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RG 8 AIRFOIL (rg8-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: RG 8 AIRFOIL (rg8-il)
Reynolds number: 100,000
Max Cl/Cd: 54.77 at α=5.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-rg8-il-100000.txt
Download as CSV file: xf-rg8-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: RG 8 AIRFOIL                                    
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.4409   0.10342   0.09836  -0.0304   1.0000   0.1224
  -9.250  -0.4407   0.10032   0.09529  -0.0307   1.0000   0.1269
  -9.000  -0.4865   0.09736   0.09258  -0.0373   1.0000   0.1315
  -8.750  -0.4617   0.09296   0.08813  -0.0336   1.0000   0.1340
  -8.500  -0.4491   0.09055   0.08572  -0.0314   1.0000   0.1399
  -8.250  -0.4730   0.08733   0.08263  -0.0334   1.0000   0.1444
  -8.000  -0.5405   0.08285   0.07834  -0.0414   1.0000   0.1460
  -7.750  -0.4748   0.08138   0.07680  -0.0304   1.0000   0.1534
  -7.500  -0.4977   0.07819   0.07374  -0.0311   1.0000   0.1573
  -7.250  -0.5439   0.07168   0.06726  -0.0392   1.0000   0.1615
  -7.000  -0.5647   0.05475   0.04977  -0.0469   1.0000   0.0935
  -6.750  -0.5733   0.04150   0.03493  -0.0492   1.0000   0.0641
  -6.500  -0.5590   0.03799   0.03105  -0.0486   1.0000   0.0644
  -6.250  -0.5417   0.03481   0.02744  -0.0480   1.0000   0.0644
  -6.000  -0.5212   0.03212   0.02423  -0.0473   1.0000   0.0637
  -5.750  -0.4997   0.02935   0.02109  -0.0467   1.0000   0.0640
  -5.500  -0.4775   0.02701   0.01850  -0.0461   1.0000   0.0653
  -5.250  -0.4546   0.02532   0.01666  -0.0454   1.0000   0.0677
  -5.000  -0.4313   0.02414   0.01529  -0.0447   1.0000   0.0730
  -4.750  -0.4075   0.02261   0.01363  -0.0440   1.0000   0.0782
  -4.500  -0.3843   0.02142   0.01246  -0.0432   1.0000   0.0859
  -4.250  -0.3610   0.02020   0.01127  -0.0425   1.0000   0.1010
  -4.000  -0.3375   0.01888   0.01023  -0.0422   1.0000   0.1385
  -3.750  -0.3137   0.01779   0.00949  -0.0421   1.0000   0.2031
  -3.500  -0.2902   0.01673   0.00904  -0.0424   1.0000   0.2992
  -3.250  -0.2688   0.01577   0.00906  -0.0417   1.0000   0.4647
  -3.000  -0.2502   0.01591   0.00942  -0.0397   1.0000   0.5746
  -2.750  -0.2331   0.01618   0.00974  -0.0374   1.0000   0.6295
  -2.500  -0.2168   0.01647   0.01005  -0.0349   1.0000   0.6698
  -2.250  -0.2013   0.01674   0.01032  -0.0324   1.0000   0.7035
  -2.000  -0.1866   0.01698   0.01055  -0.0299   1.0000   0.7326
  -1.750  -0.1724   0.01720   0.01076  -0.0273   1.0000   0.7588
  -1.500  -0.1451   0.01763   0.01116  -0.0272   0.9947   0.7870
  -1.000  -0.0758   0.01830   0.01174  -0.0294   0.9739   0.8430
  -0.750  -0.0442   0.01842   0.01183  -0.0299   0.9627   0.8691
  -0.500  -0.0131   0.01845   0.01182  -0.0302   0.9516   0.8965
  -0.250   0.0238   0.01843   0.01179  -0.0317   0.9415   0.9275
   0.000   0.0798   0.01845   0.01177  -0.0371   0.9331   0.9589
   0.250   0.1443   0.01841   0.01166  -0.0447   0.9239   0.9895
   0.500   0.1943   0.01831   0.01149  -0.0500   0.9140   1.0000
   0.750   0.2416   0.01815   0.01126  -0.0545   0.9038   1.0000
   1.000   0.2832   0.01798   0.01104  -0.0578   0.8914   1.0000
   1.250   0.3268   0.01778   0.01081  -0.0612   0.8796   1.0000
   1.500   0.3760   0.01744   0.01046  -0.0652   0.8699   1.0000
   1.750   0.4283   0.01696   0.00999  -0.0695   0.8608   1.0000
   2.000   0.4718   0.01661   0.00966  -0.0722   0.8481   1.0000
   2.250   0.5152   0.01622   0.00928  -0.0746   0.8350   1.0000
   2.500   0.5579   0.01583   0.00891  -0.0769   0.8208   1.0000
   2.750   0.5991   0.01547   0.00858  -0.0787   0.8050   1.0000
   3.000   0.6391   0.01515   0.00826  -0.0802   0.7876   1.0000
   3.250   0.6719   0.01503   0.00814  -0.0806   0.7665   1.0000
   3.500   0.7053   0.01493   0.00803  -0.0809   0.7443   1.0000
   3.750   0.7345   0.01496   0.00804  -0.0806   0.7198   1.0000
   4.000   0.7641   0.01502   0.00804  -0.0803   0.6947   1.0000
   4.250   0.7923   0.01515   0.00812  -0.0798   0.6683   1.0000
   4.500   0.8174   0.01536   0.00828  -0.0788   0.6401   1.0000
   4.750   0.8421   0.01561   0.00847  -0.0778   0.6112   1.0000
   5.000   0.8660   0.01591   0.00869  -0.0766   0.5815   1.0000
   5.250   0.8892   0.01625   0.00897  -0.0754   0.5511   1.0000
   5.500   0.9114   0.01664   0.00927  -0.0740   0.5198   1.0000
   5.750   0.9325   0.01707   0.00964  -0.0725   0.4874   1.0000
   6.000   0.9530   0.01754   0.01004  -0.0709   0.4546   1.0000
   6.250   0.9729   0.01806   0.01050  -0.0693   0.4216   1.0000
   6.500   0.9921   0.01865   0.01096  -0.0676   0.3886   1.0000
   6.750   1.0100   0.01927   0.01153  -0.0658   0.3538   1.0000
   7.000   1.0272   0.01997   0.01213  -0.0639   0.3192   1.0000
   7.250   1.0434   0.02079   0.01281  -0.0620   0.2852   1.0000
   7.500   1.0588   0.02168   0.01363  -0.0599   0.2501   1.0000
   7.750   1.0731   0.02272   0.01453  -0.0578   0.2170   1.0000
   8.000   1.0867   0.02393   0.01556  -0.0557   0.1864   1.0000
   8.250   1.0999   0.02525   0.01675  -0.0536   0.1583   1.0000
   8.500   1.1121   0.02659   0.01802  -0.0513   0.1327   1.0000
   8.750   1.1229   0.02801   0.01939  -0.0490   0.1100   1.0000
   9.000   1.1324   0.02956   0.02085  -0.0467   0.0912   1.0000
   9.250   1.1440   0.03165   0.02289  -0.0445   0.0753   1.0000
   9.500   1.1573   0.03382   0.02503  -0.0427   0.0635   1.0000
   9.750   1.1716   0.03569   0.02704  -0.0409   0.0558   1.0000
  10.000   1.1956   0.03903   0.03051  -0.0406   0.0509   1.0000
  10.250   1.2117   0.04149   0.03327  -0.0391   0.0474   1.0000
  10.500   1.2248   0.04371   0.03558  -0.0377   0.0443   1.0000
  10.750   1.2386   0.04788   0.03996  -0.0368   0.0420   1.0000
  11.000   1.2400   0.05067   0.04318  -0.0339   0.0413   1.0000
  11.250   1.2361   0.05377   0.04667  -0.0306   0.0409   1.0000
  11.500   1.2278   0.05704   0.05030  -0.0273   0.0407   1.0000
  11.750   1.2158   0.06049   0.05407  -0.0244   0.0407   1.0000
  12.000   1.2008   0.06419   0.05808  -0.0220   0.0407   1.0000
  12.250   1.1829   0.06828   0.06245  -0.0204   0.0408   1.0000
  12.500   1.1637   0.07278   0.06720  -0.0197   0.0410   1.0000
  12.750   1.1428   0.07782   0.07247  -0.0201   0.0412   1.0000
  13.000   1.1217   0.08341   0.07826  -0.0216   0.0414   1.0000
  13.250   1.0994   0.08971   0.08475  -0.0241   0.0417   1.0000
  13.500   1.0772   0.09672   0.09191  -0.0276   0.0420   1.0000
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