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NASA/LANGLEY RC-12(N)1 AIRFOIL (rc12n1-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: NASA/LANGLEY RC-12(N)1 AIRFOIL (rc12n1-il)
Reynolds number: 50,000
Max Cl/Cd: 31.99 at α=7.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-rc12n1-il-50000.txt
Download as CSV file: xf-rc12n1-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NASA/LANGLEY RC-12(N)1 AIRFOIL                  
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -11.000  -0.5530   0.13546   0.12879   0.0177   1.0000   0.2394
 -10.750  -0.5735   0.13434   0.12777   0.0150   1.0000   0.2494
 -10.500  -0.5643   0.13046   0.12392   0.0154   1.0000   0.2643
 -10.250  -0.5569   0.12676   0.12024   0.0155   1.0000   0.2793
 -10.000  -0.5515   0.12326   0.11678   0.0156   1.0000   0.2944
  -9.750  -0.5521   0.12026   0.11384   0.0155   1.0000   0.3099
  -9.500  -0.5210   0.11489   0.10842   0.0172   1.0000   0.3293
  -9.250  -0.5112   0.11162   0.10517   0.0179   1.0000   0.3501
  -9.000  -0.5256   0.10990   0.10357   0.0180   1.0000   0.3704
  -8.750  -0.5002   0.10582   0.09945   0.0197   1.0000   0.3983
  -8.500  -0.4827   0.10230   0.09595   0.0210   1.0000   0.4268
  -8.250  -0.4662   0.09875   0.09242   0.0220   1.0000   0.4533
  -7.500  -0.4403   0.08943   0.08320   0.0241   1.0000   0.5219
  -6.500  -0.6044   0.05348   0.04649  -0.0199   1.0000   0.1839
  -6.250  -0.6070   0.05039   0.04298  -0.0169   1.0000   0.1675
  -6.000  -0.6078   0.04791   0.03998  -0.0135   1.0000   0.1559
  -5.750  -0.6033   0.04522   0.03695  -0.0106   1.0000   0.1494
  -5.500  -0.5954   0.04316   0.03427  -0.0077   1.0000   0.1422
  -5.250  -0.5831   0.04060   0.03144  -0.0056   1.0000   0.1380
  -5.000  -0.5689   0.03837   0.02867  -0.0034   1.0000   0.1329
  -4.750  -0.5525   0.03706   0.02666  -0.0011   1.0000   0.1294
  -4.500  -0.5335   0.03504   0.02439   0.0003   1.0000   0.1300
  -4.250  -0.5129   0.03296   0.02227   0.0011   1.0000   0.1336
  -4.000  -0.4908   0.03145   0.02055   0.0020   1.0000   0.1365
  -3.750  -0.4662   0.03009   0.01898   0.0028   1.0000   0.1391
  -3.500  -0.4408   0.02900   0.01768   0.0036   1.0000   0.1450
  -3.250  -0.0478   0.02506   0.01638  -0.0362   1.0000   1.0000
  -3.000  -0.0555   0.02516   0.01640  -0.0328   1.0000   1.0000
  -2.750  -0.0645   0.02523   0.01639  -0.0292   1.0000   1.0000
  -2.500  -0.0738   0.02524   0.01632  -0.0255   1.0000   1.0000
  -2.250  -0.0836   0.02519   0.01619  -0.0218   1.0000   1.0000
  -2.000  -0.0938   0.02506   0.01599  -0.0180   1.0000   1.0000
  -1.750  -0.1048   0.02487   0.01572  -0.0139   1.0000   1.0000
  -1.500  -0.1161   0.02462   0.01538  -0.0098   1.0000   1.0000
  -1.250  -0.1254   0.02439   0.01505  -0.0057   1.0000   1.0000
  -1.000  -0.1297   0.02427   0.01478  -0.0023   1.0000   1.0000
  -0.750  -0.1286   0.02428   0.01462   0.0006   1.0000   1.0000
  -0.500  -0.1233   0.02440   0.01457   0.0028   1.0000   1.0000
  -0.250  -0.0881   0.02494   0.01490  -0.0005   0.9923   1.0000
   0.000  -0.0534   0.02556   0.01532  -0.0035   0.9845   1.0000
   0.250  -0.0232   0.02614   0.01574  -0.0057   0.9762   1.0000
   0.500   0.0093   0.02685   0.01630  -0.0082   0.9682   1.0000
   0.750   0.0420   0.02758   0.01691  -0.0107   0.9596   1.0000
   1.000   0.0691   0.02829   0.01753  -0.0121   0.9508   1.0000
   1.250   0.1066   0.02919   0.01835  -0.0153   0.9419   1.0000
   1.500   0.1304   0.02992   0.01902  -0.0160   0.9322   1.0000
   1.750   0.1586   0.03078   0.01984  -0.0175   0.9224   1.0000
   2.000   0.1958   0.03177   0.02082  -0.0204   0.9121   1.0000
   2.250   0.2195   0.03262   0.02166  -0.0210   0.9010   1.0000
   2.500   0.2433   0.03355   0.02259  -0.0216   0.8896   1.0000
   2.750   0.2719   0.03455   0.02361  -0.0229   0.8776   1.0000
   3.000   0.3033   0.03558   0.02470  -0.0246   0.8650   1.0000
   3.250   0.3362   0.03664   0.02582  -0.0264   0.8518   1.0000
   3.500   0.3689   0.03769   0.02695  -0.0281   0.8378   1.0000
   3.750   0.3968   0.03872   0.02809  -0.0289   0.8231   1.0000
   4.000   0.4235   0.03976   0.02922  -0.0294   0.8076   1.0000
   4.250   0.4448   0.04082   0.03037  -0.0290   0.7914   1.0000
   4.500   0.4652   0.04189   0.03154  -0.0285   0.7743   1.0000
   4.750   0.4882   0.04292   0.03271  -0.0282   0.7563   1.0000
   5.000   0.5184   0.04380   0.03376  -0.0286   0.7376   1.0000
   5.250   0.5680   0.04417   0.03439  -0.0308   0.7181   1.0000
   5.500   0.5776   0.04516   0.03551  -0.0283   0.6965   1.0000
   5.750   0.6312   0.04440   0.03507  -0.0291   0.6734   1.0000
   6.000   0.6559   0.04419   0.03505  -0.0268   0.6476   1.0000
   6.250   0.7007   0.04206   0.03326  -0.0243   0.6207   1.0000
   6.500   0.7524   0.03816   0.02970  -0.0205   0.5931   1.0000
   6.750   0.7965   0.03399   0.02585  -0.0158   0.5608   1.0000
   7.000   0.8350   0.02978   0.02184  -0.0105   0.5164   1.0000
   7.250   0.8588   0.02685   0.01863  -0.0043   0.4335   1.0000
   7.500   0.8625   0.02775   0.01849   0.0013   0.3269   1.0000
   7.750   0.8692   0.02989   0.01992   0.0047   0.2623   1.0000
   8.000   0.8841   0.03194   0.02159   0.0068   0.2216   1.0000
   8.250   0.9056   0.03401   0.02344   0.0082   0.1934   1.0000
   8.500   0.9311   0.03620   0.02546   0.0089   0.1730   1.0000
   8.750   0.9560   0.03861   0.02783   0.0096   0.1575   1.0000
   9.000   0.9751   0.04118   0.03074   0.0109   0.1473   1.0000
   9.250   0.9941   0.04415   0.03390   0.0119   0.1395   1.0000
   9.500   1.0099   0.04686   0.03686   0.0132   0.1319   1.0000
   9.750   1.0262   0.05058   0.04075   0.0141   0.1278   1.0000
  10.000   1.0274   0.05411   0.04487   0.0163   0.1258   1.0000
  10.250   1.0245   0.05782   0.04905   0.0185   0.1239   1.0000
  10.500   1.0177   0.06164   0.05326   0.0205   0.1223   1.0000
  10.750   1.0056   0.06569   0.05763   0.0224   0.1216   1.0000
  11.000   0.9858   0.07002   0.06223   0.0241   0.1221   1.0000
  11.250   0.9572   0.07459   0.06700   0.0254   0.1236   1.0000
  11.500   0.9288   0.08003   0.07257   0.0249   0.1254   1.0000
  11.750   0.9043   0.08616   0.07878   0.0233   0.1269   1.0000
  12.000   0.8864   0.09261   0.08528   0.0213   0.1281   1.0000
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