XFOIL Version 6.96 Calculated polar for: GOE 429 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -9.750 -0.8355 0.08282 0.07594 0.0086 1.0000 0.1842 -9.500 -0.8574 0.07452 0.06759 0.0040 1.0000 0.1829 -9.250 -0.8830 0.06583 0.05872 -0.0005 1.0000 0.1817 -9.000 -0.9031 0.05782 0.05026 -0.0038 1.0000 0.1823 -8.500 -0.8874 0.04959 0.04144 -0.0046 1.0000 0.1966 -8.250 -0.8717 0.04646 0.03812 -0.0045 1.0000 0.2052 -8.000 -0.8595 0.04259 0.03367 -0.0050 1.0000 0.2141 -7.750 -0.8366 0.04061 0.03172 -0.0045 1.0000 0.2246 -7.500 -0.8170 0.03784 0.02863 -0.0045 1.0000 0.2352 -7.250 -0.7957 0.03541 0.02583 -0.0045 1.0000 0.2477 -7.000 -0.7721 0.03354 0.02380 -0.0042 1.0000 0.2619 -6.750 -0.7475 0.03182 0.02202 -0.0039 1.0000 0.2773 -6.500 -0.7226 0.03037 0.02062 -0.0034 1.0000 0.2956 -6.250 -0.6973 0.02915 0.01950 -0.0026 1.0000 0.3165 -6.000 -0.6728 0.02797 0.01836 -0.0019 1.0000 0.3443 -5.750 -0.6482 0.02707 0.01760 -0.0008 1.0000 0.3766 -5.500 -0.6240 0.02652 0.01721 0.0007 1.0000 0.4116 -5.250 -0.5998 0.02608 0.01689 0.0023 1.0000 0.4455 -5.000 -0.5755 0.02578 0.01667 0.0040 1.0000 0.4767 -4.750 -0.5513 0.02546 0.01641 0.0056 1.0000 0.5058 -4.500 -0.5271 0.02517 0.01611 0.0070 1.0000 0.5347 -4.250 -0.5034 0.02532 0.01640 0.0096 1.0000 0.5589 -4.000 -0.4807 0.02545 0.01660 0.0121 1.0000 0.5871 -3.750 -0.4584 0.02544 0.01662 0.0144 1.0000 0.6160 -3.500 -0.4361 0.02537 0.01662 0.0170 1.0000 0.6397 -3.250 -0.4135 0.02478 0.01601 0.0182 1.0000 0.6652 -3.000 -0.3916 0.02435 0.01560 0.0202 1.0000 0.6874 -2.750 -0.3706 0.02371 0.01495 0.0214 1.0000 0.7129 -2.500 -0.3510 0.02323 0.01452 0.0237 1.0000 0.7350 -2.250 -0.3333 0.02261 0.01391 0.0253 1.0000 0.7605 -2.000 -0.3168 0.02214 0.01348 0.0279 1.0000 0.7826 -1.750 -0.3022 0.02160 0.01295 0.0300 1.0000 0.8084 -1.500 -0.2856 0.02118 0.01258 0.0324 1.0000 0.8323 -1.250 -0.2685 0.02076 0.01216 0.0341 1.0000 0.8596 -1.000 -0.2439 0.02046 0.01187 0.0347 1.0000 0.8888 -0.750 -0.1994 0.02035 0.01176 0.0316 1.0000 0.9200 -0.500 -0.1197 0.02040 0.01178 0.0219 1.0000 0.9515 -0.250 -0.0222 0.02026 0.01164 0.0079 1.0000 0.9793 0.000 0.0357 0.02001 0.01143 -0.0008 1.0000 1.0000 0.250 0.0032 0.01992 0.01134 0.0045 1.0000 1.0000 0.500 -0.0276 0.01968 0.01109 0.0096 1.0000 1.0000 0.750 0.0717 0.02020 0.01167 -0.0055 0.9702 1.0000 1.000 0.1953 0.02027 0.01192 -0.0224 0.9308 1.0000 1.250 0.2556 0.02024 0.01197 -0.0273 0.8876 1.0000 1.500 0.2787 0.02034 0.01210 -0.0254 0.8467 1.0000 1.750 0.2902 0.02048 0.01221 -0.0216 0.8067 1.0000 2.000 0.3005 0.02057 0.01223 -0.0172 0.7679 1.0000 2.250 0.3126 0.02063 0.01216 -0.0128 0.7303 1.0000 2.500 0.3279 0.02080 0.01221 -0.0093 0.6863 1.0000 2.750 0.3461 0.02095 0.01219 -0.0062 0.6430 1.0000 3.000 0.3668 0.02110 0.01214 -0.0035 0.6012 1.0000 3.250 0.3897 0.02139 0.01226 -0.0018 0.5606 1.0000 3.500 0.4141 0.02180 0.01249 -0.0004 0.5259 1.0000 3.750 0.4394 0.02235 0.01287 0.0006 0.4965 1.0000 4.000 0.4654 0.02302 0.01340 0.0013 0.4724 1.0000 4.250 0.4922 0.02389 0.01418 0.0016 0.4530 1.0000 4.500 0.5193 0.02491 0.01522 0.0017 0.4354 1.0000 4.750 0.5462 0.02594 0.01625 0.0018 0.4202 1.0000 5.000 0.5731 0.02703 0.01740 0.0019 0.4065 1.0000 5.250 0.5994 0.02813 0.01859 0.0020 0.3913 1.0000 5.500 0.6245 0.02889 0.01930 0.0026 0.3724 1.0000 5.750 0.6487 0.02955 0.02006 0.0032 0.3491 1.0000 6.000 0.6732 0.03000 0.02040 0.0042 0.3274 1.0000 6.250 0.6969 0.03066 0.02110 0.0049 0.3036 1.0000 6.500 0.7209 0.03115 0.02146 0.0060 0.2777 1.0000 6.750 0.7434 0.03225 0.02247 0.0070 0.2443 1.0000 7.000 0.7640 0.03418 0.02447 0.0078 0.2083 1.0000 7.250 0.7860 0.03626 0.02660 0.0084 0.1870 1.0000 7.500 0.8068 0.03916 0.02979 0.0087 0.1748 1.0000 7.750 0.8287 0.04149 0.03214 0.0091 0.1659 1.0000 8.000 0.8434 0.04511 0.03631 0.0089 0.1582 1.0000 8.250 0.8655 0.04724 0.03833 0.0094 0.1521 1.0000 8.500 0.8692 0.05280 0.04459 0.0085 0.1499 1.0000 8.750 0.8663 0.05899 0.05129 0.0071 0.1491 1.0000 9.000 0.8538 0.06603 0.05870 0.0046 0.1497 1.0000 9.250 0.8372 0.07335 0.06622 0.0015 0.1509 1.0000 9.500 0.8242 0.08026 0.07321 -0.0017 0.1521 1.0000