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Rhode St. Genese 36 (rhodesg36-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: Rhode St. Genese 36 (rhodesg36-il)
Reynolds number: 50,000
Max Cl/Cd: 13.35 at α=-0.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-rhodesg36-il-50000.txt
Download as CSV file: xf-rhodesg36-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: Rhode St. Genese 36                             
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.3517   0.12381   0.11820  -0.0042   1.0000   0.2452
  -9.250  -0.3964   0.12500   0.11950  -0.0029   1.0000   0.2495
  -9.000  -0.4152   0.12304   0.11764  -0.0013   1.0000   0.2518
  -8.750  -0.3780   0.11837   0.11296   0.0003   1.0000   0.2582
  -8.500  -0.3904   0.11707   0.11173   0.0022   1.0000   0.2651
  -8.250  -0.4389   0.11758   0.11235   0.0049   1.0000   0.2695
  -8.000  -0.4528   0.11487   0.10973   0.0063   1.0000   0.2732
  -7.750  -0.4244   0.11171   0.10658   0.0081   0.9993   0.2824
  -7.500  -0.4772   0.11173   0.10667   0.0058   0.9973   0.2915
  -7.250  -0.4358   0.10791   0.10279  -0.0019   0.9774   0.3127
  -7.000  -0.4031   0.10447   0.09932  -0.0060   0.9602   0.3338
  -6.750  -0.3699   0.10099   0.09585  -0.0079   0.9433   0.3544
  -6.500  -0.3592   0.09864   0.09350  -0.0093   0.9289   0.3765
  -6.250  -0.3336   0.09521   0.09011  -0.0090   0.9142   0.3999
  -6.000  -0.2874   0.09200   0.08692  -0.0077   0.8988   0.4305
  -5.750  -0.2606   0.08968   0.08462  -0.0059   0.8842   0.4744
  -5.000  -0.1853   0.06742   0.06030  -0.0560   0.8413   0.2301
  -4.750  -0.1400   0.06254   0.05503  -0.0604   0.8272   0.2069
  -4.500  -0.0972   0.05920   0.05127  -0.0637   0.8118   0.2003
  -4.250  -0.0592   0.05660   0.04776  -0.0658   0.7942   0.1921
  -4.000  -0.0236   0.05457   0.04534  -0.0668   0.7759   0.1920
  -3.750   0.0101   0.05272   0.04337  -0.0674   0.7577   0.1955
  -3.500   0.0448   0.05123   0.04169  -0.0679   0.7396   0.1993
  -3.250   0.0796   0.04991   0.04009  -0.0683   0.7219   0.2037
  -3.000   0.1145   0.04890   0.03864  -0.0684   0.7051   0.2111
  -2.750   0.1527   0.04742   0.03717  -0.0691   0.6910   0.2202
  -2.500   0.2028   0.04562   0.03521  -0.0708   0.6801   0.2361
  -2.250   0.2277   0.04535   0.03478  -0.0699   0.6639   0.2512
  -2.000   0.2603   0.04470   0.03423  -0.0701   0.6501   0.2768
  -1.750   0.3933   0.03830   0.03035  -0.0823   0.6450   1.0000
  -1.500   0.4073   0.03910   0.03076  -0.0802   0.6312   1.0000
  -1.250   0.4640   0.03801   0.02917  -0.0827   0.6243   1.0000
  -1.000   0.4492   0.04024   0.03127  -0.0777   0.6094   1.0000
  -0.750   0.5157   0.03863   0.02926  -0.0813   0.6043   1.0000
  -0.500   0.4769   0.04230   0.03291  -0.0743   0.5892   1.0000
  -0.250   0.5403   0.04071   0.03098  -0.0773   0.5849   1.0000
   0.000   0.4728   0.04707   0.03744  -0.0695   0.5700   1.0000
   0.250   0.5150   0.04647   0.03658  -0.0700   0.5659   1.0000
   0.500   0.5759   0.04487   0.03470  -0.0724   0.5630   1.0000
   0.750   0.4587   0.05631   0.04640  -0.0643   0.5491   1.0000
   1.000   0.5085   0.05522   0.04507  -0.0650   0.5455   1.0000
   1.250   0.4478   0.06303   0.05297  -0.0618   0.5401   1.0000
   1.500   0.4327   0.06735   0.05726  -0.0607   0.5388   1.0000
   1.750   0.4255   0.07110   0.06097  -0.0601   0.5388   1.0000
   2.000   0.4221   0.07458   0.06440  -0.0596   0.5393   1.0000
   2.250   0.4226   0.07782   0.06758  -0.0593   0.5403   1.0000
   2.500   0.4303   0.08085   0.07053  -0.0594   0.5424   1.0000
   2.750   0.2923   0.09338   0.08363  -0.0597   0.6694   1.0000
   3.000   0.3102   0.09553   0.08566  -0.0600   0.6641   1.0000
   3.250   0.3401   0.09886   0.08884  -0.0615   0.6602   1.0000
   3.500   0.3412   0.10049   0.09039  -0.0604   0.6569   1.0000
   3.750   0.3436   0.10152   0.09135  -0.0592   0.6488   1.0000
   4.000   0.3635   0.10398   0.09372  -0.0597   0.6441   1.0000
   4.250   0.3914   0.10756   0.09718  -0.0611   0.6411   1.0000
   4.500   0.3889   0.10885   0.09843  -0.0598   0.6374   1.0000
   4.750   0.3937   0.10999   0.09952  -0.0590   0.6288   1.0000
   5.000   0.4179   0.11289   0.10234  -0.0599   0.6237   1.0000
   5.250   0.4523   0.11771   0.10707  -0.0619   0.6210   1.0000
   5.500   0.4301   0.11648   0.10584  -0.0589   0.6126   1.0000
   5.750   0.4473   0.11883   0.10814  -0.0593   0.6067   1.0000
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