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RG 12A-1.8/9.0 AIRFOIL (rg12a189-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: RG 12A-1.8/9.0 AIRFOIL (rg12a189-il)
Reynolds number: 200,000
Max Cl/Cd: 67.07 at α=4.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-rg12a189-il-200000.txt
Download as CSV file: xf-rg12a189-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: RG 12A-1.8/9.0 AIRFOIL                          
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.3795   0.10118   0.09771  -0.0250   1.0000   0.0439
 -10.000  -0.3784   0.09761   0.09416  -0.0256   1.0000   0.0451
  -9.750  -0.4871   0.10057   0.09697  -0.0258   1.0000   0.0416
  -9.500  -0.4808   0.09770   0.09411  -0.0250   1.0000   0.0426
  -9.250  -0.4775   0.09457   0.09099  -0.0252   1.0000   0.0438
  -9.000  -0.4767   0.09118   0.08763  -0.0261   1.0000   0.0449
  -8.750  -0.4779   0.08759   0.08408  -0.0273   1.0000   0.0460
  -8.500  -0.4815   0.08380   0.08034  -0.0289   1.0000   0.0471
  -8.250  -0.4884   0.07985   0.07645  -0.0309   1.0000   0.0480
  -8.000  -0.5024   0.07569   0.07237  -0.0332   1.0000   0.0486
  -7.750  -0.5133   0.07106   0.06773  -0.0362   1.0000   0.0493
  -7.250  -0.5347   0.06340   0.05956  -0.0398   1.0000   0.0523
  -7.000  -0.5411   0.05662   0.05271  -0.0394   1.0000   0.0534
  -6.750  -0.5325   0.05316   0.04933  -0.0382   1.0000   0.0546
  -6.500  -0.5241   0.05059   0.04676  -0.0368   1.0000   0.0560
  -6.250  -0.5160   0.04784   0.04392  -0.0356   1.0000   0.0581
  -6.000  -0.5068   0.04476   0.04059  -0.0345   1.0000   0.0621
  -5.750  -0.4997   0.04076   0.03614  -0.0336   1.0000   0.0675
  -5.500  -0.4859   0.03814   0.03351  -0.0324   1.0000   0.0695
  -5.250  -0.4611   0.02816   0.02188  -0.0289   1.0000   0.0295
  -5.000  -0.4419   0.02412   0.01750  -0.0279   1.0000   0.0281
  -4.750  -0.4199   0.02169   0.01468  -0.0268   1.0000   0.0278
  -4.500  -0.3975   0.02104   0.01373  -0.0255   1.0000   0.0293
  -4.250  -0.3741   0.01829   0.01076  -0.0248   1.0000   0.0313
  -4.000  -0.3507   0.01698   0.00936  -0.0239   1.0000   0.0328
  -3.750  -0.3277   0.01601   0.00833  -0.0230   1.0000   0.0348
  -3.500  -0.3050   0.01521   0.00747  -0.0220   1.0000   0.0386
  -3.250  -0.2826   0.01436   0.00665  -0.0213   1.0000   0.0472
  -3.000  -0.2594   0.01339   0.00577  -0.0206   1.0000   0.0766
  -2.750  -0.2250   0.01221   0.00529  -0.0229   0.9969   0.2125
  -2.500  -0.1919   0.01055   0.00527  -0.0251   0.9925   0.5684
  -2.250  -0.1602   0.01044   0.00577  -0.0250   0.9853   0.7728
  -2.000  -0.1262   0.01054   0.00587  -0.0256   0.9771   0.8213
  -1.750  -0.0897   0.01067   0.00594  -0.0266   0.9705   0.8599
  -1.500  -0.0620   0.01064   0.00590  -0.0256   0.9603   0.8907
  -1.250  -0.0320   0.01060   0.00582  -0.0252   0.9514   0.9171
  -1.000   0.0068   0.01055   0.00569  -0.0266   0.9451   0.9385
  -0.750   0.0492   0.01050   0.00557  -0.0289   0.9380   0.9573
  -0.500   0.1045   0.01047   0.00546  -0.0340   0.9342   0.9703
  -0.250   0.1699   0.01038   0.00530  -0.0413   0.9324   0.9778
   0.000   0.2328   0.01020   0.00507  -0.0482   0.9300   0.9845
   0.250   0.2884   0.00995   0.00480  -0.0538   0.9211   0.9908
   0.500   0.3404   0.00967   0.00450  -0.0586   0.9109   0.9951
   0.750   0.3894   0.00938   0.00420  -0.0628   0.8965   0.9983
   1.000   0.4311   0.00914   0.00393  -0.0655   0.8769   1.0000
   1.250   0.4611   0.00899   0.00373  -0.0659   0.8526   1.0000
   1.500   0.4873   0.00892   0.00359  -0.0654   0.8265   1.0000
   1.750   0.5103   0.00890   0.00348  -0.0643   0.7993   1.0000
   2.000   0.5315   0.00893   0.00344  -0.0629   0.7725   1.0000
   2.250   0.5512   0.00901   0.00342  -0.0612   0.7454   1.0000
   2.500   0.5696   0.00913   0.00344  -0.0593   0.7185   1.0000
   2.750   0.5871   0.00926   0.00349  -0.0573   0.6919   1.0000
   3.000   0.6043   0.00942   0.00360  -0.0552   0.6656   1.0000
   3.250   0.6219   0.00960   0.00370  -0.0532   0.6392   1.0000
   3.500   0.6408   0.00981   0.00382  -0.0514   0.6119   1.0000
   3.750   0.6617   0.01004   0.00397  -0.0501   0.5835   1.0000
   4.000   0.6837   0.01029   0.00413  -0.0489   0.5540   1.0000
   4.250   0.7061   0.01057   0.00435  -0.0478   0.5232   1.0000
   4.750   0.7512   0.01120   0.00480  -0.0458   0.4564   1.0000
   5.000   0.7735   0.01158   0.00508  -0.0448   0.4214   1.0000
   5.250   0.7960   0.01197   0.00541  -0.0439   0.3854   1.0000
   5.500   0.8176   0.01243   0.00575  -0.0429   0.3447   1.0000
   5.750   0.8382   0.01300   0.00612  -0.0418   0.2951   1.0000
   6.000   0.8587   0.01363   0.00655  -0.0407   0.2438   1.0000
   6.250   0.8792   0.01434   0.00706  -0.0397   0.1977   1.0000
   6.500   0.8993   0.01515   0.00769  -0.0387   0.1507   1.0000
   6.750   0.9176   0.01621   0.00847  -0.0375   0.1019   1.0000
   7.000   0.9321   0.01783   0.00981  -0.0355   0.0588   1.0000
   7.250   0.9482   0.01921   0.01120  -0.0335   0.0470   1.0000
   7.500   0.9647   0.02054   0.01252  -0.0319   0.0410   1.0000
   7.750   0.9827   0.02183   0.01392  -0.0303   0.0373   1.0000
   8.000   1.0017   0.02313   0.01535  -0.0289   0.0346   1.0000
   8.250   1.0210   0.02458   0.01687  -0.0277   0.0327   1.0000
   8.500   1.0405   0.02648   0.01883  -0.0266   0.0311   1.0000
   8.750   1.0602   0.02972   0.02226  -0.0257   0.0292   1.0000
   9.000   1.0792   0.03103   0.02384  -0.0244   0.0279   1.0000
   9.250   1.0968   0.03345   0.02658  -0.0230   0.0270   1.0000
   9.500   1.1110   0.03631   0.02981  -0.0212   0.0266   1.0000
   9.750   1.1202   0.03957   0.03348  -0.0191   0.0263   1.0000
  10.000   1.1251   0.04274   0.03703  -0.0166   0.0258   1.0000
  10.250   1.1271   0.04554   0.04016  -0.0141   0.0250   1.0000
  10.500   1.1311   0.04755   0.04236  -0.0121   0.0237   1.0000
  10.750   1.1173   0.05119   0.04638  -0.0083   0.0239   1.0000
  11.000   1.0979   0.05495   0.05046  -0.0048   0.0242   1.0000
  11.250   1.0747   0.05926   0.05506  -0.0025   0.0247   1.0000
  11.500   1.0510   0.06399   0.06001  -0.0021   0.0253   1.0000
  11.750   1.0274   0.06926   0.06549  -0.0034   0.0254   1.0000
  12.000   1.0034   0.07549   0.07190  -0.0065   0.0258   1.0000
  12.250   0.9775   0.08315   0.07973  -0.0115   0.0263   1.0000
  12.500   0.9515   0.09220   0.08891  -0.0180   0.0271   1.0000
  12.750   0.9261   0.10238   0.09914  -0.0246   0.0284   1.0000
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