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AIRFOIL PROFILE12A 9.00% (rg12a-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: AIRFOIL PROFILE12A 9.00% (rg12a-il)
Reynolds number: 500,000
Max Cl/Cd: 86.69 at α=4°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-rg12a-il-500000.txt
Download as CSV file: xf-rg12a-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: AIRFOIL PROFILE12A 9.00%                        
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.4909   0.08429   0.08205  -0.0276   1.0000   0.0172
  -8.750  -0.4958   0.07997   0.07777  -0.0295   1.0000   0.0172
  -8.500  -0.5032   0.07558   0.07341  -0.0317   1.0000   0.0176
  -8.250  -0.5209   0.07071   0.06861  -0.0347   1.0000   0.0175
  -8.000  -0.5356   0.06574   0.06361  -0.0371   1.0000   0.0174
  -7.750  -0.5444   0.06101   0.05882  -0.0381   1.0000   0.0176
  -7.500  -0.5506   0.05634   0.05406  -0.0382   1.0000   0.0180
  -7.250  -0.5530   0.05177   0.04934  -0.0376   1.0000   0.0188
  -7.000  -0.5428   0.04857   0.04582  -0.0362   1.0000   0.0205
  -6.750  -0.5407   0.04546   0.04247  -0.0343   1.0000   0.0206
  -6.500  -0.5551   0.03697   0.03362  -0.0328   1.0000   0.0219
  -6.250  -0.5427   0.03553   0.03220  -0.0316   1.0000   0.0227
  -5.500  -0.4565   0.02096   0.01581  -0.0342   0.9941   0.0145
  -5.250  -0.4275   0.01743   0.01193  -0.0347   0.9919   0.0132
  -5.000  -0.3951   0.01549   0.00971  -0.0356   0.9894   0.0131
  -4.750  -0.3609   0.01415   0.00821  -0.0369   0.9870   0.0135
  -4.500  -0.3242   0.01340   0.00735  -0.0387   0.9849   0.0143
  -4.250  -0.2893   0.01184   0.00565  -0.0404   0.9831   0.0158
  -4.000  -0.2581   0.01134   0.00515  -0.0412   0.9781   0.0185
  -3.750  -0.2223   0.01083   0.00456  -0.0429   0.9746   0.0207
  -3.500  -0.1852   0.00999   0.00373  -0.0448   0.9720   0.0351
  -3.250  -0.1504   0.00931   0.00333  -0.0465   0.9687   0.0989
  -3.000  -0.1188   0.00879   0.00306  -0.0476   0.9630   0.1633
  -2.750  -0.0831   0.00807   0.00280  -0.0497   0.9597   0.2853
  -2.500  -0.0472   0.00702   0.00254  -0.0521   0.9572   0.4969
  -2.250  -0.0212   0.00630   0.00246  -0.0517   0.9495   0.6789
  -2.000   0.0148   0.00612   0.00238  -0.0531   0.9452   0.7380
  -1.750   0.0464   0.00601   0.00227  -0.0536   0.9373   0.7633
  -1.500   0.0813   0.00591   0.00216  -0.0548   0.9305   0.7888
  -1.250   0.1117   0.00584   0.00211  -0.0549   0.9192   0.8078
  -1.000   0.1435   0.00578   0.00202  -0.0554   0.9069   0.8207
  -0.750   0.1741   0.00576   0.00195  -0.0557   0.8922   0.8328
  -0.500   0.2036   0.00576   0.00189  -0.0557   0.8751   0.8440
  -0.250   0.2307   0.00577   0.00186  -0.0552   0.8554   0.8536
   0.000   0.2574   0.00582   0.00184  -0.0546   0.8341   0.8628
   0.250   0.2833   0.00589   0.00182  -0.0539   0.8116   0.8724
   0.500   0.3080   0.00596   0.00182  -0.0529   0.7887   0.8811
   0.750   0.3324   0.00603   0.00183  -0.0519   0.7646   0.8905
   1.250   0.3791   0.00623   0.00187  -0.0494   0.7178   0.9102
   1.500   0.4029   0.00631   0.00189  -0.0483   0.6939   0.9184
   1.750   0.4268   0.00641   0.00192  -0.0474   0.6708   0.9260
   2.000   0.4508   0.00651   0.00194  -0.0464   0.6475   0.9329
   2.250   0.4749   0.00661   0.00199  -0.0455   0.6236   0.9408
   2.500   0.4994   0.00671   0.00203  -0.0447   0.5999   0.9485
   2.750   0.5245   0.00684   0.00208  -0.0441   0.5751   0.9578
   3.500   0.6169   0.00736   0.00237  -0.0463   0.4888   0.9834
   3.750   0.6520   0.00760   0.00250  -0.0482   0.4554   0.9914
   4.000   0.6831   0.00788   0.00265  -0.0492   0.4192   1.0000
   4.250   0.7056   0.00814   0.00282  -0.0484   0.3907   1.0000
   4.500   0.7296   0.00847   0.00301  -0.0480   0.3525   1.0000
   4.750   0.7537   0.00886   0.00323  -0.0475   0.3117   1.0000
   5.000   0.7779   0.00927   0.00348  -0.0471   0.2731   1.0000
   5.250   0.8015   0.00975   0.00378  -0.0466   0.2290   1.0000
   5.500   0.8251   0.01025   0.00411  -0.0460   0.1896   1.0000
   5.750   0.8486   0.01077   0.00446  -0.0455   0.1542   1.0000
   6.000   0.8720   0.01129   0.00485  -0.0450   0.1213   1.0000
   6.250   0.8949   0.01189   0.00530  -0.0443   0.0901   1.0000
   6.500   0.9162   0.01266   0.00586  -0.0434   0.0531   1.0000
   6.750   0.9364   0.01360   0.00666  -0.0422   0.0283   1.0000
   7.000   0.9592   0.01422   0.00731  -0.0414   0.0241   1.0000
   7.250   0.9785   0.01524   0.00844  -0.0400   0.0210   1.0000
   7.500   1.0006   0.01588   0.00916  -0.0391   0.0201   1.0000
   7.750   1.0223   0.01655   0.00994  -0.0381   0.0189   1.0000
   8.000   1.0432   0.01727   0.01073  -0.0371   0.0175   1.0000
   8.250   1.0627   0.01814   0.01168  -0.0359   0.0165   1.0000
   8.500   1.0799   0.01927   0.01289  -0.0343   0.0156   1.0000
   8.750   1.0923   0.02112   0.01488  -0.0321   0.0147   1.0000
   9.000   1.1078   0.02276   0.01668  -0.0304   0.0140   1.0000
   9.250   1.1279   0.02347   0.01750  -0.0293   0.0132   1.0000
   9.500   1.1452   0.02463   0.01880  -0.0280   0.0125   1.0000
   9.750   1.1609   0.02606   0.02039  -0.0264   0.0120   1.0000
  10.000   1.1756   0.02747   0.02195  -0.0248   0.0114   1.0000
  10.250   1.1886   0.02895   0.02356  -0.0230   0.0109   1.0000
  10.500   1.1990   0.03060   0.02533  -0.0211   0.0104   1.0000
  10.750   1.2027   0.03319   0.02810  -0.0185   0.0100   1.0000
  11.000   1.1963   0.03707   0.03230  -0.0150   0.0097   1.0000
  11.250   1.1829   0.04046   0.03601  -0.0109   0.0094   1.0000
  11.500   1.1836   0.04143   0.03715  -0.0084   0.0091   1.0000
  11.750   1.1801   0.04342   0.03933  -0.0063   0.0089   1.0000
  12.000   1.1763   0.04558   0.04167  -0.0047   0.0086   1.0000
  12.250   1.1615   0.04948   0.04580  -0.0037   0.0086   1.0000
  12.500   1.1471   0.05364   0.05017  -0.0037   0.0086   1.0000
  12.750   1.1315   0.05839   0.05512  -0.0049   0.0085   1.0000
  13.000   1.1146   0.06392   0.06085  -0.0072   0.0085   1.0000
  13.250   1.1000   0.06965   0.06674  -0.0103   0.0084   1.0000
  13.500   1.0747   0.07800   0.07529  -0.0153   0.0086   1.0000
  13.750   1.0537   0.08640   0.08385  -0.0209   0.0087   1.0000
  14.000   1.0332   0.09547   0.09307  -0.0270   0.0088   1.0000
  14.250   1.0045   0.10721   0.10494  -0.0346   0.0091   1.0000
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