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Rhode St. Genese 30 (rhodesg30-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: Rhode St. Genese 30 (rhodesg30-il)
Reynolds number: 100,000
Max Cl/Cd: 51.49 at α=6.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-rhodesg30-il-100000-n5.txt
Download as CSV file: xf-rhodesg30-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: Rhode St. Genese 30                             
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -11.250  -0.4320   0.09096   0.08601  -0.0343   1.0000   0.0206
 -11.000  -0.4572   0.08235   0.07753  -0.0382   1.0000   0.0198
 -10.750  -0.4989   0.07211   0.06737  -0.0434   1.0000   0.0191
 -10.500  -0.5203   0.06713   0.06250  -0.0456   1.0000   0.0190
 -10.250  -0.5411   0.06062   0.05602  -0.0495   1.0000   0.0188
 -10.000  -0.5595   0.05383   0.04914  -0.0521   1.0000   0.0186
  -9.750  -0.5736   0.04756   0.04264  -0.0528   1.0000   0.0184
  -9.500  -0.5800   0.04269   0.03749  -0.0521   1.0000   0.0184
  -9.250  -0.5796   0.03919   0.03368  -0.0508   1.0000   0.0184
  -9.000  -0.5742   0.03644   0.03063  -0.0493   1.0000   0.0185
  -8.750  -0.5654   0.03418   0.02808  -0.0478   1.0000   0.0186
  -8.500  -0.5540   0.03226   0.02587  -0.0462   1.0000   0.0187
  -8.250  -0.5273   0.03030   0.02356  -0.0474   0.9961   0.0190
  -8.000  -0.4964   0.02877   0.02176  -0.0491   0.9909   0.0195
  -7.750  -0.4638   0.02758   0.02035  -0.0508   0.9861   0.0201
  -7.500  -0.4331   0.02657   0.01913  -0.0520   0.9804   0.0211
  -7.250  -0.3939   0.03047   0.02397  -0.0540   0.9758   0.0254
  -7.000  -0.3674   0.02571   0.01806  -0.0545   0.9698   0.0381
  -6.750  -0.3337   0.02461   0.01651  -0.0557   0.9651   0.0411
  -6.500  -0.3017   0.02415   0.01577  -0.0566   0.9595   0.0434
  -6.250  -0.2684   0.02375   0.01502  -0.0576   0.9538   0.0462
  -6.000  -0.2302   0.02386   0.01509  -0.0599   0.9493   0.0507
  -5.750  -0.1994   0.02384   0.01491  -0.0606   0.9407   0.0549
  -5.500  -0.1585   0.02359   0.01438  -0.0631   0.9353   0.0568
  -5.250  -0.1271   0.02278   0.01356  -0.0641   0.9264   0.0606
  -5.000  -0.0885   0.02235   0.01307  -0.0663   0.9200   0.0650
  -4.750  -0.0581   0.02208   0.01260  -0.0667   0.9101   0.0696
  -4.500  -0.0211   0.02131   0.01168  -0.0685   0.9038   0.0731
  -4.250   0.0073   0.02064   0.01096  -0.0685   0.8931   0.0743
  -4.000   0.0386   0.02001   0.01020  -0.0688   0.8836   0.0741
  -3.750   0.0716   0.01936   0.00946  -0.0695   0.8746   0.0740
  -3.500   0.0994   0.01880   0.00885  -0.0691   0.8619   0.0741
  -3.250   0.1268   0.01828   0.00828  -0.0686   0.8493   0.0744
  -3.000   0.1540   0.01783   0.00780  -0.0682   0.8377   0.0746
  -2.750   0.1816   0.01739   0.00734  -0.0678   0.8271   0.0751
  -2.500   0.2086   0.01700   0.00693  -0.0674   0.8156   0.0761
  -2.250   0.2341   0.01668   0.00659  -0.0667   0.8022   0.0781
  -2.000   0.2601   0.01639   0.00627  -0.0660   0.7882   0.0804
  -1.750   0.2865   0.01613   0.00596  -0.0654   0.7737   0.0823
  -1.500   0.3130   0.01590   0.00567  -0.0648   0.7584   0.0839
  -1.250   0.3398   0.01570   0.00541  -0.0642   0.7423   0.0855
  -1.000   0.3666   0.01550   0.00516  -0.0636   0.7252   0.0883
  -0.750   0.3932   0.01535   0.00498  -0.0630   0.7061   0.0925
  -0.500   0.4197   0.01522   0.00485  -0.0624   0.6845   0.1005
  -0.250   0.4462   0.01490   0.00476  -0.0620   0.6613   0.1853
   0.000   0.5082   0.01288   0.00482  -0.0686   0.6288   1.0000
   0.250   0.5313   0.01306   0.00478  -0.0674   0.5995   1.0000
   0.500   0.5541   0.01328   0.00479  -0.0662   0.5691   1.0000
   0.750   0.5767   0.01353   0.00483  -0.0650   0.5389   1.0000
   1.000   0.5993   0.01381   0.00492  -0.0639   0.5114   1.0000
   1.250   0.6221   0.01411   0.00503  -0.0628   0.4889   1.0000
   1.500   0.6453   0.01442   0.00519  -0.0619   0.4717   1.0000
   1.750   0.6688   0.01475   0.00540  -0.0611   0.4579   1.0000
   2.000   0.6927   0.01508   0.00562  -0.0604   0.4467   1.0000
   2.250   0.7168   0.01542   0.00587  -0.0597   0.4371   1.0000
   2.500   0.7413   0.01575   0.00618  -0.0591   0.4287   1.0000
   2.750   0.7658   0.01611   0.00648  -0.0586   0.4213   1.0000
   3.000   0.7905   0.01645   0.00682  -0.0581   0.4140   1.0000
   3.250   0.8150   0.01682   0.00719  -0.0575   0.4069   1.0000
   3.500   0.8397   0.01719   0.00757  -0.0570   0.3999   1.0000
   3.750   0.8634   0.01757   0.00793  -0.0564   0.3904   1.0000
   4.000   0.8865   0.01792   0.00833  -0.0557   0.3794   1.0000
   4.250   0.9089   0.01828   0.00870  -0.0548   0.3672   1.0000
   4.500   0.9310   0.01864   0.00907  -0.0539   0.3549   1.0000
   4.750   0.9525   0.01899   0.00944  -0.0529   0.3415   1.0000
   5.000   0.9742   0.01931   0.00987  -0.0520   0.3289   1.0000
   5.250   0.9964   0.01964   0.01032  -0.0512   0.3180   1.0000
   5.500   1.0182   0.02000   0.01077  -0.0503   0.3074   1.0000
   5.750   1.0390   0.02033   0.01124  -0.0492   0.2931   1.0000
   6.000   1.0598   0.02065   0.01172  -0.0482   0.2772   1.0000
   6.250   1.0807   0.02099   0.01224  -0.0472   0.2575   1.0000
   6.500   1.0981   0.02145   0.01269  -0.0457   0.2060   1.0000
   6.750   1.1044   0.02288   0.01355  -0.0430   0.1423   1.0000
   7.000   1.1147   0.02433   0.01485  -0.0409   0.1103   1.0000
   7.250   1.1265   0.02556   0.01605  -0.0389   0.0852   1.0000
   7.500   1.1365   0.02681   0.01726  -0.0368   0.0727   1.0000
   7.750   1.1455   0.02801   0.01851  -0.0345   0.0677   1.0000
   8.000   1.1513   0.02922   0.01981  -0.0317   0.0641   1.0000
   8.250   1.1534   0.03062   0.02130  -0.0287   0.0608   1.0000
   8.500   1.1534   0.03221   0.02295  -0.0258   0.0578   1.0000
   8.750   1.1566   0.03369   0.02461  -0.0234   0.0548   1.0000
   9.000   1.1580   0.03539   0.02645  -0.0212   0.0521   1.0000
   9.250   1.1566   0.03741   0.02856  -0.0192   0.0491   1.0000
   9.500   1.1524   0.03983   0.03099  -0.0172   0.0466   1.0000
   9.750   1.1560   0.04179   0.03311  -0.0158   0.0441   1.0000
  10.000   1.1599   0.04382   0.03532  -0.0146   0.0414   1.0000
  10.250   1.1626   0.04606   0.03769  -0.0136   0.0388   1.0000
  10.500   1.1643   0.04850   0.04017  -0.0127   0.0365   1.0000
  10.750   1.1679   0.05112   0.04280  -0.0117   0.0339   1.0000
  11.000   1.1723   0.05353   0.04546  -0.0111   0.0321   1.0000
  11.250   1.1752   0.05618   0.04832  -0.0106   0.0301   1.0000
  11.500   1.1767   0.05899   0.05128  -0.0103   0.0284   1.0000
  11.750   1.1758   0.06198   0.05437  -0.0105   0.0269   1.0000
  12.000   1.1764   0.06502   0.05746  -0.0106   0.0256   1.0000
  12.250   1.1764   0.06852   0.06112  -0.0105   0.0246   1.0000
  12.500   1.1715   0.07254   0.06544  -0.0112   0.0238   1.0000
  12.750   1.1655   0.07686   0.07002  -0.0121   0.0232   1.0000
  13.000   1.1559   0.08175   0.07518  -0.0137   0.0225   1.0000
  13.250   1.1456   0.08698   0.08064  -0.0156   0.0221   1.0000
  13.500   1.1337   0.09268   0.08657  -0.0181   0.0217   1.0000
  13.750   1.1204   0.09888   0.09299  -0.0211   0.0214   1.0000
  14.000   1.1048   0.10582   0.10014  -0.0247   0.0211   1.0000
  14.250   1.0877   0.11343   0.10795  -0.0289   0.0211   1.0000
  14.500   1.0676   0.12211   0.11683  -0.0339   0.0213   1.0000
  14.750   1.0451   0.13187   0.12677  -0.0397   0.0216   1.0000
  15.000   1.0200   0.14304   0.13808  -0.0464   0.0223   1.0000
  15.250   0.9916   0.15638   0.15151  -0.0542   0.0229   1.0000
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