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GOE 400 AIRFOIL (goe400-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 400 AIRFOIL (goe400-il)
Reynolds number: 1,000,000
Max Cl/Cd: 126.02 at α=5.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe400-il-1000000.txt
Download as CSV file: xf-goe400-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 400 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.4170   0.09698   0.09545  -0.0001   1.0000   0.0169
  -8.000  -0.4112   0.09335   0.09183  -0.0025   1.0000   0.0170
  -7.750  -0.4050   0.08951   0.08801  -0.0053   1.0000   0.0170
  -7.500  -0.3945   0.08518   0.08368  -0.0095   1.0000   0.0171
  -7.250  -0.3867   0.08084   0.07936  -0.0121   1.0000   0.0176
  -7.000  -0.3712   0.07867   0.07720  -0.0139   1.0000   0.0179
  -6.750  -0.3546   0.07613   0.07465  -0.0166   1.0000   0.0185
  -6.500  -0.3356   0.07301   0.07153  -0.0206   0.9965   0.0195
  -6.250  -0.2927   0.06574   0.06418  -0.0351   0.9643   0.0216
  -6.000  -0.2442   0.04248   0.04056  -0.0395   0.8173   0.0222
  -5.750  -0.2264   0.04045   0.03840  -0.0407   0.7889   0.0226
  -5.500  -0.2068   0.03867   0.03652  -0.0419   0.7669   0.0232
  -5.250  -0.1850   0.03609   0.03385  -0.0445   0.7490   0.0243
  -5.000  -0.1692   0.04762   0.04521  -0.0551   0.7823   0.0274
  -4.500  -0.0919   0.01638   0.01228  -0.0772   0.7560   0.0271
  -4.250  -0.0644   0.01580   0.01148  -0.0771   0.7388   0.0275
  -4.000  -0.0383   0.01244   0.00748  -0.0777   0.7252   0.0286
  -3.750  -0.0110   0.01164   0.00650  -0.0777   0.7121   0.0293
  -3.500   0.0165   0.01104   0.00575  -0.0775   0.6999   0.0298
  -3.250   0.0443   0.01051   0.00508  -0.0774   0.6888   0.0301
  -3.000   0.0721   0.01005   0.00448  -0.0772   0.6786   0.0305
  -2.500   0.1279   0.00927   0.00350  -0.0769   0.6594   0.0315
  -2.250   0.1558   0.00899   0.00314  -0.0767   0.6507   0.0323
  -2.000   0.1838   0.00874   0.00281  -0.0766   0.6418   0.0332
  -1.750   0.2118   0.00850   0.00250  -0.0764   0.6337   0.0339
  -1.500   0.2398   0.00832   0.00225  -0.0762   0.6251   0.0345
  -1.250   0.2678   0.00816   0.00205  -0.0761   0.6172   0.0349
  -1.000   0.2958   0.00804   0.00187  -0.0759   0.6090   0.0352
  -0.750   0.3239   0.00777   0.00154  -0.0757   0.6010   0.0363
  -0.250   0.3800   0.00750   0.00120  -0.0754   0.5847   0.0406
   0.000   0.4079   0.00744   0.00111  -0.0752   0.5764   0.0438
   0.250   0.4359   0.00731   0.00103  -0.0751   0.5659   0.0631
   0.500   0.4640   0.00745   0.00122  -0.0749   0.5550   0.0908
   0.750   0.4920   0.00750   0.00127  -0.0748   0.5455   0.0973
   1.000   0.5200   0.00758   0.00132  -0.0747   0.5343   0.1013
   1.250   0.5479   0.00767   0.00138  -0.0745   0.5223   0.1035
   1.500   0.5757   0.00763   0.00132  -0.0744   0.5099   0.1070
   1.750   0.6035   0.00766   0.00133  -0.0743   0.4964   0.1102
   2.000   0.6312   0.00773   0.00138  -0.0741   0.4839   0.1143
   2.250   0.6589   0.00779   0.00140  -0.0740   0.4719   0.1159
   2.750   0.7143   0.00786   0.00142  -0.0737   0.4465   0.1202
   3.000   0.7420   0.00791   0.00146  -0.0736   0.4343   0.1215
   3.250   0.7696   0.00798   0.00151  -0.0735   0.4217   0.1227
   3.500   0.7970   0.00808   0.00157  -0.0733   0.4064   0.1240
   3.750   0.8244   0.00818   0.00166  -0.0732   0.3925   0.1254
   4.000   0.8518   0.00830   0.00175  -0.0731   0.3777   0.1270
   4.250   0.8791   0.00843   0.00185  -0.0729   0.3629   0.1289
   4.500   0.9063   0.00857   0.00197  -0.0728   0.3488   0.1311
   4.750   0.9333   0.00873   0.00211  -0.0726   0.3310   0.1394
   5.000   0.9599   0.00871   0.00238  -0.0726   0.3098   0.3469
   5.250   0.9842   0.00781   0.00265  -0.0722   0.2844   1.0000
   5.500   1.0103   0.00816   0.00287  -0.0719   0.2554   1.0000
   5.750   1.0357   0.00863   0.00316  -0.0716   0.2177   1.0000
   6.000   1.0602   0.00925   0.00353  -0.0713   0.1726   1.0000
   6.250   1.0840   0.00998   0.00398  -0.0709   0.1231   1.0000
   6.500   1.1085   0.01058   0.00441  -0.0705   0.0945   1.0000
   6.750   1.1341   0.01093   0.00474  -0.0702   0.0850   1.0000
   7.000   1.1594   0.01135   0.00511  -0.0699   0.0754   1.0000
   7.250   1.1849   0.01170   0.00543  -0.0696   0.0645   1.0000
   7.500   1.2064   0.01273   0.00617  -0.0689   0.0239   1.0000
   7.750   1.2304   0.01332   0.00677  -0.0683   0.0188   1.0000
   8.000   1.2551   0.01376   0.00725  -0.0679   0.0171   1.0000
   8.250   1.2787   0.01436   0.00786  -0.0673   0.0152   1.0000
   8.500   1.3020   0.01498   0.00855  -0.0667   0.0140   1.0000
   8.750   1.3258   0.01547   0.00909  -0.0662   0.0133   1.0000
   9.000   1.3489   0.01602   0.00969  -0.0656   0.0126   1.0000
   9.250   1.3714   0.01664   0.01035  -0.0650   0.0119   1.0000
   9.500   1.3917   0.01753   0.01131  -0.0641   0.0111   1.0000
   9.750   1.4088   0.01877   0.01267  -0.0628   0.0105   1.0000
  10.000   1.4307   0.01934   0.01330  -0.0621   0.0102   1.0000
  10.250   1.4515   0.01998   0.01400  -0.0613   0.0098   1.0000
  10.500   1.4713   0.02071   0.01478  -0.0604   0.0093   1.0000
  10.750   1.4898   0.02152   0.01566  -0.0594   0.0090   1.0000
  11.000   1.5071   0.02239   0.01658  -0.0583   0.0086   1.0000
  11.250   1.5225   0.02339   0.01765  -0.0570   0.0083   1.0000
  11.500   1.5321   0.02483   0.01917  -0.0551   0.0080   1.0000
  11.750   1.5275   0.02706   0.02155  -0.0516   0.0077   1.0000
  12.000   1.5270   0.02895   0.02356  -0.0490   0.0076   1.0000
  12.250   1.5349   0.03031   0.02501  -0.0476   0.0075   1.0000
  12.500   1.5405   0.03201   0.02681  -0.0464   0.0074   1.0000
  12.750   1.5447   0.03402   0.02892  -0.0455   0.0073   1.0000
  13.000   1.5477   0.03634   0.03135  -0.0450   0.0072   1.0000
  13.250   1.5499   0.03888   0.03400  -0.0447   0.0071   1.0000
  13.500   1.5507   0.04168   0.03693  -0.0446   0.0069   1.0000
  13.750   1.5499   0.04475   0.04012  -0.0447   0.0068   1.0000
  14.000   1.5486   0.04795   0.04342  -0.0449   0.0067   1.0000
  14.250   1.5458   0.05139   0.04697  -0.0453   0.0066   1.0000
  14.500   1.5411   0.05513   0.05083  -0.0458   0.0065   1.0000
  14.750   1.5367   0.05888   0.05470  -0.0465   0.0064   1.0000
  15.000   1.5308   0.06293   0.05885  -0.0473   0.0064   1.0000
  15.250   1.5239   0.06717   0.06321  -0.0484   0.0063   1.0000
  15.500   1.5172   0.07152   0.06766  -0.0496   0.0062   1.0000
  15.750   1.5094   0.07624   0.07248  -0.0511   0.0061   1.0000
  16.000   1.5009   0.08115   0.07750  -0.0527   0.0061   1.0000
  16.250   1.4920   0.08631   0.08275  -0.0546   0.0060   1.0000
  16.500   1.4829   0.09163   0.08818  -0.0566   0.0059   1.0000
  16.750   1.4726   0.09723   0.09388  -0.0588   0.0059   1.0000
  17.000   1.4612   0.10312   0.09987  -0.0612   0.0058   1.0000
  17.250   1.4493   0.10921   0.10607  -0.0638   0.0058   1.0000
  17.500   1.4371   0.11548   0.11246  -0.0665   0.0058   1.0000
  17.750   1.4246   0.12189   0.11896  -0.0694   0.0057   1.0000
  18.000   1.4116   0.12855   0.12573  -0.0726   0.0057   1.0000
  18.250   1.3983   0.13545   0.13275  -0.0760   0.0057   1.0000
  18.500   1.3850   0.14253   0.13994  -0.0797   0.0056   1.0000
  18.750   1.3717   0.14976   0.14728  -0.0837   0.0056   1.0000
  19.000   1.3581   0.15737   0.15501  -0.0880   0.0056   1.0000
  19.250   1.3446   0.16523   0.16299  -0.0927   0.0056   1.0000
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