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RG 15A-1.8/11.0 AIRFOIL (rg15a111-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: RG 15A-1.8/11.0 AIRFOIL (rg15a111-il)
Reynolds number: 500,000
Max Cl/Cd: 79.68 at α=5.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-rg15a111-il-500000-n5.txt
Download as CSV file: xf-rg15a111-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: RG 15A-1.8/11.0 AIRFOIL                         
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -14.000  -0.7668   0.08309   0.08033  -0.0384   1.0000   0.0063
 -13.750  -0.8106   0.07004   0.06715  -0.0461   1.0000   0.0062
 -13.500  -0.8439   0.05862   0.05557  -0.0541   1.0000   0.0062
 -13.250  -0.8699   0.04962   0.04636  -0.0611   1.0000   0.0061
 -13.000  -0.8882   0.04365   0.04019  -0.0651   1.0000   0.0061
 -12.750  -0.9006   0.03958   0.03595  -0.0668   1.0000   0.0062
 -12.500  -0.9133   0.03622   0.03242  -0.0669   1.0000   0.0062
 -12.250  -0.9218   0.03391   0.02994  -0.0656   1.0000   0.0063
 -12.000  -0.9353   0.03201   0.02790  -0.0622   1.0000   0.0063
 -11.750  -0.9411   0.03043   0.02615  -0.0588   1.0000   0.0063
 -11.500  -0.9401   0.02886   0.02440  -0.0561   1.0000   0.0064
 -11.250  -0.9391   0.02714   0.02253  -0.0533   1.0000   0.0066
 -11.000  -0.9315   0.02588   0.02116  -0.0511   1.0000   0.0068
 -10.750  -0.9207   0.02484   0.02001  -0.0491   1.0000   0.0069
 -10.500  -0.9077   0.02396   0.01904  -0.0472   1.0000   0.0071
 -10.250  -0.8943   0.02306   0.01803  -0.0454   1.0000   0.0073
 -10.000  -0.8789   0.02236   0.01725  -0.0438   1.0000   0.0076
  -9.750  -0.8557   0.02152   0.01629  -0.0437   0.9990   0.0080
  -9.500  -0.8262   0.02063   0.01525  -0.0449   0.9970   0.0085
  -9.250  -0.7963   0.01975   0.01422  -0.0461   0.9950   0.0090
  -9.000  -0.7672   0.01885   0.01319  -0.0471   0.9929   0.0094
  -8.750  -0.7397   0.01787   0.01213  -0.0478   0.9900   0.0100
  -8.500  -0.7097   0.01719   0.01138  -0.0489   0.9873   0.0105
  -8.250  -0.6786   0.01654   0.01065  -0.0500   0.9851   0.0112
  -8.000  -0.6465   0.01591   0.00992  -0.0514   0.9833   0.0119
  -7.750  -0.6195   0.01533   0.00926  -0.0515   0.9792   0.0126
  -7.500  -0.5904   0.01470   0.00855  -0.0522   0.9754   0.0133
  -7.250  -0.5594   0.01407   0.00790  -0.0533   0.9726   0.0145
  -7.000  -0.5266   0.01356   0.00732  -0.0546   0.9704   0.0156
  -6.750  -0.5009   0.01310   0.00680  -0.0543   0.9644   0.0164
  -6.500  -0.4699   0.01269   0.00633  -0.0552   0.9605   0.0173
  -6.250  -0.4376   0.01211   0.00571  -0.0563   0.9577   0.0190
  -6.000  -0.4094   0.01170   0.00527  -0.0565   0.9516   0.0205
  -5.750  -0.3776   0.01133   0.00484  -0.0575   0.9467   0.0220
  -5.500  -0.3434   0.01093   0.00441  -0.0589   0.9429   0.0249
  -5.250  -0.3141   0.01057   0.00407  -0.0593   0.9351   0.0295
  -5.000  -0.2802   0.01019   0.00371  -0.0607   0.9293   0.0405
  -4.750  -0.2497   0.00985   0.00341  -0.0613   0.9203   0.0545
  -4.500  -0.2175   0.00956   0.00314  -0.0623   0.9117   0.0685
  -4.250  -0.1872   0.00929   0.00290  -0.0629   0.9012   0.0854
  -4.000  -0.1583   0.00902   0.00268  -0.0631   0.8894   0.1065
  -3.750  -0.1299   0.00879   0.00248  -0.0633   0.8771   0.1286
  -3.500  -0.1021   0.00858   0.00230  -0.0633   0.8641   0.1528
  -3.250  -0.0750   0.00835   0.00214  -0.0632   0.8504   0.1853
  -3.000  -0.0485   0.00811   0.00198  -0.0630   0.8364   0.2262
  -2.750  -0.0223   0.00787   0.00185  -0.0627   0.8220   0.2724
  -2.500   0.0039   0.00765   0.00173  -0.0624   0.8078   0.3195
  -2.250   0.0300   0.00745   0.00162  -0.0621   0.7933   0.3663
  -2.000   0.0556   0.00720   0.00152  -0.0617   0.7788   0.4293
  -1.750   0.0810   0.00695   0.00145  -0.0613   0.7640   0.4983
  -1.500   0.1065   0.00678   0.00142  -0.0608   0.7489   0.5603
  -1.250   0.1326   0.00672   0.00142  -0.0603   0.7334   0.6050
  -1.000   0.1591   0.00672   0.00142  -0.0599   0.7175   0.6342
  -0.750   0.1856   0.00674   0.00143  -0.0595   0.7014   0.6567
  -0.500   0.2123   0.00678   0.00143  -0.0591   0.6851   0.6750
  -0.250   0.2389   0.00683   0.00144  -0.0587   0.6686   0.6904
   0.000   0.2655   0.00689   0.00146  -0.0583   0.6518   0.7039
   0.250   0.2919   0.00696   0.00148  -0.0579   0.6346   0.7163
   0.500   0.3185   0.00703   0.00152  -0.0576   0.6169   0.7276
   0.750   0.3450   0.00711   0.00155  -0.0572   0.5982   0.7384
   1.000   0.3712   0.00721   0.00160  -0.0568   0.5788   0.7496
   1.250   0.3973   0.00731   0.00165  -0.0563   0.5594   0.7603
   1.500   0.4234   0.00741   0.00172  -0.0559   0.5389   0.7707
   1.750   0.4492   0.00754   0.00179  -0.0554   0.5178   0.7815
   2.000   0.4751   0.00767   0.00187  -0.0550   0.4969   0.7922
   2.250   0.5007   0.00780   0.00197  -0.0545   0.4761   0.8024
   2.500   0.5262   0.00795   0.00207  -0.0540   0.4551   0.8134
   3.250   0.6024   0.00842   0.00243  -0.0524   0.3931   0.8438
   3.750   0.6518   0.00880   0.00272  -0.0511   0.3484   0.8661
   4.000   0.6757   0.00902   0.00288  -0.0503   0.3246   0.8791
   4.250   0.6995   0.00921   0.00305  -0.0495   0.3034   0.8936
   4.750   0.7468   0.00962   0.00341  -0.0478   0.2638   0.9330
   5.000   0.7764   0.00985   0.00362  -0.0482   0.2453   0.9586
   5.250   0.8103   0.01017   0.00386  -0.0498   0.2238   0.9959
   5.500   0.8351   0.01049   0.00410  -0.0494   0.2034   1.0000
   5.750   0.8588   0.01087   0.00438  -0.0488   0.1811   1.0000
   6.000   0.8822   0.01128   0.00467  -0.0482   0.1572   1.0000
   6.250   0.9058   0.01166   0.00499  -0.0476   0.1396   1.0000
   6.500   0.9297   0.01202   0.00530  -0.0470   0.1255   1.0000
   6.750   0.9532   0.01241   0.00563  -0.0464   0.1116   1.0000
   7.000   0.9765   0.01281   0.00598  -0.0458   0.0983   1.0000
   7.250   0.9995   0.01323   0.00636  -0.0451   0.0867   1.0000
   7.500   1.0225   0.01363   0.00675  -0.0444   0.0771   1.0000
   7.750   1.0453   0.01404   0.00715  -0.0437   0.0684   1.0000
   8.000   1.0676   0.01449   0.00758  -0.0429   0.0602   1.0000
   8.250   1.0895   0.01496   0.00803  -0.0420   0.0529   1.0000
   8.500   1.1114   0.01540   0.00850  -0.0412   0.0468   1.0000
   8.750   1.1320   0.01594   0.00901  -0.0402   0.0400   1.0000
   9.000   1.1525   0.01646   0.00953  -0.0391   0.0344   1.0000
   9.250   1.1725   0.01700   0.01008  -0.0381   0.0300   1.0000
   9.500   1.1923   0.01753   0.01063  -0.0369   0.0269   1.0000
   9.750   1.2107   0.01816   0.01127  -0.0356   0.0240   1.0000
  10.000   1.2302   0.01864   0.01184  -0.0344   0.0226   1.0000
  10.250   1.2483   0.01920   0.01244  -0.0331   0.0208   1.0000
  10.500   1.2633   0.01984   0.01310  -0.0313   0.0187   1.0000
  10.750   1.2782   0.02044   0.01376  -0.0294   0.0170   1.0000
  11.000   1.2928   0.02104   0.01443  -0.0275   0.0156   1.0000
  11.250   1.3056   0.02176   0.01517  -0.0255   0.0139   1.0000
  11.500   1.3180   0.02250   0.01598  -0.0235   0.0126   1.0000
  11.750   1.3300   0.02329   0.01684  -0.0216   0.0112   1.0000
  12.000   1.3398   0.02422   0.01782  -0.0195   0.0100   1.0000
  12.250   1.3496   0.02517   0.01885  -0.0175   0.0089   1.0000
  12.500   1.3579   0.02624   0.01999  -0.0156   0.0079   1.0000
  12.750   1.3644   0.02748   0.02131  -0.0136   0.0072   1.0000
  13.000   1.3702   0.02884   0.02276  -0.0117   0.0067   1.0000
  13.250   1.3755   0.03028   0.02430  -0.0101   0.0063   1.0000
  13.500   1.3799   0.03187   0.02600  -0.0086   0.0059   1.0000
  13.750   1.3830   0.03366   0.02790  -0.0073   0.0056   1.0000
  14.000   1.3839   0.03576   0.03009  -0.0062   0.0053   1.0000
  14.250   1.3843   0.03802   0.03248  -0.0054   0.0051   1.0000
  14.500   1.3802   0.04090   0.03548  -0.0049   0.0048   1.0000
  14.750   1.3784   0.04372   0.03843  -0.0047   0.0047   1.0000
  15.000   1.3762   0.04673   0.04158  -0.0049   0.0046   1.0000
  15.250   1.3708   0.05032   0.04531  -0.0055   0.0045   1.0000
  15.500   1.3660   0.05404   0.04916  -0.0064   0.0044   1.0000
  15.750   1.3591   0.05823   0.05349  -0.0078   0.0043   1.0000
  16.000   1.3502   0.06296   0.05837  -0.0095   0.0041   1.0000
  16.250   1.3391   0.06827   0.06382  -0.0118   0.0041   1.0000
  16.500   1.3265   0.07407   0.06977  -0.0145   0.0041   1.0000
  16.750   1.3125   0.08037   0.07622  -0.0176   0.0041   1.0000
  17.000   1.2967   0.08724   0.08324  -0.0212   0.0040   1.0000
  17.250   1.2775   0.09501   0.09117  -0.0253   0.0040   1.0000
  17.500   1.2597   0.10273   0.09904  -0.0295   0.0039   1.0000
  17.750   1.2393   0.11121   0.10766  -0.0342   0.0040   1.0000
  18.000   1.2205   0.11960   0.11619  -0.0389   0.0040   1.0000
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