GOE 429 AIRFOIL (goe429-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 429 AIRFOIL (goe429-il) Reynolds number: 50,000 Max Cl/Cd: 23.14 at α=6.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe429-il-50000.txt Download as CSV file: xf-goe429-il-50000.csv |
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
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Polar data table (+)
Polar graphs
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