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GOE 330 (PFALZ 59) AIRFOIL (goe330-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 330 (PFALZ 59) AIRFOIL (goe330-il)
Reynolds number: 100,000
Max Cl/Cd: 58.57 at α=5.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe330-il-100000-n5.txt
Download as CSV file: xf-goe330-il-100000-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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.2653   0.11949   0.11475  -0.0356   1.0000   0.0414
  -9.500  -0.2703   0.11788   0.11320  -0.0339   1.0000   0.0422
  -9.250  -0.2767   0.11640   0.11180  -0.0321   1.0000   0.0431
  -9.000  -0.2653   0.11297   0.10836  -0.0358   0.9962   0.0450
  -8.750  -0.2554   0.10995   0.10536  -0.0415   0.9904   0.0465
  -8.500  -0.2484   0.10734   0.10277  -0.0487   0.9831   0.0470
  -8.250  -0.2369   0.10305   0.09851  -0.0519   0.9775   0.0476
  -8.000  -0.2145   0.09837   0.09379  -0.0507   0.9764   0.0497
  -7.750  -0.2016   0.09510   0.09051  -0.0535   0.9705   0.0515
  -7.500  -0.1885   0.09179   0.08719  -0.0576   0.9640   0.0536
  -7.250  -0.1774   0.08870   0.08411  -0.0648   0.9534   0.0560
  -7.000  -0.1576   0.08484   0.08020  -0.0766   0.9438   0.0567
  -6.750  -0.1442   0.08056   0.07594  -0.0761   0.9393   0.0576
  -6.500  -0.1253   0.07728   0.07265  -0.0758   0.9361   0.0602
  -6.250  -0.1068   0.07393   0.06927  -0.0801   0.9291   0.0631
  -6.000  -0.0720   0.06943   0.06454  -0.0946   0.9200   0.0665
  -5.750  -0.0481   0.06554   0.06041  -0.1010   0.9113   0.0669
  -5.500  -0.0367   0.06186   0.05689  -0.0982   0.9073   0.0681
  -5.250  -0.0140   0.05904   0.05406  -0.0993   0.9037   0.0715
  -5.000   0.0194   0.05568   0.05030  -0.1073   0.8938   0.0775
  -4.750   0.0550   0.05186   0.04608  -0.1126   0.8888   0.0779
  -4.500   0.0767   0.04527   0.03924  -0.1138   0.8805   0.0567
  -4.000   0.1309   0.03928   0.03289  -0.1167   0.8666   0.0559
  -3.750   0.1609   0.03646   0.02985  -0.1184   0.8601   0.0545
  -3.500   0.1876   0.03393   0.02703  -0.1190   0.8515   0.0533
  -3.250   0.2195   0.03134   0.02405  -0.1202   0.8448   0.0525
  -3.000   0.2465   0.02946   0.02181  -0.1202   0.8355   0.0535
  -2.750   0.2792   0.02755   0.01947  -0.1210   0.8287   0.0548
  -2.500   0.3049   0.02609   0.01769  -0.1206   0.8191   0.0546
  -2.250   0.3368   0.02458   0.01582  -0.1211   0.8128   0.0545
  -2.000   0.3622   0.02352   0.01448  -0.1204   0.8031   0.0546
  -1.750   0.3940   0.02236   0.01302  -0.1208   0.7965   0.0551
  -1.500   0.4188   0.02158   0.01203  -0.1200   0.7859   0.0557
  -1.250   0.4477   0.02080   0.01105  -0.1198   0.7775   0.0573
  -1.000   0.4740   0.02024   0.01048  -0.1195   0.7675   0.0600
  -0.750   0.4998   0.01972   0.00989  -0.1189   0.7568   0.0621
  -0.500   0.5278   0.01911   0.00918  -0.1185   0.7472   0.0637
  -0.250   0.5540   0.01863   0.00863  -0.1179   0.7360   0.0656
   0.000   0.5793   0.01819   0.00818  -0.1172   0.7240   0.0679
   0.250   0.6056   0.01779   0.00777  -0.1167   0.7122   0.0718
   0.500   0.6327   0.01749   0.00734  -0.1163   0.7004   0.0779
   0.750   0.6606   0.01712   0.00692  -0.1160   0.6886   0.0917
   1.000   0.6886   0.01681   0.00662  -0.1159   0.6756   0.1182
   1.250   0.7257   0.01479   0.00654  -0.1178   0.6623   1.0000
   1.500   0.7520   0.01490   0.00640  -0.1172   0.6488   1.0000
   1.750   0.7782   0.01504   0.00634  -0.1167   0.6353   1.0000
   2.000   0.8041   0.01522   0.00632  -0.1161   0.6216   1.0000
   2.250   0.8295   0.01542   0.00635  -0.1155   0.6076   1.0000
   2.500   0.8546   0.01565   0.00643  -0.1149   0.5934   1.0000
   2.750   0.8793   0.01589   0.00654  -0.1142   0.5794   1.0000
   3.000   0.9035   0.01614   0.00670  -0.1135   0.5651   1.0000
   3.250   0.9273   0.01641   0.00689  -0.1127   0.5506   1.0000
   3.500   0.9508   0.01668   0.00708  -0.1119   0.5358   1.0000
   3.750   0.9740   0.01696   0.00727  -0.1110   0.5211   1.0000
   4.000   0.9972   0.01725   0.00749  -0.1102   0.5071   1.0000
   4.250   1.0203   0.01756   0.00772  -0.1093   0.4938   1.0000
   4.500   1.0432   0.01789   0.00796  -0.1085   0.4815   1.0000
   4.750   1.0663   0.01824   0.00824  -0.1076   0.4703   1.0000
   5.000   1.0893   0.01861   0.00854  -0.1068   0.4601   1.0000
   5.250   1.1123   0.01899   0.00891  -0.1061   0.4506   1.0000
   5.500   1.1353   0.01940   0.00924  -0.1053   0.4420   1.0000
   5.750   1.1577   0.01981   0.00969  -0.1045   0.4325   1.0000
   6.000   1.1805   0.02025   0.01010  -0.1037   0.4243   1.0000
   6.250   1.2028   0.02068   0.01057  -0.1029   0.4161   1.0000
   6.500   1.2257   0.02114   0.01104  -0.1022   0.4092   1.0000
   6.750   1.2477   0.02159   0.01158  -0.1014   0.4016   1.0000
   7.000   1.2707   0.02207   0.01205  -0.1007   0.3952   1.0000
   7.250   1.2917   0.02254   0.01267  -0.0998   0.3878   1.0000
   7.500   1.3138   0.02303   0.01323  -0.0990   0.3814   1.0000
   7.750   1.3348   0.02353   0.01387  -0.0981   0.3745   1.0000
   8.000   1.3554   0.02404   0.01449  -0.0970   0.3676   1.0000
   8.250   1.3741   0.02456   0.01511  -0.0957   0.3591   1.0000
   8.500   1.3894   0.02504   0.01565  -0.0938   0.3476   1.0000
   8.750   1.4001   0.02555   0.01625  -0.0912   0.3329   1.0000
   9.000   1.4091   0.02609   0.01688  -0.0884   0.3180   1.0000
   9.250   1.4172   0.02671   0.01759  -0.0855   0.3029   1.0000
   9.500   1.4242   0.02745   0.01838  -0.0826   0.2867   1.0000
   9.750   1.4317   0.02830   0.01932  -0.0800   0.2684   1.0000
  10.000   1.4374   0.02932   0.02039  -0.0773   0.2479   1.0000
  10.250   1.4387   0.03068   0.02168  -0.0744   0.2209   1.0000
  10.500   1.4368   0.03243   0.02330  -0.0714   0.1941   1.0000
  10.750   1.4320   0.03460   0.02532  -0.0685   0.1702   1.0000
  11.000   1.4257   0.03712   0.02772  -0.0658   0.1412   1.0000
  11.250   1.4069   0.04087   0.03109  -0.0629   0.0800   1.0000
  11.500   1.3852   0.04520   0.03517  -0.0603   0.0467   1.0000
  11.750   1.3738   0.04882   0.03879  -0.0586   0.0393   1.0000
  12.000   1.3659   0.05229   0.04236  -0.0574   0.0358   1.0000
  12.250   1.3568   0.05606   0.04626  -0.0565   0.0335   1.0000
  12.500   1.3489   0.05990   0.05027  -0.0560   0.0318   1.0000
  12.750   1.3411   0.06393   0.05450  -0.0559   0.0304   1.0000
  13.000   1.3318   0.06834   0.05910  -0.0560   0.0292   1.0000
  13.250   1.3209   0.07315   0.06409  -0.0565   0.0283   1.0000
  13.500   1.3088   0.07833   0.06949  -0.0573   0.0275   1.0000
  13.750   1.2959   0.08383   0.07517  -0.0585   0.0270   1.0000
  14.000   1.2824   0.08958   0.08109  -0.0598   0.0266   1.0000
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