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 30 (rhodesg30-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: Rhode St. Genese 30 (rhodesg30-il)
Reynolds number: 200,000
Max Cl/Cd: 67.11 at α=5.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-rhodesg30-il-200000.txt
Download as CSV file: xf-rhodesg30-il-200000.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 =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.000  -0.4304   0.09027   0.08671  -0.0323   1.0000   0.0311
 -10.750  -0.4772   0.07720   0.07378  -0.0395   1.0000   0.0283
 -10.500  -0.7031   0.03260   0.02823  -0.0572   1.0000   0.0226
 -10.250  -0.7051   0.02898   0.02414  -0.0545   1.0000   0.0229
 -10.000  -0.6990   0.02663   0.02142  -0.0519   1.0000   0.0232
  -9.750  -0.6893   0.02472   0.01918  -0.0496   1.0000   0.0236
  -9.500  -0.6758   0.02342   0.01764  -0.0475   1.0000   0.0239
  -9.250  -0.6597   0.02265   0.01674  -0.0456   1.0000   0.0244
  -9.000  -0.6423   0.02207   0.01606  -0.0438   1.0000   0.0248
  -8.750  -0.6236   0.02189   0.01586  -0.0421   1.0000   0.0254
  -8.500  -0.6037   0.02226   0.01632  -0.0406   1.0000   0.0261
  -8.250  -0.5828   0.02334   0.01762  -0.0392   1.0000   0.0272
  -8.000  -0.5623   0.02445   0.01890  -0.0378   1.0000   0.0283
  -7.750  -0.5380   0.02292   0.01701  -0.0375   0.9986   0.0334
  -7.500  -0.5032   0.02079   0.01416  -0.0390   0.9951   0.0395
  -7.250  -0.4643   0.02103   0.01430  -0.0412   0.9902   0.0424
  -7.000  -0.4221   0.02125   0.01436  -0.0440   0.9850   0.0458
  -6.750  -0.3811   0.02166   0.01450  -0.0464   0.9787   0.0486
  -6.500  -0.3402   0.02124   0.01416  -0.0494   0.9731   0.0510
  -6.250  -0.3001   0.02146   0.01443  -0.0520   0.9677   0.0541
  -6.000  -0.2615   0.02193   0.01478  -0.0540   0.9609   0.0580
  -5.750  -0.2204   0.02095   0.01370  -0.0571   0.9571   0.0615
  -5.500  -0.1856   0.02109   0.01394  -0.0588   0.9496   0.0675
  -5.250  -0.1429   0.02154   0.01420  -0.0614   0.9447   0.0708
  -5.000  -0.1018   0.01978   0.01248  -0.0648   0.9420   0.0768
  -4.750  -0.0689   0.01951   0.01213  -0.0657   0.9339   0.0812
  -4.500  -0.0282   0.01907   0.01152  -0.0679   0.9288   0.0833
  -4.250   0.0044   0.01788   0.01033  -0.0691   0.9212   0.0890
  -4.000   0.0406   0.01699   0.00930  -0.0702   0.9137   0.0886
  -3.750   0.0714   0.01625   0.00843  -0.0702   0.9041   0.0869
  -3.500   0.1049   0.01566   0.00773  -0.0708   0.8969   0.0858
  -3.250   0.1314   0.01521   0.00724  -0.0700   0.8861   0.0853
  -3.000   0.1595   0.01472   0.00672  -0.0696   0.8763   0.0850
  -2.750   0.1879   0.01420   0.00618  -0.0693   0.8667   0.0850
  -2.500   0.2126   0.01373   0.00571  -0.0682   0.8542   0.0854
  -2.250   0.2378   0.01329   0.00529  -0.0673   0.8417   0.0859
  -2.000   0.2630   0.01291   0.00491  -0.0664   0.8288   0.0867
  -1.750   0.2883   0.01257   0.00458  -0.0655   0.8153   0.0877
  -1.500   0.3137   0.01230   0.00430  -0.0646   0.8010   0.0895
  -1.250   0.3391   0.01207   0.00406  -0.0637   0.7851   0.0928
  -1.000   0.3646   0.01189   0.00383  -0.0629   0.7676   0.0958
  -0.750   0.3904   0.01174   0.00362  -0.0620   0.7485   0.0984
  -0.500   0.4155   0.01160   0.00345  -0.0610   0.7259   0.1036
  -0.250   0.4402   0.01148   0.00334  -0.0600   0.6999   0.1206
   0.000   0.4490   0.00961   0.00341  -0.0563   0.6724   0.7323
   0.250   0.5352   0.00949   0.00336  -0.0677   0.6076   1.0000
   0.500   0.5549   0.00981   0.00338  -0.0658   0.5578   1.0000
   0.750   0.5748   0.01018   0.00344  -0.0642   0.5166   1.0000
   1.000   0.5959   0.01054   0.00355  -0.0628   0.4892   1.0000
   1.250   0.6180   0.01088   0.00371  -0.0617   0.4703   1.0000
   1.500   0.6408   0.01120   0.00390  -0.0607   0.4562   1.0000
   1.750   0.6640   0.01154   0.00410  -0.0598   0.4450   1.0000
   2.000   0.6880   0.01182   0.00432  -0.0591   0.4356   1.0000
   2.250   0.7123   0.01215   0.00456  -0.0584   0.4283   1.0000
   2.500   0.7362   0.01244   0.00481  -0.0577   0.4191   1.0000
   2.750   0.7600   0.01271   0.00506  -0.0570   0.4086   1.0000
   3.000   0.7837   0.01304   0.00531  -0.0562   0.3991   1.0000
   3.250   0.8076   0.01328   0.00558  -0.0555   0.3900   1.0000
   3.500   0.8316   0.01357   0.00586  -0.0549   0.3816   1.0000
   3.750   0.8558   0.01384   0.00614  -0.0543   0.3741   1.0000
   4.000   0.8800   0.01413   0.00646  -0.0537   0.3669   1.0000
   4.250   0.9036   0.01438   0.00673  -0.0530   0.3578   1.0000
   4.500   0.9265   0.01458   0.00700  -0.0521   0.3469   1.0000
   4.750   0.9489   0.01479   0.00724  -0.0512   0.3345   1.0000
   5.000   0.9712   0.01500   0.00750  -0.0503   0.3225   1.0000
   5.250   0.9931   0.01518   0.00774  -0.0493   0.3087   1.0000
   5.500   1.0148   0.01528   0.00795  -0.0482   0.2886   1.0000
   5.750   1.0355   0.01543   0.00813  -0.0469   0.2529   1.0000
   6.000   1.0426   0.01690   0.00885  -0.0441   0.1327   1.0000
   6.250   1.0548   0.01823   0.00992  -0.0419   0.0880   1.0000
   6.500   1.0703   0.01916   0.01076  -0.0401   0.0730   1.0000
   6.750   1.0844   0.02011   0.01169  -0.0382   0.0664   1.0000
   7.000   1.0975   0.02107   0.01273  -0.0360   0.0626   1.0000
   7.250   1.1097   0.02204   0.01380  -0.0338   0.0593   1.0000
   7.500   1.1178   0.02324   0.01503  -0.0311   0.0561   1.0000
   7.750   1.1197   0.02479   0.01658  -0.0274   0.0536   1.0000
   8.000   1.1297   0.02585   0.01775  -0.0250   0.0518   1.0000
   8.250   1.1396   0.02702   0.01902  -0.0227   0.0494   1.0000
   8.500   1.1489   0.02837   0.02043  -0.0205   0.0469   1.0000
   8.750   1.1596   0.03005   0.02210  -0.0187   0.0446   1.0000
   9.000   1.1794   0.03269   0.02477  -0.0182   0.0416   1.0000
   9.250   1.1906   0.03386   0.02612  -0.0163   0.0398   1.0000
   9.500   1.2058   0.03556   0.02796  -0.0151   0.0379   1.0000
   9.750   1.2204   0.03734   0.02984  -0.0139   0.0360   1.0000
  10.000   1.2367   0.03948   0.03204  -0.0133   0.0342   1.0000
  10.250   1.2555   0.04390   0.03667  -0.0135   0.0320   1.0000
  10.500   1.2538   0.04540   0.03842  -0.0105   0.0314   1.0000
  10.750   1.2537   0.04763   0.04091  -0.0082   0.0309   1.0000
  11.000   1.2507   0.05012   0.04366  -0.0060   0.0303   1.0000
  11.250   1.2454   0.05297   0.04677  -0.0041   0.0299   1.0000
  11.500   1.2374   0.05604   0.05008  -0.0026   0.0296   1.0000
  11.750   1.2268   0.05938   0.05367  -0.0014   0.0292   1.0000
  12.000   1.2145   0.06302   0.05753  -0.0008   0.0288   1.0000
  12.250   1.2001   0.06717   0.06191  -0.0008   0.0288   1.0000
  12.500   1.1883   0.07096   0.06586  -0.0014   0.0279   1.0000
  12.750   1.1679   0.07644   0.07158  -0.0029   0.0281   1.0000
  13.000   1.1438   0.08300   0.07840  -0.0053   0.0288   1.0000
  13.250   1.1243   0.08904   0.08462  -0.0083   0.0286   1.0000
  13.500   1.0965   0.09727   0.09307  -0.0128   0.0293   1.0000
  13.750   1.0701   0.10605   0.10203  -0.0179   0.0300   1.0000
  14.000   1.0425   0.11581   0.11194  -0.0237   0.0308   1.0000
  14.250   1.0167   0.12590   0.12215  -0.0297   0.0314   1.0000
<< Back to Rhode St. Genese 30 (rhodesg30-il)

Polar data table (+)

Polar graphs


<< Back to Rhode St. Genese 30 (rhodesg30-il)