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 36 (rhodesg36-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: Rhode St. Genese 36 (rhodesg36-il)
Reynolds number: 100,000
Max Cl/Cd: 42.18 at α=2°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-rhodesg36-il-100000.txt
Download as CSV file: xf-rhodesg36-il-100000.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 =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.0712   0.09351   0.08885  -0.0756   0.9216   0.1531
  -9.500  -0.1138   0.09267   0.08806  -0.0798   0.9070   0.1582
  -9.250  -0.1855   0.09278   0.08811  -0.0800   0.8872   0.1591
  -9.000  -0.0713   0.08522   0.08063  -0.0805   0.8940   0.1635
  -8.750  -0.0767   0.08370   0.07914  -0.0781   0.8832   0.1662
  -8.500  -0.0868   0.08141   0.07685  -0.0791   0.8731   0.1712
  -8.250  -0.1049   0.07719   0.07252  -0.0849   0.8638   0.1769
  -7.750  -0.0691   0.07209   0.06745  -0.0829   0.8496   0.1834
  -7.500  -0.1059   0.07027   0.06534  -0.0844   0.8354   0.1934
  -7.250  -0.0615   0.06591   0.06112  -0.0853   0.8326   0.1969
  -7.000  -0.0402   0.06344   0.05853  -0.0873   0.8270   0.2082
  -6.500  -0.0345   0.05066   0.04420  -0.0918   0.8121   0.1442
  -6.000  -0.0173   0.04169   0.03420  -0.0877   0.7960   0.1183
  -5.750   0.0301   0.03837   0.03043  -0.0905   0.7935   0.1185
  -5.500   0.0292   0.03773   0.02964  -0.0859   0.7807   0.1184
  -5.250   0.0770   0.03490   0.02640  -0.0883   0.7774   0.1186
  -5.000   0.1304   0.03253   0.02401  -0.0915   0.7748   0.1221
  -4.750   0.1413   0.03211   0.02351  -0.0885   0.7628   0.1244
  -4.500   0.1881   0.03016   0.02126  -0.0903   0.7582   0.1280
  -4.250   0.2417   0.02806   0.01895  -0.0932   0.7548   0.1331
  -4.000   0.2564   0.02767   0.01858  -0.0905   0.7415   0.1374
  -3.750   0.3092   0.02587   0.01656  -0.0931   0.7362   0.1449
  -3.500   0.3297   0.02513   0.01593  -0.0913   0.7226   0.1512
  -3.250   0.3806   0.02341   0.01416  -0.0938   0.7156   0.1648
  -3.000   0.4022   0.02264   0.01341  -0.0919   0.7000   0.1769
  -2.750   0.4279   0.02158   0.01253  -0.0906   0.6845   0.1995
  -2.500   0.4547   0.02031   0.01154  -0.0895   0.6680   0.2568
  -2.250   0.4821   0.01910   0.01078  -0.0887   0.6485   0.3648
  -2.000   0.6351   0.01720   0.01008  -0.1096   0.6060   1.0000
  -1.750   0.6546   0.01729   0.00979  -0.1077   0.5819   1.0000
  -1.500   0.6689   0.01753   0.00979  -0.1052   0.5583   1.0000
  -1.250   0.6862   0.01776   0.00975  -0.1032   0.5397   1.0000
  -1.000   0.7053   0.01800   0.00971  -0.1016   0.5246   1.0000
  -0.750   0.7238   0.01829   0.00978  -0.0999   0.5112   1.0000
  -0.500   0.7432   0.01861   0.00991  -0.0984   0.4997   1.0000
  -0.250   0.7666   0.01892   0.00993  -0.0976   0.4907   1.0000
   0.000   0.7856   0.01931   0.01020  -0.0961   0.4813   1.0000
   0.250   0.8102   0.01967   0.01033  -0.0955   0.4739   1.0000
   0.500   0.8316   0.02012   0.01067  -0.0945   0.4669   1.0000
   0.750   0.8545   0.02057   0.01098  -0.0938   0.4607   1.0000
   1.000   0.8821   0.02103   0.01123  -0.0939   0.4554   1.0000
   1.250   0.9041   0.02158   0.01172  -0.0931   0.4506   1.0000
   1.500   0.9254   0.02211   0.01222  -0.0921   0.4458   1.0000
   1.750   0.9500   0.02264   0.01265  -0.0918   0.4413   1.0000
   2.000   0.9790   0.02321   0.01304  -0.0922   0.4371   1.0000
   2.250   1.0006   0.02387   0.01368  -0.0914   0.4333   1.0000
   2.500   1.0184   0.02450   0.01437  -0.0900   0.4293   1.0000
   2.750   1.0394   0.02515   0.01501  -0.0892   0.4257   1.0000
   3.000   1.0633   0.02580   0.01562  -0.0889   0.4225   1.0000
   3.250   1.0900   0.02650   0.01624  -0.0890   0.4196   1.0000
   3.500   1.1196   0.02739   0.01702  -0.0898   0.4170   1.0000
   3.750   1.1333   0.02822   0.01799  -0.0879   0.4147   1.0000
   4.000   1.1475   0.02912   0.01900  -0.0861   0.4123   1.0000
   4.250   1.1627   0.03003   0.02002  -0.0846   0.4095   1.0000
   4.500   1.1791   0.03094   0.02100  -0.0833   0.4068   1.0000
   4.750   1.1978   0.03185   0.02193  -0.0823   0.4042   1.0000
   5.000   1.2191   0.03278   0.02288  -0.0819   0.4018   1.0000
   5.250   1.2422   0.03382   0.02391  -0.0817   0.3999   1.0000
   5.500   1.2673   0.03511   0.02518  -0.0821   0.3981   1.0000
   5.750   1.2688   0.03657   0.02685  -0.0788   0.3966   1.0000
   6.000   1.2643   0.03829   0.02880  -0.0748   0.3949   1.0000
   6.250   1.2530   0.04036   0.03109  -0.0702   0.3933   1.0000
   6.500   1.2249   0.04302   0.03396  -0.0635   0.3914   1.0000
   6.750   0.5904   0.11599   0.10817  -0.0544   0.4562   1.0000
<< Back to Rhode St. Genese 36 (rhodesg36-il)

Polar data table (+)

Polar graphs


<< Back to Rhode St. Genese 36 (rhodesg36-il)