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Rhode St. Genese 34 (rhodesg34-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: Rhode St. Genese 34 (rhodesg34-il)
Reynolds number: 50,000
Max Cl/Cd: 30.9 at α=3.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-rhodesg34-il-50000-n5.txt
Download as CSV file: xf-rhodesg34-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: Rhode St. Genese 34                             
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.500  -0.2589   0.12798   0.12083  -0.0381   1.0000   0.1419
 -12.250  -0.2768   0.12754   0.12052  -0.0376   1.0000   0.1428
 -11.750  -0.3002   0.12483   0.11803  -0.0345   1.0000   0.1436
 -11.500  -0.2944   0.12177   0.11502  -0.0321   1.0000   0.1445
 -11.250  -0.2948   0.11959   0.11289  -0.0300   1.0000   0.1454
 -11.000  -0.2974   0.11771   0.11108  -0.0279   1.0000   0.1467
 -10.750  -0.3019   0.11603   0.10947  -0.0260   1.0000   0.1486
 -10.500  -0.3003   0.11358   0.10706  -0.0266   0.9976   0.1504
  -9.500  -0.2944   0.09281   0.08617  -0.0484   0.9674   0.0942
  -9.000  -0.3045   0.08130   0.07453  -0.0601   0.9469   0.0858
  -8.750  -0.2890   0.07753   0.07071  -0.0632   0.9407   0.0848
  -8.500  -0.2857   0.07386   0.06698  -0.0648   0.9316   0.0839
  -8.250  -0.2747   0.06932   0.06228  -0.0685   0.9247   0.0835
  -8.000  -0.2716   0.06555   0.05835  -0.0697   0.9159   0.0835
  -7.750  -0.2589   0.06130   0.05383  -0.0723   0.9088   0.0838
  -7.500  -0.2481   0.05769   0.04994  -0.0733   0.9007   0.0839
  -7.250  -0.2321   0.05419   0.04612  -0.0745   0.8927   0.0836
  -7.000  -0.2091   0.05055   0.04207  -0.0763   0.8859   0.0835
  -6.750  -0.1931   0.04775   0.03889  -0.0760   0.8759   0.0836
  -6.500  -0.1583   0.04422   0.03473  -0.0786   0.8693   0.0850
  -6.250  -0.1395   0.04202   0.03209  -0.0776   0.8573   0.0866
  -6.000  -0.1028   0.04037   0.03034  -0.0792   0.8479   0.0889
  -5.750  -0.0687   0.03844   0.02809  -0.0801   0.8372   0.0907
  -5.500  -0.0385   0.03669   0.02601  -0.0801   0.8260   0.0925
  -5.250   0.0003   0.03482   0.02368  -0.0813   0.8176   0.0960
  -5.000   0.0234   0.03408   0.02297  -0.0803   0.8060   0.0991
  -4.750   0.0610   0.03288   0.02159  -0.0813   0.7991   0.1034
  -4.500   0.0823   0.03211   0.02065  -0.0797   0.7876   0.1068
  -4.250   0.1203   0.03121   0.01975  -0.0808   0.7806   0.1131
  -4.000   0.1401   0.03074   0.01918  -0.0790   0.7679   0.1189
  -3.750   0.1690   0.03011   0.01851  -0.0786   0.7574   0.1264
  -3.500   0.2019   0.02936   0.01771  -0.0788   0.7472   0.1375
  -3.250   0.2229   0.02888   0.01721  -0.0771   0.7334   0.1490
  -3.000   0.2459   0.02827   0.01661  -0.0758   0.7200   0.1669
  -2.750   0.2709   0.02746   0.01592  -0.0747   0.7070   0.1957
  -2.250   0.3207   0.02556   0.01472  -0.0728   0.6799   0.3313
  -2.000   0.4225   0.02315   0.01410  -0.0842   0.6626   1.0000
  -1.750   0.4466   0.02296   0.01358  -0.0829   0.6449   1.0000
  -1.500   0.4721   0.02279   0.01308  -0.0817   0.6266   1.0000
  -1.250   0.4976   0.02270   0.01266  -0.0807   0.6076   1.0000
  -1.000   0.5208   0.02274   0.01240  -0.0794   0.5876   1.0000
  -0.750   0.5429   0.02289   0.01228  -0.0780   0.5683   1.0000
  -0.500   0.5649   0.02309   0.01222  -0.0767   0.5503   1.0000
  -0.250   0.5871   0.02334   0.01221  -0.0755   0.5343   1.0000
   0.000   0.6078   0.02367   0.01233  -0.0742   0.5193   1.0000
   0.250   0.6294   0.02402   0.01247  -0.0731   0.5066   1.0000
   0.500   0.6529   0.02434   0.01254  -0.0722   0.4965   1.0000
   0.750   0.6747   0.02475   0.01279  -0.0712   0.4866   1.0000
   1.000   0.6989   0.02513   0.01297  -0.0706   0.4788   1.0000
   1.250   0.7213   0.02560   0.01332  -0.0698   0.4712   1.0000
   1.500   0.7476   0.02600   0.01354  -0.0696   0.4656   1.0000
   1.750   0.7709   0.02652   0.01399  -0.0690   0.4600   1.0000
   2.000   0.7944   0.02706   0.01447  -0.0685   0.4548   1.0000
   2.250   0.8206   0.02755   0.01486  -0.0684   0.4503   1.0000
   2.500   0.8490   0.02802   0.01520  -0.0686   0.4465   1.0000
   2.750   0.8687   0.02873   0.01594  -0.0677   0.4418   1.0000
   3.000   0.8909   0.02939   0.01661  -0.0671   0.4376   1.0000
   3.250   0.9155   0.02999   0.01717  -0.0668   0.4339   1.0000
   3.500   0.9433   0.03055   0.01766  -0.0670   0.4308   1.0000
   3.750   0.9666   0.03128   0.01840  -0.0667   0.4278   1.0000
   4.000   0.9834   0.03222   0.01945  -0.0656   0.4247   1.0000
   4.250   1.0015   0.03316   0.02047  -0.0646   0.4219   1.0000
   4.500   1.0206   0.03409   0.02148  -0.0638   0.4192   1.0000
   4.750   1.0412   0.03501   0.02244  -0.0632   0.4168   1.0000
   5.000   1.0639   0.03586   0.02332  -0.0629   0.4144   1.0000
   5.250   1.0901   0.03664   0.02412  -0.0631   0.4122   1.0000
   5.500   1.1015   0.03793   0.02553  -0.0614   0.4095   1.0000
   5.750   1.1022   0.03963   0.02742  -0.0586   0.4065   1.0000
   6.000   1.1038   0.04140   0.02934  -0.0560   0.4038   1.0000
   6.250   1.1059   0.04320   0.03127  -0.0535   0.4012   1.0000
   6.500   1.1111   0.04484   0.03301  -0.0514   0.3985   1.0000
   6.750   1.1318   0.04582   0.03406  -0.0510   0.3957   1.0000
   7.000   1.1592   0.04651   0.03476  -0.0513   0.3923   1.0000
   7.250   0.9337   0.06626   0.05491  -0.0387   0.3822   1.0000
   7.500   0.9534   0.06707   0.05576  -0.0381   0.3785   1.0000
   7.750   1.0200   0.06270   0.05140  -0.0376   0.3765   1.0000
   8.250   0.9510   0.07596   0.06480  -0.0366   0.3580   1.0000
   8.500   1.0104   0.07145   0.06032  -0.0350   0.3562   1.0000
   9.000   0.9564   0.08439   0.07343  -0.0359   0.3379   1.0000
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