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RG 14 9.5% AIRFOIL (rg1495-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: RG 14 9.5% AIRFOIL (rg1495-il)
Reynolds number: 200,000
Max Cl/Cd: 63.56 at α=4.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-rg1495-il-200000.txt
Download as CSV file: xf-rg1495-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: RG 14 9.5% 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
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.4131   0.08391   0.08048  -0.0276   1.0000   0.0657
  -9.250  -0.4164   0.07966   0.07626  -0.0288   1.0000   0.0677
  -9.000  -0.4248   0.07477   0.07141  -0.0308   1.0000   0.0696
  -8.750  -0.4450   0.06858   0.06529  -0.0353   1.0000   0.0716
  -8.500  -0.5749   0.06867   0.06518  -0.0410   1.0000   0.0624
  -8.250  -0.5656   0.06704   0.06360  -0.0389   1.0000   0.0639
  -8.000  -0.5659   0.06426   0.06080  -0.0382   1.0000   0.0659
  -7.750  -0.5715   0.06061   0.05706  -0.0381   1.0000   0.0689
  -7.500  -0.5946   0.05741   0.05322  -0.0372   1.0000   0.0732
  -7.000  -0.6063   0.03875   0.03380  -0.0327   1.0000   0.0462
  -6.750  -0.6110   0.03076   0.02462  -0.0283   1.0000   0.0388
  -6.500  -0.5973   0.02812   0.02160  -0.0261   1.0000   0.0387
  -6.250  -0.5824   0.02537   0.01854  -0.0243   1.0000   0.0393
  -6.000  -0.5650   0.02403   0.01715  -0.0229   1.0000   0.0415
  -5.750  -0.5461   0.02270   0.01565  -0.0214   1.0000   0.0433
  -5.500  -0.5263   0.02113   0.01380  -0.0198   1.0000   0.0444
  -5.250  -0.5058   0.01983   0.01229  -0.0184   1.0000   0.0457
  -5.000  -0.4849   0.01908   0.01135  -0.0170   1.0000   0.0480
  -4.750  -0.4643   0.01758   0.00977  -0.0158   1.0000   0.0507
  -4.500  -0.4435   0.01672   0.00892  -0.0146   1.0000   0.0533
  -4.250  -0.4226   0.01606   0.00820  -0.0133   1.0000   0.0569
  -4.000  -0.4020   0.01543   0.00751  -0.0121   1.0000   0.0618
  -3.750  -0.3819   0.01480   0.00695  -0.0109   1.0000   0.0693
  -3.500  -0.3591   0.01414   0.00633  -0.0103   0.9994   0.0827
  -3.250  -0.3198   0.01334   0.00580  -0.0131   0.9946   0.1329
  -3.000  -0.2821   0.01264   0.00552  -0.0157   0.9887   0.2169
  -2.750  -0.2431   0.01192   0.00543  -0.0187   0.9836   0.3521
  -2.500  -0.2128   0.01094   0.00535  -0.0197   0.9760   0.5518
  -2.250  -0.1808   0.01043   0.00567  -0.0197   0.9706   0.7561
  -2.000  -0.1515   0.01040   0.00575  -0.0191   0.9614   0.8360
  -1.750  -0.1153   0.01045   0.00581  -0.0198   0.9555   0.8845
  -1.500  -0.0803   0.01051   0.00584  -0.0202   0.9476   0.9191
  -1.250  -0.0286   0.01064   0.00589  -0.0241   0.9447   0.9460
  -1.000   0.0339   0.01075   0.00589  -0.0304   0.9437   0.9620
  -0.750   0.1007   0.01074   0.00579  -0.0379   0.9430   0.9727
  -0.500   0.1613   0.01063   0.00562  -0.0443   0.9388   0.9831
  -0.250   0.2240   0.01036   0.00531  -0.0512   0.9342   0.9904
   0.000   0.2863   0.01002   0.00495  -0.0581   0.9292   0.9974
   0.250   0.3315   0.00973   0.00463  -0.0616   0.9161   1.0000
   0.500   0.3677   0.00949   0.00435  -0.0631   0.8994   1.0000
   0.750   0.3950   0.00933   0.00414  -0.0628   0.8764   1.0000
   1.000   0.4213   0.00920   0.00394  -0.0622   0.8532   1.0000
   1.250   0.4437   0.00914   0.00380  -0.0608   0.8272   1.0000
   1.500   0.4648   0.00913   0.00371  -0.0592   0.8012   1.0000
   1.750   0.4861   0.00914   0.00365  -0.0577   0.7772   1.0000
   2.000   0.5069   0.00918   0.00359  -0.0561   0.7515   1.0000
   2.250   0.5268   0.00925   0.00356  -0.0543   0.7243   1.0000
   2.500   0.5467   0.00934   0.00359  -0.0526   0.6984   1.0000
   2.750   0.5666   0.00947   0.00363  -0.0509   0.6733   1.0000
   3.000   0.5860   0.00961   0.00368  -0.0491   0.6468   1.0000
   3.250   0.6047   0.00978   0.00375  -0.0472   0.6178   1.0000
   3.500   0.6232   0.00998   0.00386  -0.0452   0.5879   1.0000
   3.750   0.6416   0.01019   0.00397  -0.0433   0.5579   1.0000
   4.000   0.6603   0.01043   0.00411  -0.0414   0.5278   1.0000
   4.250   0.6791   0.01069   0.00428  -0.0396   0.4963   1.0000
   4.500   0.6979   0.01098   0.00448  -0.0378   0.4633   1.0000
   4.750   0.7167   0.01132   0.00469  -0.0360   0.4290   1.0000
   5.000   0.7358   0.01168   0.00494  -0.0343   0.3905   1.0000
   5.250   0.7546   0.01213   0.00522  -0.0326   0.3465   1.0000
   5.500   0.7729   0.01269   0.00558  -0.0310   0.2982   1.0000
   5.750   0.7912   0.01334   0.00600  -0.0294   0.2496   1.0000
   6.000   0.8097   0.01405   0.00649  -0.0279   0.2103   1.0000
   6.250   0.8289   0.01477   0.00704  -0.0266   0.1808   1.0000
   6.500   0.8484   0.01550   0.00768  -0.0253   0.1570   1.0000
   6.750   0.8668   0.01638   0.00842  -0.0239   0.1386   1.0000
   7.000   0.8873   0.01707   0.00912  -0.0227   0.1228   1.0000
   7.250   0.9075   0.01780   0.00982  -0.0216   0.1096   1.0000
   7.500   0.9271   0.01861   0.01058  -0.0204   0.0978   1.0000
   7.750   0.9482   0.01924   0.01130  -0.0193   0.0876   1.0000
   8.000   0.9675   0.02020   0.01231  -0.0180   0.0792   1.0000
   8.250   0.9853   0.02139   0.01343  -0.0167   0.0714   1.0000
   8.500   1.0057   0.02208   0.01426  -0.0155   0.0645   1.0000
   8.750   1.0234   0.02339   0.01556  -0.0143   0.0584   1.0000
   9.000   1.0425   0.02412   0.01645  -0.0130   0.0527   1.0000
   9.250   1.0593   0.02575   0.01807  -0.0117   0.0477   1.0000
   9.500   1.0773   0.02670   0.01921  -0.0103   0.0434   1.0000
   9.750   1.0929   0.02800   0.02049  -0.0090   0.0394   1.0000
  10.000   1.1085   0.02969   0.02242  -0.0075   0.0361   1.0000
  10.250   1.1235   0.03118   0.02409  -0.0059   0.0335   1.0000
  10.500   1.1374   0.03269   0.02568  -0.0044   0.0316   1.0000
  10.750   1.1472   0.03618   0.02938  -0.0029   0.0296   1.0000
  11.000   1.1540   0.03760   0.03111  -0.0004   0.0284   1.0000
  11.250   1.1569   0.03949   0.03328   0.0024   0.0272   1.0000
  11.500   1.1580   0.04133   0.03532   0.0051   0.0260   1.0000
  11.750   1.1561   0.04368   0.03789   0.0076   0.0255   1.0000
  12.000   1.1511   0.04616   0.04059   0.0100   0.0249   1.0000
  12.250   1.1452   0.04876   0.04337   0.0118   0.0244   1.0000
  12.500   1.1354   0.05195   0.04677   0.0131   0.0241   1.0000
  12.750   1.1229   0.05559   0.05063   0.0137   0.0240   1.0000
  13.000   1.1052   0.06009   0.05539   0.0134   0.0240   1.0000
  13.250   1.0876   0.06499   0.06049   0.0120   0.0239   1.0000
  13.500   1.0583   0.07218   0.06800   0.0086   0.0243   1.0000
  13.750   1.0094   0.08407   0.08026   0.0008   0.0253   1.0000
  14.000   0.9484   0.10148   0.09797  -0.0118   0.0270   1.0000
  14.250   0.8967   0.11988   0.11643  -0.0234   0.0288   1.0000
  14.500   0.8694   0.13243   0.12895  -0.0297   0.0297   1.0000
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