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GOE 380 AIRFOIL (goe380-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 380 AIRFOIL (goe380-il)
Reynolds number: 100,000
Max Cl/Cd: 54.41 at α=8.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe380-il-100000.txt
Download as CSV file: xf-goe380-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 380 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.3113   0.11163   0.10690  -0.0258   1.0000   0.0425
  -8.250  -0.3154   0.11072   0.10608  -0.0264   1.0000   0.0426
  -8.000  -0.3195   0.10969   0.10516  -0.0273   1.0000   0.0427
  -7.750  -0.3180   0.10814   0.10367  -0.0291   1.0000   0.0428
  -7.500  -0.3153   0.10645   0.10203  -0.0310   1.0000   0.0429
  -7.250  -0.3030   0.09598   0.09161  -0.0232   1.0000   0.0444
  -7.000  -0.3000   0.09285   0.08853  -0.0219   1.0000   0.0454
  -6.750  -0.2992   0.09038   0.08610  -0.0212   1.0000   0.0463
  -6.500  -0.2993   0.08814   0.08393  -0.0205   1.0000   0.0473
  -6.250  -0.2998   0.08602   0.08187  -0.0200   1.0000   0.0482
  -6.000  -0.3004   0.08393   0.07985  -0.0195   1.0000   0.0494
  -5.750  -0.3005   0.08193   0.07790  -0.0191   1.0000   0.0505
  -5.500  -0.2995   0.07995   0.07596  -0.0190   1.0000   0.0516
  -5.250  -0.2954   0.07816   0.07420  -0.0200   1.0000   0.0534
  -5.000  -0.2822   0.07751   0.07349  -0.0240   1.0000   0.0549
  -4.750  -0.2624   0.07755   0.07334  -0.0289   1.0000   0.0555
  -4.500  -0.2620   0.07289   0.06879  -0.0271   1.0000   0.0560
  -4.250  -0.2696   0.06842   0.06448  -0.0225   1.0000   0.0577
  -4.000  -0.2651   0.06590   0.06200  -0.0214   1.0000   0.0596
  -3.750  -0.2035   0.06277   0.05859  -0.0329   0.9913   0.0677
  -3.500  -0.1565   0.05779   0.05346  -0.0408   0.9834   0.0700
  -3.250  -0.1243   0.05337   0.04900  -0.0444   0.9740   0.0742
  -3.000  -0.0576   0.05165   0.04673  -0.0540   0.9635   0.0823
  -2.750  -0.0257   0.04600   0.04119  -0.0575   0.9563   0.0858
  -2.500   0.0303   0.04401   0.03871  -0.0636   0.9442   0.0955
  -2.250   0.0661   0.03949   0.03424  -0.0668   0.9329   0.1009
  -2.000   0.1136   0.03642   0.03088  -0.0711   0.9219   0.1133
  -1.750   0.1654   0.03341   0.02756  -0.0761   0.9140   0.1367
  -1.500   0.2047   0.03081   0.02477  -0.0786   0.9022   0.1650
  -1.000   0.2765   0.02609   0.01978  -0.0817   0.8783   0.2563
  -0.750   0.3450   0.02377   0.01609  -0.0831   0.8710   0.0932
  -0.500   0.3833   0.02159   0.01354  -0.0837   0.8583   0.0891
  -0.250   0.4195   0.02008   0.01157  -0.0837   0.8441   0.0964
   0.000   0.4508   0.01867   0.01001  -0.0834   0.8277   0.1181
   0.250   0.4804   0.01740   0.00873  -0.0832   0.8104   0.1571
   0.500   0.5102   0.01659   0.00789  -0.0828   0.7932   0.1802
   0.750   0.5406   0.01608   0.00727  -0.0824   0.7761   0.1970
   1.250   0.6323   0.01375   0.00635  -0.0888   0.7387   1.0000
   1.500   0.6574   0.01391   0.00617  -0.0876   0.7208   1.0000
   1.750   0.6827   0.01408   0.00607  -0.0865   0.7036   1.0000
   2.000   0.7063   0.01430   0.00610  -0.0853   0.6849   1.0000
   2.250   0.7303   0.01454   0.00616  -0.0842   0.6668   1.0000
   2.500   0.7548   0.01479   0.00623  -0.0832   0.6497   1.0000
   2.750   0.7794   0.01508   0.00632  -0.0822   0.6331   1.0000
   3.000   0.8027   0.01541   0.00655  -0.0811   0.6151   1.0000
   3.250   0.8263   0.01577   0.00679  -0.0801   0.5978   1.0000
   3.500   0.8500   0.01611   0.00704  -0.0791   0.5804   1.0000
   3.750   0.8738   0.01647   0.00724  -0.0780   0.5635   1.0000
   4.000   0.8969   0.01685   0.00753  -0.0770   0.5468   1.0000
   4.250   0.9201   0.01726   0.00789  -0.0760   0.5314   1.0000
   4.500   0.9436   0.01769   0.00827  -0.0751   0.5175   1.0000
   4.750   0.9673   0.01812   0.00873  -0.0743   0.5043   1.0000
   5.000   0.9912   0.01855   0.00912  -0.0735   0.4917   1.0000
   5.250   1.0139   0.01897   0.00958  -0.0725   0.4786   1.0000
   5.500   1.0366   0.01938   0.01005  -0.0716   0.4656   1.0000
   5.750   1.0592   0.01980   0.01054  -0.0706   0.4529   1.0000
   6.000   1.0818   0.02022   0.01109  -0.0696   0.4403   1.0000
   6.250   1.1043   0.02063   0.01157  -0.0686   0.4275   1.0000
   6.500   1.1266   0.02104   0.01205  -0.0675   0.4142   1.0000
   6.750   1.1488   0.02149   0.01258  -0.0665   0.4009   1.0000
   7.000   1.1708   0.02198   0.01320  -0.0654   0.3872   1.0000
   7.250   1.1925   0.02252   0.01383  -0.0643   0.3731   1.0000
   7.500   1.2131   0.02296   0.01434  -0.0629   0.3569   1.0000
   7.750   1.2300   0.02301   0.01435  -0.0609   0.3347   1.0000
   8.000   1.2451   0.02313   0.01453  -0.0587   0.3126   1.0000
   8.250   1.2599   0.02335   0.01488  -0.0565   0.2922   1.0000
   8.500   1.2709   0.02337   0.01509  -0.0538   0.2648   1.0000
   8.750   1.2825   0.02357   0.01543  -0.0511   0.2287   1.0000
   9.000   1.2884   0.02466   0.01619  -0.0478   0.1651   1.0000
   9.250   1.2821   0.02730   0.01801  -0.0438   0.0701   1.0000
   9.500   1.2785   0.02967   0.02013  -0.0398   0.0515   1.0000
   9.750   1.2784   0.03141   0.02200  -0.0360   0.0471   1.0000
  10.000   1.2769   0.03321   0.02398  -0.0325   0.0445   1.0000
  10.250   1.2713   0.03535   0.02629  -0.0290   0.0424   1.0000
  10.500   1.2643   0.03773   0.02882  -0.0261   0.0412   1.0000
  10.750   1.2560   0.04043   0.03166  -0.0237   0.0403   1.0000
  11.000   1.2489   0.04330   0.03465  -0.0218   0.0393   1.0000
  11.250   1.2474   0.04590   0.03742  -0.0204   0.0378   1.0000
  11.500   1.2469   0.04856   0.04021  -0.0192   0.0363   1.0000
  11.750   1.2499   0.05107   0.04287  -0.0179   0.0351   1.0000
  12.000   1.2607   0.05315   0.04503  -0.0161   0.0345   1.0000
  12.250   1.2802   0.05515   0.04713  -0.0141   0.0341   1.0000
  12.500   1.3019   0.05776   0.04995  -0.0124   0.0340   1.0000
  12.750   1.3130   0.06106   0.05356  -0.0111   0.0345   1.0000
  13.000   1.3154   0.06488   0.05771  -0.0102   0.0351   1.0000
  13.250   1.3103   0.06908   0.06222  -0.0097   0.0357   1.0000
  13.500   1.3008   0.07352   0.06695  -0.0098   0.0361   1.0000
  13.750   1.2875   0.07840   0.07210  -0.0105   0.0365   1.0000
  14.000   1.2719   0.08360   0.07756  -0.0119   0.0367   1.0000
  14.250   1.2543   0.08927   0.08347  -0.0140   0.0368   1.0000
  14.500   1.2367   0.09539   0.08981  -0.0167   0.0373   1.0000
  14.750   1.2172   0.10199   0.09661  -0.0201   0.0376   1.0000
  15.000   1.1987   0.10892   0.10371  -0.0238   0.0381   1.0000
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