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AIRFOIL PROFILE12A 9.00% (rg12a-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: AIRFOIL PROFILE12A 9.00% (rg12a-il)
Reynolds number: 500,000
Max Cl/Cd: 75.32 at α=4.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-rg12a-il-500000-n5.txt
Download as CSV file: xf-rg12a-il-500000-n5.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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.5105   0.08491   0.08262  -0.0266   1.0000   0.0047
  -9.250  -0.5182   0.07969   0.07744  -0.0290   1.0000   0.0047
  -9.000  -0.5313   0.07370   0.07151  -0.0322   1.0000   0.0047
  -8.750  -0.5471   0.06812   0.06598  -0.0360   1.0000   0.0048
  -8.500  -0.5720   0.06180   0.05963  -0.0392   1.0000   0.0047
  -8.250  -0.5893   0.05518   0.05291  -0.0405   1.0000   0.0046
  -8.000  -0.6171   0.04476   0.04219  -0.0400   1.0000   0.0044
  -7.750  -0.6350   0.03333   0.03014  -0.0387   0.9992   0.0045
  -7.500  -0.6168   0.02629   0.02230  -0.0407   0.9959   0.0046
  -7.250  -0.5899   0.02354   0.01915  -0.0420   0.9937   0.0048
  -7.000  -0.5624   0.02187   0.01721  -0.0429   0.9910   0.0053
  -6.750  -0.5341   0.01981   0.01479  -0.0437   0.9883   0.0055
  -6.500  -0.5040   0.01803   0.01268  -0.0447   0.9860   0.0058
  -6.250  -0.4728   0.01645   0.01084  -0.0457   0.9842   0.0059
  -6.000  -0.4441   0.01523   0.00942  -0.0462   0.9813   0.0060
  -5.750  -0.4161   0.01423   0.00825  -0.0464   0.9775   0.0061
  -5.500  -0.3855   0.01340   0.00730  -0.0471   0.9744   0.0064
  -5.250  -0.3543   0.01233   0.00613  -0.0481   0.9720   0.0068
  -5.000  -0.3246   0.01174   0.00548  -0.0487   0.9683   0.0076
  -4.750  -0.2961   0.01123   0.00492  -0.0489   0.9632   0.0083
  -4.500  -0.2637   0.01078   0.00439  -0.0500   0.9596   0.0093
  -4.250  -0.2323   0.01031   0.00388  -0.0508   0.9554   0.0113
  -4.000  -0.2033   0.00993   0.00346  -0.0510   0.9487   0.0139
  -3.750  -0.1687   0.00952   0.00303  -0.0525   0.9446   0.0201
  -3.500  -0.1386   0.00913   0.00272  -0.0531   0.9370   0.0401
  -3.250  -0.1042   0.00873   0.00245  -0.0546   0.9309   0.0707
  -3.000  -0.0722   0.00839   0.00222  -0.0556   0.9216   0.1058
  -2.750  -0.0390   0.00797   0.00199  -0.0570   0.9113   0.1631
  -2.500  -0.0071   0.00755   0.00178  -0.0581   0.8985   0.2358
  -2.250   0.0231   0.00717   0.00160  -0.0587   0.8825   0.3115
  -2.000   0.0519   0.00686   0.00145  -0.0591   0.8639   0.3845
  -1.750   0.0790   0.00652   0.00131  -0.0590   0.8439   0.4733
  -1.500   0.1029   0.00599   0.00125  -0.0583   0.8223   0.6290
  -1.250   0.1280   0.00591   0.00129  -0.0575   0.8002   0.7076
  -1.000   0.1542   0.00596   0.00128  -0.0570   0.7768   0.7339
  -0.750   0.1802   0.00603   0.00128  -0.0564   0.7530   0.7538
  -0.500   0.2061   0.00612   0.00128  -0.0558   0.7296   0.7691
  -0.250   0.2320   0.00622   0.00129  -0.0553   0.7068   0.7822
   0.000   0.2580   0.00632   0.00131  -0.0547   0.6844   0.7934
   0.250   0.2839   0.00643   0.00133  -0.0542   0.6626   0.8044
   0.500   0.3099   0.00653   0.00137  -0.0537   0.6409   0.8152
   1.000   0.3609   0.00674   0.00147  -0.0525   0.5981   0.8374
   1.250   0.3865   0.00686   0.00153  -0.0519   0.5764   0.8473
   1.500   0.4123   0.00698   0.00159  -0.0514   0.5537   0.8543
   1.750   0.4385   0.00712   0.00165  -0.0511   0.5308   0.8599
   2.000   0.4641   0.00726   0.00172  -0.0506   0.5074   0.8646
   2.250   0.4901   0.00741   0.00181  -0.0502   0.4832   0.8699
   2.500   0.5158   0.00757   0.00190  -0.0498   0.4583   0.8752
   2.750   0.5412   0.00775   0.00200  -0.0493   0.4334   0.8808
   3.000   0.5666   0.00795   0.00212  -0.0489   0.4058   0.8869
   3.250   0.5915   0.00814   0.00226  -0.0483   0.3802   0.8934
   3.500   0.6166   0.00835   0.00241  -0.0478   0.3540   0.9010
   3.750   0.6407   0.00858   0.00256  -0.0471   0.3257   0.9090
   4.000   0.6645   0.00885   0.00274  -0.0464   0.2947   0.9182
   4.500   0.7118   0.00945   0.00316  -0.0448   0.2293   0.9438
   4.750   0.7378   0.00991   0.00342  -0.0448   0.1839   0.9616
   5.000   0.7684   0.01035   0.00372  -0.0457   0.1472   0.9857
   5.250   0.7941   0.01082   0.00405  -0.0457   0.1164   1.0000
   5.500   0.8181   0.01130   0.00440  -0.0452   0.0887   1.0000
   5.750   0.8426   0.01173   0.00475  -0.0448   0.0696   1.0000
   6.000   0.8666   0.01220   0.00514  -0.0444   0.0520   1.0000
   6.250   0.8904   0.01268   0.00556  -0.0438   0.0361   1.0000
   6.500   0.9136   0.01325   0.00607  -0.0432   0.0225   1.0000
   6.750   0.9374   0.01372   0.00655  -0.0426   0.0182   1.0000
   7.000   0.9607   0.01426   0.00712  -0.0420   0.0153   1.0000
   7.250   0.9845   0.01472   0.00765  -0.0414   0.0143   1.0000
   7.500   1.0078   0.01521   0.00822  -0.0408   0.0136   1.0000
   7.750   1.0306   0.01576   0.00887  -0.0400   0.0130   1.0000
   8.000   1.0528   0.01634   0.00954  -0.0392   0.0124   1.0000
   8.250   1.0743   0.01699   0.01026  -0.0384   0.0119   1.0000
   8.500   1.0949   0.01770   0.01105  -0.0374   0.0112   1.0000
   8.750   1.1131   0.01865   0.01209  -0.0360   0.0104   1.0000
   9.000   1.1295   0.01975   0.01331  -0.0344   0.0098   1.0000
   9.250   1.1499   0.02039   0.01404  -0.0335   0.0095   1.0000
   9.500   1.1691   0.02112   0.01487  -0.0324   0.0090   1.0000
   9.750   1.1884   0.02178   0.01565  -0.0313   0.0084   1.0000
  10.000   1.2054   0.02265   0.01662  -0.0299   0.0079   1.0000
  10.250   1.2213   0.02355   0.01762  -0.0285   0.0075   1.0000
  10.500   1.2366   0.02443   0.01859  -0.0269   0.0071   1.0000
  10.750   1.2488   0.02543   0.01969  -0.0250   0.0068   1.0000
  11.000   1.2524   0.02694   0.02131  -0.0219   0.0064   1.0000
  11.250   1.2583   0.02826   0.02278  -0.0192   0.0061   1.0000
  11.500   1.2704   0.02908   0.02372  -0.0174   0.0058   1.0000
  11.750   1.2776   0.03030   0.02508  -0.0153   0.0056   1.0000
  12.000   1.2850   0.03150   0.02644  -0.0133   0.0052   1.0000
  12.250   1.2929   0.03267   0.02772  -0.0117   0.0049   1.0000
  12.500   1.2975   0.03417   0.02935  -0.0101   0.0046   1.0000
  12.750   1.3012   0.03584   0.03113  -0.0087   0.0044   1.0000
  13.000   1.3034   0.03774   0.03315  -0.0076   0.0043   1.0000
  13.250   1.3068   0.03965   0.03516  -0.0069   0.0041   1.0000
  13.500   1.3031   0.04250   0.03816  -0.0065   0.0040   1.0000
  13.750   1.2973   0.04584   0.04165  -0.0066   0.0039   1.0000
  14.000   1.2884   0.04988   0.04584  -0.0075   0.0038   1.0000
  14.250   1.2761   0.05480   0.05092  -0.0092   0.0037   1.0000
  14.500   1.2678   0.05954   0.05584  -0.0112   0.0037   1.0000
  14.750   1.2519   0.06581   0.06229  -0.0143   0.0037   1.0000
  15.000   1.2378   0.07220   0.06886  -0.0177   0.0036   1.0000
  15.250   1.2248   0.07879   0.07562  -0.0214   0.0036   1.0000
  15.500   1.2039   0.08717   0.08415  -0.0262   0.0036   1.0000
  15.750   1.1813   0.09631   0.09345  -0.0316   0.0037   1.0000
  16.000   1.1631   0.10497   0.10226  -0.0366   0.0036   1.0000
  16.250   1.1396   0.11507   0.11249  -0.0425   0.0037   1.0000
  16.500   1.1177   0.12525   0.12280  -0.0483   0.0037   1.0000
  17.000   1.0769   0.14600   0.14378  -0.0602   0.0038   1.0000
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