XFOIL Version 6.96 Calculated polar for: ONERA NACA CAMBRE AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -10.000 -0.4754 0.08074 0.07850 -0.0215 1.0000 0.0295 -9.750 -0.4903 0.07338 0.07117 -0.0253 1.0000 0.0297 -9.500 -0.5340 0.06085 0.05857 -0.0351 1.0000 0.0293 -9.250 -0.5710 0.05423 0.05182 -0.0381 1.0000 0.0291 -9.000 -0.5964 0.05017 0.04766 -0.0368 1.0000 0.0291 -8.750 -0.6114 0.04645 0.04383 -0.0348 1.0000 0.0294 -8.500 -0.6193 0.04271 0.03995 -0.0329 1.0000 0.0298 -8.250 -0.6249 0.03899 0.03607 -0.0305 1.0000 0.0307 -8.000 -0.6422 0.03612 0.03257 -0.0245 1.0000 0.0325 -7.750 -0.6584 0.02962 0.02578 -0.0204 1.0000 0.0331 -7.500 -0.6492 0.02701 0.02319 -0.0186 1.0000 0.0334 -7.250 -0.6413 0.02506 0.02121 -0.0162 1.0000 0.0338 -7.000 -0.6338 0.02342 0.01952 -0.0137 1.0000 0.0342 -6.750 -0.6262 0.02191 0.01793 -0.0110 1.0000 0.0347 -6.500 -0.6063 0.01994 0.01581 -0.0107 0.9985 0.0358 -6.250 -0.5707 0.01991 0.01525 -0.0114 0.9951 0.0393 -5.750 -0.5682 0.02019 0.01403 -0.0041 0.9957 0.0276 -5.500 -0.5333 0.01861 0.01230 -0.0057 0.9940 0.0276 -5.250 -0.5000 0.01726 0.01087 -0.0069 0.9910 0.0279 -5.000 -0.4654 0.01623 0.00981 -0.0084 0.9881 0.0284 -4.750 -0.4291 0.01547 0.00905 -0.0103 0.9856 0.0293 -4.500 -0.3908 0.01475 0.00830 -0.0126 0.9835 0.0305 -4.250 -0.3566 0.01397 0.00749 -0.0138 0.9785 0.0312 -4.000 -0.3189 0.01327 0.00676 -0.0158 0.9747 0.0320 -3.750 -0.2816 0.01259 0.00605 -0.0178 0.9710 0.0328 -3.500 -0.2539 0.01172 0.00521 -0.0178 0.9623 0.0342 -3.250 -0.2212 0.01126 0.00477 -0.0188 0.9563 0.0361 -3.000 -0.1943 0.01092 0.00442 -0.0184 0.9442 0.0380 -2.750 -0.1675 0.01057 0.00404 -0.0179 0.9305 0.0395 -2.500 -0.1426 0.01005 0.00350 -0.0170 0.9150 0.0426 -2.250 -0.1166 0.00979 0.00320 -0.0163 0.8992 0.0460 -2.000 -0.0910 0.00948 0.00286 -0.0155 0.8823 0.0519 -1.750 -0.0655 0.00921 0.00257 -0.0148 0.8635 0.0648 -1.500 -0.0511 0.00737 0.00209 -0.0129 0.8420 0.4466 -1.250 -0.0313 0.00669 0.00197 -0.0112 0.8193 0.6073 -1.000 -0.0088 0.00641 0.00192 -0.0097 0.7966 0.6974 -0.750 0.0146 0.00624 0.00192 -0.0084 0.7732 0.7641 -0.500 0.0390 0.00619 0.00192 -0.0072 0.7499 0.8102 -0.250 0.0640 0.00619 0.00194 -0.0062 0.7269 0.8443 0.000 0.0887 0.00625 0.00198 -0.0051 0.7042 0.8761 0.250 0.1134 0.00637 0.00206 -0.0038 0.6820 0.9034 0.500 0.1387 0.00651 0.00213 -0.0028 0.6586 0.9238 0.750 0.1652 0.00669 0.00220 -0.0021 0.6337 0.9384 1.000 0.1946 0.00686 0.00226 -0.0022 0.6066 0.9484 1.250 0.2236 0.00704 0.00232 -0.0022 0.5800 0.9583 1.500 0.2573 0.00725 0.00239 -0.0033 0.5540 0.9646 1.750 0.2897 0.00742 0.00245 -0.0042 0.5298 0.9715 2.250 0.3651 0.00780 0.00259 -0.0085 0.4803 0.9780 2.500 0.3980 0.00801 0.00268 -0.0096 0.4549 0.9833 2.750 0.4364 0.00820 0.00274 -0.0120 0.4259 0.9854 3.000 0.4739 0.00839 0.00281 -0.0142 0.3970 0.9884 3.250 0.5097 0.00861 0.00290 -0.0161 0.3695 0.9919 3.750 0.5838 0.00903 0.00311 -0.0205 0.3227 0.9976 4.000 0.6199 0.00926 0.00322 -0.0225 0.2995 1.0000 4.250 0.6429 0.00945 0.00333 -0.0217 0.2822 1.0000 4.500 0.6659 0.00964 0.00346 -0.0209 0.2671 1.0000 4.750 0.6888 0.00982 0.00359 -0.0201 0.2531 1.0000 5.000 0.7117 0.01001 0.00374 -0.0192 0.2399 1.0000 5.250 0.7343 0.01021 0.00390 -0.0183 0.2273 1.0000 5.500 0.7568 0.01044 0.00409 -0.0174 0.2150 1.0000 5.750 0.7790 0.01070 0.00429 -0.0164 0.2031 1.0000 6.000 0.8012 0.01096 0.00450 -0.0154 0.1919 1.0000 6.250 0.8237 0.01119 0.00473 -0.0145 0.1818 1.0000 6.500 0.8458 0.01147 0.00498 -0.0135 0.1721 1.0000 6.750 0.8678 0.01177 0.00524 -0.0124 0.1624 1.0000 7.000 0.8902 0.01204 0.00551 -0.0115 0.1540 1.0000 7.250 0.9117 0.01241 0.00583 -0.0104 0.1454 1.0000 7.500 0.9342 0.01268 0.00610 -0.0095 0.1372 1.0000 7.750 0.9563 0.01301 0.00641 -0.0085 0.1289 1.0000 8.000 0.9783 0.01335 0.00673 -0.0076 0.1218 1.0000 8.250 1.0007 0.01369 0.00708 -0.0067 0.1164 1.0000 8.500 1.0238 0.01399 0.00740 -0.0060 0.1112 1.0000 8.750 1.0451 0.01446 0.00785 -0.0050 0.1060 1.0000 9.000 1.0690 0.01471 0.00817 -0.0045 0.1024 1.0000 9.250 1.0920 0.01505 0.00853 -0.0038 0.0976 1.0000 9.500 1.1137 0.01552 0.00899 -0.0030 0.0927 1.0000 9.750 1.1375 0.01579 0.00934 -0.0024 0.0885 1.0000 10.000 1.1594 0.01624 0.00978 -0.0017 0.0833 1.0000 10.250 1.1823 0.01659 0.01019 -0.0011 0.0784 1.0000 10.500 1.2037 0.01708 0.01065 -0.0003 0.0711 1.0000 10.750 1.2254 0.01754 0.01111 0.0004 0.0614 1.0000 11.000 1.2441 0.01827 0.01177 0.0014 0.0467 1.0000 11.250 1.2588 0.01933 0.01274 0.0030 0.0371 1.0000 11.500 1.2744 0.02024 0.01368 0.0045 0.0331 1.0000 11.750 1.2876 0.02129 0.01479 0.0062 0.0304 1.0000 12.000 1.3023 0.02214 0.01573 0.0078 0.0286 1.0000 12.250 1.3123 0.02316 0.01680 0.0099 0.0271 1.0000 12.500 1.3139 0.02460 0.01831 0.0130 0.0258 1.0000 12.750 1.3244 0.02557 0.01938 0.0148 0.0250 1.0000 13.000 1.3322 0.02675 0.02068 0.0166 0.0242 1.0000 13.250 1.3382 0.02815 0.02217 0.0182 0.0235 1.0000 13.500 1.3424 0.02978 0.02390 0.0196 0.0229 1.0000 13.750 1.3437 0.03180 0.02600 0.0207 0.0223 1.0000 14.000 1.3405 0.03444 0.02874 0.0214 0.0218 1.0000 14.250 1.3316 0.03792 0.03234 0.0215 0.0213 1.0000 14.500 1.3325 0.04067 0.03521 0.0211 0.0210 1.0000 14.750 1.3327 0.04368 0.03836 0.0203 0.0207 1.0000 15.000 1.3304 0.04714 0.04196 0.0192 0.0203 1.0000 15.250 1.3258 0.05103 0.04598 0.0178 0.0200 1.0000 15.500 1.3194 0.05529 0.05037 0.0160 0.0197 1.0000 15.750 1.3111 0.05990 0.05510 0.0141 0.0195 1.0000 16.000 1.3013 0.06477 0.06009 0.0121 0.0193 1.0000 16.250 1.2905 0.06984 0.06527 0.0099 0.0191 1.0000 16.500 1.2791 0.07510 0.07063 0.0076 0.0189 1.0000 16.750 1.2675 0.08049 0.07613 0.0052 0.0187 1.0000 17.000 1.2560 0.08591 0.08164 0.0028 0.0186 1.0000