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GOE 494 AIRFOIL (goe494-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: GOE 494 AIRFOIL (goe494-il)
Reynolds number: 1,000,000
Max Cl/Cd: 112.28 at α=1.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe494-il-1000000-n5.txt
Download as CSV file: xf-goe494-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 494 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.2947   0.08724   0.08562  -0.0479   0.9857   0.0032
  -8.000  -0.2842   0.08314   0.08153  -0.0514   0.9798   0.0033
  -7.750  -0.2737   0.07795   0.07634  -0.0563   0.9724   0.0035
  -7.500  -0.2531   0.07311   0.07150  -0.0634   0.9673   0.0037
  -7.250  -0.2278   0.06798   0.06635  -0.0719   0.9613   0.0039
  -7.000  -0.1967   0.06230   0.06063  -0.0823   0.9551   0.0042
  -6.750  -0.1653   0.05492   0.05320  -0.0950   0.9438   0.0049
  -6.500  -0.1294   0.04303   0.04116  -0.1145   0.9277   0.0055
  -6.250  -0.0751   0.01140   0.00737  -0.1477   0.9126   0.0059
  -5.750  -0.0204   0.00964   0.00524  -0.1482   0.9014   0.0081
  -5.500   0.0072   0.00929   0.00480  -0.1482   0.8961   0.0100
  -5.250   0.0349   0.01020   0.00588  -0.1479   0.8901   0.0117
  -5.000   0.0623   0.00992   0.00551  -0.1479   0.8843   0.0144
  -4.750   0.0898   0.01016   0.00573  -0.1477   0.8775   0.0171
  -4.500   0.1171   0.01018   0.00567  -0.1475   0.8706   0.0195
  -4.250   0.1444   0.01033   0.00577  -0.1474   0.8629   0.0214
  -4.000   0.1716   0.01049   0.00588  -0.1472   0.8553   0.0224
  -3.500   0.2258   0.01010   0.00525  -0.1470   0.8340   0.0244
  -3.250   0.2525   0.00942   0.00446  -0.1471   0.8206   0.0260
  -3.000   0.2793   0.00916   0.00410  -0.1469   0.8061   0.0270
  -2.750   0.3062   0.00882   0.00364  -0.1467   0.7927   0.0273
  -2.500   0.3331   0.00849   0.00318  -0.1465   0.7804   0.0274
  -2.250   0.3601   0.00825   0.00286  -0.1464   0.7695   0.0279
  -2.000   0.3871   0.00796   0.00247  -0.1462   0.7597   0.0276
  -1.750   0.4146   0.00767   0.00210  -0.1461   0.7519   0.0270
  -1.500   0.4419   0.00745   0.00180  -0.1460   0.7458   0.0265
  -1.250   0.4696   0.00727   0.00158  -0.1459   0.7405   0.0261
  -1.000   0.4972   0.00713   0.00140  -0.1459   0.7354   0.0257
  -0.750   0.5247   0.00702   0.00126  -0.1458   0.7312   0.0254
  -0.500   0.5524   0.00692   0.00114  -0.1457   0.7269   0.0252
  -0.250   0.5799   0.00685   0.00104  -0.1456   0.7210   0.0250
   0.000   0.6072   0.00679   0.00097  -0.1455   0.7144   0.0248
   0.250   0.6346   0.00674   0.00090  -0.1454   0.7075   0.0247
   0.500   0.6618   0.00671   0.00084  -0.1452   0.7005   0.0247
   0.750   0.6889   0.00669   0.00080  -0.1450   0.6906   0.0249
   1.000   0.7154   0.00672   0.00076  -0.1447   0.6739   0.0255
   1.250   0.7419   0.00675   0.00074  -0.1443   0.6513   0.0286
   1.500   0.7680   0.00684   0.00078  -0.1439   0.6249   0.0331
   1.750   0.7920   0.00712   0.00087  -0.1431   0.5696   0.0423
   2.000   0.8156   0.00729   0.00108  -0.1425   0.5136   0.1823
   2.250   0.8393   0.00762   0.00131  -0.1419   0.4565   0.2424
   2.500   0.8589   0.00844   0.00172  -0.1406   0.3298   0.3085
   2.750   0.8798   0.00916   0.00216  -0.1397   0.2286   0.3766
   3.000   0.9022   0.00960   0.00255  -0.1390   0.1552   0.4979
   3.500   0.9450   0.00996   0.00334  -0.1369   0.0366   1.0000
   3.750   0.9703   0.01023   0.00360  -0.1364   0.0271   1.0000
   4.000   0.9953   0.01055   0.00387  -0.1359   0.0170   1.0000
   4.250   1.0204   0.01085   0.00416  -0.1354   0.0115   1.0000
   4.500   1.0454   0.01115   0.00446  -0.1349   0.0095   1.0000
   4.750   1.0696   0.01156   0.00487  -0.1342   0.0071   1.0000
   5.000   1.0944   0.01188   0.00524  -0.1336   0.0064   1.0000
   5.250   1.1187   0.01225   0.00564  -0.1330   0.0057   1.0000
   5.500   1.1426   0.01268   0.00608  -0.1323   0.0050   1.0000
   5.750   1.1648   0.01334   0.00682  -0.1313   0.0044   1.0000
   6.000   1.1884   0.01378   0.00730  -0.1305   0.0041   1.0000
   6.250   1.2117   0.01424   0.00783  -0.1297   0.0037   1.0000
   6.500   1.2347   0.01473   0.00836  -0.1289   0.0034   1.0000
   6.750   1.2571   0.01528   0.00895  -0.1280   0.0031   1.0000
   7.000   1.2788   0.01592   0.00964  -0.1270   0.0029   1.0000
   7.250   1.2971   0.01704   0.01088  -0.1254   0.0026   1.0000
   7.500   1.3177   0.01785   0.01178  -0.1242   0.0026   1.0000
   7.750   1.3380   0.01868   0.01271  -0.1230   0.0024   1.0000
   8.000   1.3574   0.01968   0.01384  -0.1216   0.0023   1.0000
   8.250   1.3761   0.02086   0.01519  -0.1201   0.0022   1.0000
   8.500   1.3942   0.02221   0.01670  -0.1185   0.0020   1.0000
   8.750   1.4119   0.02374   0.01842  -0.1169   0.0019   1.0000
   9.000   1.4286   0.02555   0.02044  -0.1152   0.0018   1.0000
   9.250   1.4438   0.02780   0.02296  -0.1133   0.0018   1.0000
   9.500   1.4579   0.03005   0.02547  -0.1114   0.0017   1.0000
   9.750   1.4717   0.03190   0.02753  -0.1095   0.0016   1.0000
  10.000   1.4841   0.03367   0.02949  -0.1075   0.0016   1.0000
  10.250   1.4929   0.03595   0.03200  -0.1050   0.0015   1.0000
  10.500   1.4854   0.04151   0.03806  -0.1006   0.0015   1.0000
  10.750   1.4117   0.05654   0.05395  -0.0887   0.0014   1.0000
  11.000   1.3854   0.06128   0.05892  -0.0841   0.0014   1.0000
  11.250   1.3583   0.06653   0.06438  -0.0811   0.0014   1.0000
  11.500   1.3335   0.07200   0.07004  -0.0797   0.0014   1.0000
  11.750   1.3084   0.07818   0.07638  -0.0799   0.0014   1.0000
  12.000   1.2825   0.08527   0.08362  -0.0818   0.0015   1.0000
  12.250   1.2515   0.09449   0.09301  -0.0859   0.0015   1.0000
  12.500   1.2088   0.10944   0.10815  -0.0954   0.0015   1.0000
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