.05679 0.05124 0.0386 0.0394 1.0000 12.750 0.9101 0.06640 0.06175 0.0417 0.0430 1.0000 13.000 0.8838 0.07194 0.06749 0.0409 0.0438 1.0000 13.250 0.8602 0.07772 0.07342 0.0392 0.0446 1.0000 13.500 0.8398 0.08376 0.07957 0.0371 0.0453 1.0000