Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

GOE 575 AIRFOIL (goe575-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: GOE 575 AIRFOIL (goe575-il)
Reynolds number: 500,000
Max Cl/Cd: 70.36 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe575-il-500000-n5.txt
Download as CSV file: xf-goe575-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 575 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -15.000  -1.0378   0.04310   0.03922  -0.0953   0.9890   0.0269
 -14.750  -1.0379   0.04115   0.03718  -0.0946   0.9878   0.0271
 -14.500  -1.0285   0.04010   0.03607  -0.0938   0.9869   0.0274
 -14.250  -1.0225   0.03869   0.03454  -0.0928   0.9859   0.0276
 -14.000  -1.0265   0.03724   0.03301  -0.0890   0.9828   0.0278
 -13.750  -1.0194   0.03646   0.03215  -0.0865   0.9810   0.0281
 -13.500  -1.0165   0.03524   0.03081  -0.0837   0.9793   0.0283
 -13.250  -1.0064   0.03447   0.02993  -0.0816   0.9781   0.0288
 -13.000  -0.9975   0.03347   0.02879  -0.0794   0.9771   0.0291
 -12.750  -0.9995   0.03256   0.02775  -0.0744   0.9737   0.0295
 -12.500  -0.9955   0.03160   0.02664  -0.0708   0.9712   0.0299
 -12.250  -0.9873   0.03071   0.02555  -0.0677   0.9695   0.0304
 -12.000  -0.9777   0.02972   0.02438  -0.0650   0.9682   0.0307
 -11.750  -0.9719   0.02912   0.02372  -0.0610   0.9659   0.0309
 -11.500  -0.9663   0.02874   0.02331  -0.0567   0.9628   0.0312
 -11.250  -0.9493   0.02837   0.02291  -0.0548   0.9609   0.0315
 -11.000  -0.9289   0.02825   0.02277  -0.0535   0.9596   0.0321
 -10.750  -0.9099   0.02772   0.02216  -0.0520   0.9586   0.0324
 -10.500  -0.8899   0.02715   0.02149  -0.0507   0.9578   0.0329
 -10.250  -0.8881   0.02659   0.02084  -0.0455   0.9538   0.0332
 -10.000  -0.8716   0.02604   0.02018  -0.0434   0.9514   0.0337
  -9.750  -0.8490   0.02535   0.01936  -0.0425   0.9495   0.0343
  -9.500  -0.8238   0.02470   0.01854  -0.0421   0.9482   0.0348
  -9.250  -0.7978   0.02392   0.01763  -0.0419   0.9473   0.0352
  -9.000  -0.7937   0.02344   0.01713  -0.0369   0.9420   0.0355
  -8.750  -0.7728   0.02298   0.01665  -0.0355   0.9399   0.0360
  -8.500  -0.7479   0.02246   0.01607  -0.0350   0.9383   0.0363
  -8.250  -0.7206   0.02194   0.01551  -0.0348   0.9370   0.0367
  -8.000  -0.6926   0.02141   0.01492  -0.0349   0.9360   0.0371
  -7.750  -0.6851   0.02105   0.01450  -0.0304   0.9298   0.0376
  -7.500  -0.6599   0.02057   0.01395  -0.0298   0.9273   0.0382
  -7.250  -0.6321   0.02007   0.01338  -0.0297   0.9256   0.0387
  -7.000  -0.6032   0.01953   0.01277  -0.0299   0.9244   0.0391
  -6.750  -0.5722   0.01908   0.01223  -0.0304   0.9234   0.0398
  -6.500  -0.5643   0.01876   0.01187  -0.0260   0.9165   0.0399
  -6.250  -0.5374   0.01818   0.01126  -0.0257   0.9141   0.0404
  -6.000  -0.5076   0.01763   0.01071  -0.0260   0.9122   0.0409
  -5.750  -0.4765   0.01719   0.01026  -0.0266   0.9107   0.0416
  -5.500  -0.4445   0.01674   0.00980  -0.0273   0.9095   0.0423
  -5.250  -0.4335   0.01652   0.00956  -0.0235   0.9015   0.0429
  -5.000  -0.4042   0.01608   0.00910  -0.0236   0.8984   0.0432
  -4.750  -0.3729   0.01563   0.00862  -0.0241   0.8961   0.0441
  -4.500  -0.3394   0.01516   0.00812  -0.0251   0.8939   0.0447
  -4.250  -0.3264   0.01491   0.00784  -0.0216   0.8820   0.0450
  -4.000  -0.2918   0.01444   0.00734  -0.0227   0.8776   0.0456
  -3.750  -0.2730   0.01411   0.00702  -0.0206   0.8654   0.0461
  -3.500  -0.2356   0.01356   0.00648  -0.0225   0.8599   0.0473
  -3.250  -0.2061   0.01322   0.00614  -0.0226   0.8470   0.0484
  -3.000  -0.1623   0.01272   0.00562  -0.0259   0.8353   0.0493
  -2.750  -0.1002   0.01209   0.00492  -0.0331   0.8146   0.0506
  -2.500  -0.0281   0.01152   0.00421  -0.0428   0.7796   0.0524
  -2.250   0.0180   0.01130   0.00380  -0.0468   0.7417   0.0545
  -2.000   0.0449   0.01131   0.00364  -0.0464   0.7106   0.0556
  -1.750   0.0683   0.01132   0.00354  -0.0453   0.6881   0.0573
  -1.500   0.0911   0.01133   0.00347  -0.0441   0.6702   0.0588
  -1.250   0.1143   0.01131   0.00339  -0.0430   0.6540   0.0613
  -1.000   0.1372   0.01126   0.00332  -0.0418   0.6375   0.0664
  -0.750   0.1611   0.01114   0.00330  -0.0409   0.6212   0.1010
  -0.500   0.1828   0.01115   0.00329  -0.0395   0.6047   0.1161
  -0.250   0.2040   0.01118   0.00330  -0.0380   0.5859   0.1286
   0.000   0.2251   0.01124   0.00331  -0.0364   0.5687   0.1365
   0.250   0.2468   0.01128   0.00333  -0.0350   0.5520   0.1485
   0.500   0.2676   0.01136   0.00335  -0.0334   0.5318   0.1558
   0.750   0.2887   0.01144   0.00338  -0.0320   0.5121   0.1684
   1.250   0.3315   0.01160   0.00348  -0.0291   0.4726   0.1955
   1.500   0.3538   0.01168   0.00353  -0.0279   0.4573   0.2066
   1.750   0.3765   0.01175   0.00358  -0.0269   0.4419   0.2245
   2.000   0.3999   0.01178   0.00365  -0.0260   0.4251   0.2534
   2.250   0.4286   0.01156   0.00377  -0.0265   0.4088   0.3899
   2.750   0.6926   0.01326   0.00682  -0.0734   0.3569   0.9811
   3.250   0.7776   0.01352   0.00693  -0.0801   0.3349   0.9891
   3.500   0.8427   0.01340   0.00674  -0.0885   0.3239   0.9973
   3.750   0.8814   0.01337   0.00663  -0.0911   0.3114   1.0000
   4.000   0.9015   0.01354   0.00675  -0.0895   0.3027   1.0000
   4.250   0.9219   0.01369   0.00687  -0.0880   0.2939   1.0000
   4.500   0.9421   0.01383   0.00700  -0.0864   0.2879   1.0000
   4.750   0.9619   0.01401   0.00713  -0.0848   0.2792   1.0000
   5.000   0.9814   0.01420   0.00728  -0.0831   0.2692   1.0000
   5.250   1.0014   0.01437   0.00744  -0.0815   0.2632   1.0000
   5.500   1.0209   0.01456   0.00760  -0.0799   0.2536   1.0000
   5.750   1.0396   0.01480   0.00778  -0.0781   0.2398   1.0000
   6.000   1.0582   0.01504   0.00798  -0.0763   0.2294   1.0000
   6.250   1.0762   0.01532   0.00819  -0.0744   0.2160   1.0000
   6.750   1.1118   0.01590   0.00868  -0.0706   0.1936   1.0000
   7.000   1.1286   0.01623   0.00895  -0.0685   0.1841   1.0000
   7.250   1.1456   0.01653   0.00924  -0.0665   0.1769   1.0000
   7.500   1.1622   0.01686   0.00954  -0.0644   0.1705   1.0000
   7.750   1.1791   0.01717   0.00984  -0.0623   0.1640   1.0000
   8.000   1.1957   0.01749   0.01015  -0.0603   0.1591   1.0000
   8.250   1.2123   0.01781   0.01048  -0.0582   0.1543   1.0000
   8.500   1.2290   0.01812   0.01080  -0.0562   0.1495   1.0000
   8.750   1.2443   0.01849   0.01118  -0.0540   0.1442   1.0000
   9.000   1.2599   0.01885   0.01155  -0.0518   0.1403   1.0000
   9.250   1.2759   0.01918   0.01191  -0.0497   0.1359   1.0000
   9.500   1.2909   0.01958   0.01231  -0.0475   0.1303   1.0000
   9.750   1.3052   0.02001   0.01274  -0.0452   0.1237   1.0000
  10.000   1.3181   0.02049   0.01321  -0.0428   0.1151   1.0000
  10.250   1.3306   0.02101   0.01372  -0.0403   0.1054   1.0000
  10.500   1.3409   0.02167   0.01431  -0.0374   0.0940   1.0000
  10.750   1.3498   0.02238   0.01498  -0.0345   0.0848   1.0000
  11.000   1.3589   0.02310   0.01569  -0.0316   0.0781   1.0000
  11.250   1.3688   0.02378   0.01639  -0.0289   0.0744   1.0000
  11.500   1.3772   0.02455   0.01718  -0.0260   0.0710   1.0000
  11.750   1.3864   0.02529   0.01795  -0.0234   0.0682   1.0000
  12.000   1.3960   0.02601   0.01873  -0.0209   0.0671   1.0000
  12.250   1.4035   0.02689   0.01963  -0.0181   0.0645   1.0000
  12.500   1.4100   0.02785   0.02063  -0.0154   0.0626   1.0000
  12.750   1.4154   0.02889   0.02173  -0.0126   0.0609   1.0000
  13.000   1.4242   0.02977   0.02267  -0.0104   0.0597   1.0000
  13.250   1.4314   0.03076   0.02373  -0.0081   0.0591   1.0000
  13.500   1.4373   0.03189   0.02493  -0.0057   0.0581   1.0000
  13.750   1.4431   0.03308   0.02618  -0.0035   0.0571   1.0000
  14.000   1.4473   0.03442   0.02760  -0.0013   0.0563   1.0000
  14.250   1.4514   0.03583   0.02909   0.0007   0.0562   1.0000
  14.500   1.4528   0.03752   0.03084   0.0027   0.0549   1.0000
  14.750   1.4511   0.03959   0.03296   0.0047   0.0533   1.0000
  15.000   1.4514   0.04158   0.03504   0.0063   0.0528   1.0000
  15.250   1.4548   0.04340   0.03695   0.0075   0.0521   1.0000
  15.500   1.4565   0.04544   0.03910   0.0086   0.0519   1.0000
  15.750   1.4574   0.04763   0.04138   0.0096   0.0515   1.0000
  16.000   1.4597   0.04974   0.04359   0.0104   0.0505   1.0000
  16.250   1.4582   0.05230   0.04625   0.0110   0.0500   1.0000
  16.500   1.4563   0.05500   0.04905   0.0115   0.0499   1.0000
  16.750   1.4527   0.05798   0.05211   0.0119   0.0485   1.0000
  17.000   1.4478   0.06119   0.05541   0.0120   0.0480   1.0000
  17.250   1.4425   0.06452   0.05883   0.0120   0.0472   1.0000
  17.500   1.4335   0.06837   0.06277   0.0117   0.0464   1.0000
  17.750   1.4272   0.07200   0.06651   0.0114   0.0465   1.0000
  18.000   1.4174   0.07614   0.07073   0.0107   0.0453   1.0000
  18.250   1.4093   0.08011   0.07481   0.0101   0.0451   1.0000
  18.500   1.4037   0.08381   0.07862   0.0094   0.0445   1.0000
  18.750   1.3975   0.08762   0.08255   0.0086   0.0440   1.0000
  19.000   1.3917   0.09144   0.08646   0.0078   0.0427   1.0000
  19.250   1.3826   0.09572   0.09086   0.0067   0.0429   1.0000
<< Back to GOE 575 AIRFOIL (goe575-il)

Polar data table (+)

Polar graphs


<< Back to GOE 575 AIRFOIL (goe575-il)