XFOIL Version 6.96 Calculated polar for: NACA 0012-34 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 ------ -------- --------- --------- -------- -------- -------- -11.250 -0.6411 0.08921 0.08427 -0.0362 1.0000 0.0199 -11.000 -0.6607 0.08149 0.07649 -0.0414 1.0000 0.0195 -10.750 -0.6820 0.07531 0.07020 -0.0446 1.0000 0.0191 -10.500 -0.7031 0.07030 0.06506 -0.0458 1.0000 0.0188 -10.250 -0.7230 0.06622 0.06083 -0.0452 1.0000 0.0187 -10.000 -0.7420 0.06276 0.05721 -0.0431 1.0000 0.0185 -9.750 -0.7600 0.05983 0.05411 -0.0395 1.0000 0.0185 -9.500 -0.7756 0.05706 0.05115 -0.0353 1.0000 0.0185 -9.250 -0.7869 0.05416 0.04801 -0.0312 1.0000 0.0185 -9.000 -0.7955 0.05127 0.04485 -0.0270 1.0000 0.0185 -8.750 -0.8013 0.04838 0.04166 -0.0227 1.0000 0.0184 -8.500 -0.8038 0.04554 0.03849 -0.0186 1.0000 0.0184 -8.250 -0.8031 0.04281 0.03540 -0.0146 1.0000 0.0184 -8.000 -0.7991 0.04019 0.03242 -0.0109 1.0000 0.0185 -7.750 -0.7916 0.03769 0.02956 -0.0076 1.0000 0.0187 -7.500 -0.7805 0.03534 0.02685 -0.0047 1.0000 0.0191 -7.250 -0.7665 0.03323 0.02434 -0.0022 1.0000 0.0198 -7.000 -0.7506 0.03147 0.02229 0.0000 1.0000 0.0214 -6.750 -0.7323 0.02979 0.02033 0.0019 1.0000 0.0228 -6.500 -0.7129 0.02814 0.01847 0.0036 1.0000 0.0237 -6.250 -0.6950 0.02675 0.01692 0.0055 1.0000 0.0246 -6.000 -0.6820 0.02518 0.01534 0.0080 1.0000 0.0262 -5.750 -0.6698 0.02417 0.01433 0.0105 1.0000 0.0291 -5.500 -0.6573 0.02325 0.01330 0.0132 1.0000 0.0322 -5.250 -0.6449 0.02237 0.01226 0.0159 1.0000 0.0347 -5.000 -0.6327 0.02142 0.01121 0.0185 1.0000 0.0402 -4.750 -0.6186 0.02056 0.01029 0.0208 1.0000 0.0495 -4.500 -0.6043 0.01958 0.00940 0.0231 1.0000 0.0733 -4.250 -0.5972 0.01752 0.00850 0.0258 1.0000 0.2575 -4.000 -0.5828 0.01587 0.00813 0.0276 0.9973 0.4949 -3.750 -0.5591 0.01537 0.00845 0.0292 0.9940 0.6666 -3.500 -0.5310 0.01563 0.00890 0.0305 0.9900 0.7561 -3.250 -0.4964 0.01587 0.00898 0.0295 0.9865 0.7857 -3.000 -0.4626 0.01604 0.00898 0.0284 0.9821 0.8050 -2.750 -0.4273 0.01622 0.00896 0.0269 0.9781 0.8232 -2.500 -0.3926 0.01639 0.00897 0.0255 0.9738 0.8389 -2.250 -0.3574 0.01656 0.00899 0.0239 0.9691 0.8521 -2.000 -0.3178 0.01675 0.00903 0.0214 0.9657 0.8631 -1.750 -0.2826 0.01690 0.00906 0.0198 0.9605 0.8736 -1.500 -0.2459 0.01702 0.00907 0.0178 0.9556 0.8839 -1.250 -0.2034 0.01717 0.00911 0.0145 0.9523 0.8920 -1.000 -0.1670 0.01728 0.00915 0.0126 0.9465 0.9001 -0.750 -0.1289 0.01735 0.00915 0.0102 0.9413 0.9090 -0.250 -0.0453 0.01750 0.00923 0.0039 0.9314 0.9218 0.000 0.0000 0.01751 0.00923 0.0000 0.9268 0.9268 0.250 0.0453 0.01749 0.00923 -0.0039 0.9218 0.9314 0.750 0.1290 0.01734 0.00915 -0.0102 0.9090 0.9413 1.000 0.1670 0.01728 0.00915 -0.0126 0.9001 0.9465 1.250 0.2034 0.01716 0.00911 -0.0145 0.8921 0.9524 1.500 0.2459 0.01701 0.00907 -0.0178 0.8839 0.9556 1.750 0.2826 0.01690 0.00906 -0.0198 0.8736 0.9606 2.000 0.3178 0.01675 0.00903 -0.0214 0.8631 0.9657 2.250 0.3574 0.01655 0.00899 -0.0239 0.8521 0.9691 2.500 0.3926 0.01638 0.00896 -0.0255 0.8389 0.9738 2.750 0.4273 0.01622 0.00896 -0.0269 0.8232 0.9781 3.000 0.4626 0.01604 0.00898 -0.0284 0.8050 0.9822 3.250 0.4964 0.01587 0.00898 -0.0295 0.7857 0.9866 3.500 0.5310 0.01563 0.00890 -0.0305 0.7561 0.9901 3.750 0.5591 0.01536 0.00845 -0.0292 0.6665 0.9940 4.000 0.5828 0.01587 0.00813 -0.0276 0.4951 0.9974 4.250 0.5970 0.01752 0.00850 -0.0258 0.2577 1.0000 4.500 0.6042 0.01957 0.00939 -0.0231 0.0734 1.0000 4.750 0.6185 0.02055 0.01028 -0.0208 0.0496 1.0000 5.000 0.6326 0.02141 0.01121 -0.0185 0.0403 1.0000 5.250 0.6448 0.02236 0.01225 -0.0159 0.0347 1.0000 5.500 0.6572 0.02325 0.01329 -0.0131 0.0322 1.0000 5.750 0.6697 0.02417 0.01432 -0.0105 0.0292 1.0000 6.000 0.6819 0.02517 0.01534 -0.0080 0.0262 1.0000 6.250 0.6949 0.02674 0.01691 -0.0055 0.0246 1.0000 6.500 0.7128 0.02813 0.01846 -0.0036 0.0237 1.0000 6.750 0.7322 0.02978 0.02032 -0.0019 0.0228 1.0000 7.000 0.7504 0.03146 0.02227 0.0000 0.0214 1.0000 7.250 0.7664 0.03322 0.02433 0.0022 0.0198 1.0000 7.500 0.7804 0.03533 0.02683 0.0047 0.0191 1.0000 7.750 0.7915 0.03768 0.02954 0.0076 0.0187 1.0000 8.000 0.7990 0.04018 0.03240 0.0109 0.0185 1.0000 8.250 0.8031 0.04280 0.03539 0.0146 0.0184 1.0000 8.500 0.8038 0.04554 0.03849 0.0186 0.0184 1.0000 8.750 0.8013 0.04838 0.04166 0.0227 0.0184 1.0000 9.000 0.7956 0.05127 0.04485 0.0270 0.0185 1.0000 9.250 0.7871 0.05416 0.04802 0.0312 0.0185 1.0000 9.500 0.7758 0.05708 0.05117 0.0352 0.0185 1.0000 9.750 0.7603 0.05985 0.05413 0.0394 0.0185 1.0000 10.000 0.7423 0.06278 0.05723 0.0430 0.0185 1.0000 10.250 0.7234 0.06625 0.06087 0.0451 0.0187 1.0000 10.500 0.7035 0.07036 0.06512 0.0457 0.0188 1.0000 10.750 0.6825 0.07538 0.07027 0.0445 0.0191 1.0000 11.000 0.6613 0.08158 0.07658 0.0412 0.0195 1.0000 11.250 0.6418 0.08931 0.08438 0.0360 0.0199 1.0000