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GOE 330 (PFALZ 59) AIRFOIL (goe330-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: GOE 330 (PFALZ 59) AIRFOIL (goe330-il)
Reynolds number: 1,000,000
Max Cl/Cd: 121.9 at α=5.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe330-il-1000000-n5.txt
Download as CSV file: xf-goe330-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 330 (PFALZ 59) 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
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.2243   0.10314   0.10137  -0.0578   0.9402   0.0075
 -10.250  -0.2202   0.09986   0.09804  -0.0589   0.9239   0.0078
 -10.000  -0.2267   0.09393   0.09205  -0.0610   0.9060   0.0088
  -9.750  -0.2193   0.09152   0.08957  -0.0621   0.8904   0.0090
  -9.500  -0.2115   0.08910   0.08709  -0.0632   0.8765   0.0091
  -9.250  -0.2036   0.08659   0.08452  -0.0645   0.8636   0.0093
  -9.000  -0.1962   0.08388   0.08176  -0.0660   0.8521   0.0096
  -8.750  -0.1896   0.08089   0.07871  -0.0678   0.8418   0.0099
  -8.250  -0.1893   0.07073   0.06851  -0.0761   0.8262   0.0116
  -8.000  -0.1740   0.06824   0.06600  -0.0794   0.8199   0.0118
  -7.750  -0.1577   0.06554   0.06325  -0.0830   0.8136   0.0120
  -7.500  -0.1403   0.06229   0.05998  -0.0875   0.8079   0.0123
  -7.250  -0.1244   0.04983   0.04739  -0.1042   0.8023   0.0146
  -7.000  -0.1013   0.04753   0.04501  -0.1073   0.7963   0.0148
  -6.750  -0.0771   0.04513   0.04256  -0.1103   0.7909   0.0151
  -6.500  -0.0592   0.02584   0.02251  -0.1243   0.7863   0.0185
  -6.250  -0.0351   0.02412   0.02062  -0.1248   0.7807   0.0188
  -6.000  -0.0102   0.02264   0.01902  -0.1251   0.7751   0.0191
  -5.750   0.0139   0.02077   0.01694  -0.1253   0.7679   0.0195
  -5.500   0.0375   0.01855   0.01448  -0.1254   0.7599   0.0202
  -5.250   0.0585   0.01498   0.01038  -0.1251   0.7504   0.0212
  -5.000   0.0837   0.01374   0.00889  -0.1249   0.7397   0.0217
  -4.750   0.1096   0.01305   0.00800  -0.1246   0.7262   0.0222
  -4.500   0.1354   0.01263   0.00738  -0.1242   0.7054   0.0226
  -4.250   0.1606   0.01223   0.00676  -0.1238   0.6795   0.0228
  -4.000   0.1859   0.01194   0.00627  -0.1233   0.6574   0.0229
  -3.750   0.2120   0.01165   0.00583  -0.1229   0.6419   0.0231
  -3.500   0.2383   0.01130   0.00534  -0.1227   0.6301   0.0232
  -3.250   0.2642   0.01052   0.00440  -0.1224   0.6210   0.0235
  -2.750   0.3175   0.00979   0.00349  -0.1220   0.6053   0.0241
  -2.500   0.3444   0.00956   0.00319  -0.1218   0.5981   0.0243
  -2.250   0.3716   0.00936   0.00295  -0.1216   0.5913   0.0246
  -2.000   0.3987   0.00924   0.00278  -0.1215   0.5827   0.0251
  -1.750   0.4259   0.00910   0.00260  -0.1213   0.5743   0.0255
  -1.500   0.4527   0.00899   0.00243  -0.1211   0.5632   0.0258
  -1.250   0.4794   0.00892   0.00228  -0.1209   0.5487   0.0262
  -1.000   0.5060   0.00887   0.00215  -0.1206   0.5301   0.0267
  -0.750   0.5318   0.00890   0.00206  -0.1202   0.5037   0.0272
  -0.500   0.5569   0.00901   0.00201  -0.1197   0.4722   0.0277
  -0.250   0.5823   0.00912   0.00199  -0.1193   0.4471   0.0281
   0.000   0.6082   0.00921   0.00198  -0.1189   0.4295   0.0285
   0.250   0.6346   0.00926   0.00197  -0.1187   0.4169   0.0288
   0.500   0.6610   0.00932   0.00197  -0.1184   0.4057   0.0291
   1.000   0.7145   0.00941   0.00198  -0.1181   0.3894   0.0297
   1.250   0.7413   0.00945   0.00198  -0.1179   0.3828   0.0312
   1.500   0.7682   0.00949   0.00201  -0.1177   0.3771   0.0334
   1.750   0.7952   0.00953   0.00205  -0.1176   0.3711   0.0360
   2.000   0.8217   0.00958   0.00213  -0.1174   0.3652   0.0528
   2.250   0.8487   0.00964   0.00221  -0.1173   0.3609   0.0667
   2.500   0.8756   0.00969   0.00228  -0.1172   0.3561   0.0733
   2.750   0.9022   0.00978   0.00235  -0.1170   0.3512   0.0769
   3.000   0.9287   0.00987   0.00244  -0.1169   0.3463   0.0803
   3.250   0.9554   0.00995   0.00253  -0.1167   0.3407   0.0863
   3.500   0.9811   0.00972   0.00272  -0.1166   0.3351   0.3246
   4.000   1.0366   0.00873   0.00315  -0.1172   0.3254   1.0000
   4.250   1.0620   0.00889   0.00327  -0.1168   0.3199   1.0000
   4.500   1.0874   0.00904   0.00340  -0.1165   0.3145   1.0000
   4.750   1.1129   0.00919   0.00353  -0.1161   0.3080   1.0000
   5.000   1.1377   0.00938   0.00368  -0.1157   0.3015   1.0000
   5.250   1.1629   0.00954   0.00383  -0.1153   0.2942   1.0000
   5.500   1.1867   0.00981   0.00402  -0.1147   0.2800   1.0000
   5.750   1.2092   0.01015   0.00425  -0.1139   0.2602   1.0000
   6.000   1.2313   0.01052   0.00451  -0.1130   0.2399   1.0000
   6.250   1.2511   0.01105   0.00488  -0.1118   0.2101   1.0000
   6.500   1.2699   0.01165   0.00531  -0.1105   0.1820   1.0000
   6.750   1.2907   0.01209   0.00566  -0.1094   0.1676   1.0000
   7.000   1.3119   0.01249   0.00601  -0.1084   0.1564   1.0000
   7.250   1.3330   0.01287   0.00636  -0.1075   0.1470   1.0000
   7.500   1.3539   0.01327   0.00671  -0.1065   0.1354   1.0000
   7.750   1.3623   0.01443   0.00753  -0.1035   0.0830   1.0000
   8.250   1.3788   0.01650   0.00929  -0.0973   0.0179   1.0000
   8.500   1.3958   0.01702   0.00982  -0.0957   0.0150   1.0000
   8.750   1.4132   0.01749   0.01032  -0.0943   0.0133   1.0000
   9.000   1.4304   0.01800   0.01085  -0.0928   0.0122   1.0000
   9.250   1.4464   0.01857   0.01144  -0.0913   0.0112   1.0000
   9.500   1.4614   0.01922   0.01212  -0.0896   0.0101   1.0000
   9.750   1.4773   0.01980   0.01275  -0.0881   0.0097   1.0000
  10.000   1.4928   0.02043   0.01342  -0.0866   0.0091   1.0000
  10.250   1.5074   0.02113   0.01415  -0.0851   0.0085   1.0000
  10.500   1.5209   0.02191   0.01496  -0.0835   0.0079   1.0000
  10.750   1.5328   0.02282   0.01592  -0.0818   0.0074   1.0000
  11.000   1.5450   0.02374   0.01689  -0.0802   0.0071   1.0000
  11.250   1.5573   0.02467   0.01788  -0.0787   0.0069   1.0000
  11.500   1.5688   0.02568   0.01895  -0.0772   0.0066   1.0000
  11.750   1.5793   0.02678   0.02010  -0.0757   0.0063   1.0000
  12.000   1.5893   0.02797   0.02135  -0.0742   0.0061   1.0000
  12.250   1.5984   0.02925   0.02269  -0.0727   0.0058   1.0000
  12.500   1.6061   0.03067   0.02416  -0.0713   0.0056   1.0000
  12.750   1.6119   0.03229   0.02585  -0.0697   0.0053   1.0000
  13.000   1.6152   0.03419   0.02783  -0.0682   0.0051   1.0000
  13.250   1.6215   0.03587   0.02958  -0.0669   0.0050   1.0000
  13.500   1.6261   0.03774   0.03153  -0.0657   0.0049   1.0000
  13.750   1.6296   0.03980   0.03367  -0.0646   0.0047   1.0000
  14.000   1.6318   0.04207   0.03603  -0.0636   0.0046   1.0000
  14.250   1.6334   0.04449   0.03854  -0.0628   0.0045   1.0000
  14.500   1.6337   0.04717   0.04131  -0.0621   0.0044   1.0000
  14.750   1.6333   0.05003   0.04426  -0.0615   0.0043   1.0000
  15.000   1.6320   0.05309   0.04742  -0.0612   0.0042   1.0000
  15.250   1.6295   0.05637   0.05079  -0.0610   0.0041   1.0000
  15.500   1.6258   0.05988   0.05439  -0.0609   0.0040   1.0000
  15.750   1.6211   0.06360   0.05821  -0.0609   0.0040   1.0000
  16.000   1.6146   0.06764   0.06235  -0.0612   0.0039   1.0000
  16.250   1.6062   0.07201   0.06682  -0.0615   0.0039   1.0000
  16.500   1.5973   0.07653   0.07144  -0.0621   0.0038   1.0000
  16.750   1.5867   0.08143   0.07645  -0.0628   0.0037   1.0000
  17.000   1.5753   0.08656   0.08169  -0.0638   0.0037   1.0000
  17.250   1.5623   0.09197   0.08721  -0.0649   0.0036   1.0000
  17.500   1.5490   0.09750   0.09285  -0.0662   0.0036   1.0000
  17.750   1.5345   0.10332   0.09878  -0.0677   0.0035   1.0000
  18.000   1.5204   0.10909   0.10466  -0.0692   0.0035   1.0000
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