Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

Rhode St. Genese 32 (rhodesg32-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: Rhode St. Genese 32 (rhodesg32-il)
Reynolds number: 50,000
Max Cl/Cd: 33.4 at α=4°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-rhodesg32-il-50000-n5.txt
Download as CSV file: xf-rhodesg32-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: Rhode St. Genese 32                             
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.3214   0.10073   0.09382  -0.0332   1.0000   0.1583
 -10.000  -0.3746   0.09450   0.08774  -0.0377   1.0000   0.1068
  -9.750  -0.3782   0.09224   0.08555  -0.0354   1.0000   0.1058
  -9.500  -0.3889   0.09015   0.08355  -0.0331   1.0000   0.1045
  -9.000  -0.4477   0.08135   0.07481  -0.0365   1.0000   0.0950
  -8.750  -0.4490   0.07896   0.07246  -0.0346   1.0000   0.0943
  -8.500  -0.4521   0.07629   0.06980  -0.0332   1.0000   0.0935
  -8.250  -0.4492   0.07271   0.06617  -0.0342   0.9978   0.0924
  -8.000  -0.4308   0.06752   0.06078  -0.0395   0.9899   0.0919
  -7.750  -0.4113   0.06232   0.05527  -0.0447   0.9821   0.0926
  -7.500  -0.3911   0.05768   0.05030  -0.0486   0.9742   0.0928
  -7.250  -0.3692   0.05360   0.04588  -0.0514   0.9666   0.0924
  -7.000  -0.3432   0.04972   0.04158  -0.0545   0.9596   0.0922
  -6.750  -0.3200   0.04634   0.03772  -0.0562   0.9511   0.0933
  -6.500  -0.2879   0.04292   0.03360  -0.0591   0.9442   0.0949
  -6.250  -0.2619   0.04076   0.03118  -0.0599   0.9343   0.0958
  -6.000  -0.2266   0.03865   0.02874  -0.0620   0.9263   0.0966
  -5.750  -0.1945   0.03693   0.02675  -0.0632   0.9162   0.0978
  -5.500  -0.1609   0.03555   0.02515  -0.0645   0.9061   0.1007
  -5.250  -0.1206   0.03394   0.02317  -0.0668   0.8974   0.1038
  -5.000  -0.0900   0.03259   0.02148  -0.0671   0.8864   0.1056
  -4.750  -0.0474   0.03114   0.01972  -0.0693   0.8785   0.1077
  -4.500  -0.0146   0.03023   0.01879  -0.0700   0.8670   0.1108
  -4.250   0.0189   0.02938   0.01783  -0.0705   0.8548   0.1157
  -4.000   0.0570   0.02838   0.01661  -0.0714   0.8436   0.1204
  -3.750   0.0938   0.02749   0.01572  -0.0724   0.8327   0.1247
  -3.500   0.1226   0.02689   0.01502  -0.0720   0.8201   0.1303
  -3.250   0.1525   0.02631   0.01442  -0.0718   0.8088   0.1391
  -3.000   0.1873   0.02557   0.01364  -0.0724   0.7990   0.1517
  -2.750   0.2124   0.02498   0.01307  -0.0714   0.7852   0.1664
  -2.500   0.2383   0.02427   0.01250  -0.0707   0.7713   0.1951
  -2.250   0.2640   0.02328   0.01201  -0.0701   0.7570   0.2735
  -2.000   0.3492   0.02068   0.01152  -0.0789   0.7428   1.0000
  -1.750   0.3737   0.02059   0.01114  -0.0777   0.7249   1.0000
  -1.500   0.3989   0.02050   0.01079  -0.0766   0.7059   1.0000
  -1.250   0.4252   0.02040   0.01044  -0.0757   0.6860   1.0000
  -1.000   0.4499   0.02037   0.01018  -0.0745   0.6634   1.0000
  -0.750   0.4747   0.02038   0.00994  -0.0734   0.6394   1.0000
  -0.500   0.4999   0.02043   0.00973  -0.0723   0.6149   1.0000
  -0.250   0.5234   0.02059   0.00964  -0.0712   0.5896   1.0000
   0.000   0.5476   0.02079   0.00956  -0.0701   0.5669   1.0000
   0.250   0.5703   0.02108   0.00964  -0.0690   0.5458   1.0000
   0.500   0.5938   0.02140   0.00974  -0.0681   0.5286   1.0000
   0.750   0.6177   0.02175   0.00988  -0.0673   0.5149   1.0000
   1.000   0.6420   0.02212   0.01007  -0.0666   0.5035   1.0000
   1.250   0.6659   0.02254   0.01037  -0.0660   0.4935   1.0000
   1.500   0.6916   0.02293   0.01059  -0.0656   0.4861   1.0000
   1.750   0.7158   0.02340   0.01102  -0.0652   0.4783   1.0000
   2.000   0.7418   0.02383   0.01134  -0.0649   0.4721   1.0000
   2.250   0.7669   0.02432   0.01178  -0.0646   0.4663   1.0000
   2.500   0.7920   0.02482   0.01227  -0.0643   0.4608   1.0000
   2.750   0.8186   0.02530   0.01270  -0.0642   0.4563   1.0000
   3.000   0.8445   0.02584   0.01322  -0.0641   0.4523   1.0000
   3.250   0.8685   0.02646   0.01392  -0.0638   0.4484   1.0000
   3.500   0.8933   0.02708   0.01458  -0.0635   0.4449   1.0000
   3.750   0.9189   0.02769   0.01523  -0.0634   0.4419   1.0000
   4.000   0.9455   0.02831   0.01588  -0.0635   0.4394   1.0000
   4.250   0.9696   0.02904   0.01669  -0.0632   0.4368   1.0000
   4.500   0.9899   0.02989   0.01770  -0.0625   0.4333   1.0000
   4.750   1.0110   0.03066   0.01859  -0.0618   0.4290   1.0000
   5.000   1.0359   0.03128   0.01923  -0.0616   0.4244   1.0000
   5.250   1.0572   0.03203   0.02007  -0.0609   0.4197   1.0000
   5.500   1.0734   0.03295   0.02117  -0.0596   0.4140   1.0000
   5.750   1.0972   0.03356   0.02184  -0.0591   0.4086   1.0000
   6.000   1.1184   0.03434   0.02271  -0.0584   0.4037   1.0000
   6.250   1.1310   0.03546   0.02405  -0.0568   0.3985   1.0000
   6.500   1.1519   0.03622   0.02494  -0.0561   0.3932   1.0000
   6.750   1.1763   0.03687   0.02564  -0.0557   0.3880   1.0000
   7.000   1.1823   0.03824   0.02728  -0.0534   0.3821   1.0000
   7.250   1.2020   0.03902   0.02819  -0.0525   0.3762   1.0000
   7.500   1.2241   0.03974   0.02903  -0.0519   0.3706   1.0000
   7.750   1.2246   0.04133   0.03089  -0.0490   0.3642   1.0000
   8.000   1.2525   0.04157   0.03118  -0.0489   0.3566   1.0000
   8.250   1.2504   0.04310   0.03295  -0.0456   0.3490   1.0000
   8.500   1.2831   0.04266   0.03248  -0.0457   0.3379   1.0000
   8.750   1.2646   0.04477   0.03491  -0.0408   0.3302   1.0000
   9.000   1.2873   0.04462   0.03479  -0.0398   0.3196   1.0000
   9.250   1.2642   0.04695   0.03737  -0.0347   0.3126   1.0000
   9.500   1.2853   0.04684   0.03731  -0.0335   0.3028   1.0000
   9.750   1.2502   0.05049   0.04124  -0.0290   0.2962   1.0000
  10.000   1.2658   0.05055   0.04136  -0.0275   0.2862   1.0000
  10.250   1.2100   0.05716   0.04823  -0.0246   0.2795   1.0000
  10.500   1.2072   0.05905   0.05024  -0.0233   0.2693   1.0000
  10.750   1.1365   0.07015   0.06147  -0.0246   0.2594   1.0000
  11.000   1.0830   0.08096   0.07231  -0.0276   0.2455   1.0000
  11.250   1.0586   0.08796   0.07934  -0.0297   0.2318   1.0000
  11.750   1.0376   0.09771   0.08920  -0.0324   0.2076   1.0000
  12.000   1.0399   0.10033   0.09190  -0.0329   0.1973   1.0000
  12.250   1.0594   0.09953   0.09123  -0.0320   0.1882   1.0000
  12.500   1.0976   0.09505   0.08685  -0.0294   0.1779   1.0000
  12.750   1.1267   0.09229   0.08397  -0.0272   0.1642   1.0000
  13.000   1.1322   0.09412   0.08569  -0.0270   0.1517   1.0000
  13.250   1.1280   0.09800   0.08956  -0.0277   0.1413   1.0000
  13.500   1.1300   0.10069   0.09217  -0.0279   0.1312   1.0000
  13.750   1.1280   0.10433   0.09583  -0.0286   0.1224   1.0000
  14.000   1.1229   0.10884   0.10040  -0.0299   0.1155   1.0000
  14.250   1.1186   0.11330   0.10495  -0.0314   0.1092   1.0000
  14.500   1.1210   0.11635   0.10799  -0.0321   0.1037   1.0000
  14.750   1.1035   0.12401   0.11589  -0.0354   0.0994   1.0000
  15.000   1.1025   0.12799   0.11991  -0.0370   0.0948   1.0000
  15.250   1.0987   0.13273   0.12471  -0.0389   0.0912   1.0000
  15.500   1.0587   0.14660   0.13880  -0.0459   0.0891   1.0000
<< Back to Rhode St. Genese 32 (rhodesg32-il)

Polar data table (+)

Polar graphs


<< Back to Rhode St. Genese 32 (rhodesg32-il)