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S2048 (s2048-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: S2048 (s2048-il)
Reynolds number: 1,000,000
Max Cl/Cd: 110.32 at α=2.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s2048-il-1000000.txt
Download as CSV file: xf-s2048-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S2048                                           
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.750  -0.4759   0.12602   0.12427  -0.0179   1.0000   0.0082
 -11.500  -0.4731   0.12170   0.11996  -0.0197   1.0000   0.0091
  -7.500  -0.5425   0.02579   0.02277  -0.0633   0.9882   0.0076
  -7.250  -0.5156   0.02235   0.01892  -0.0650   0.9862   0.0081
  -7.000  -0.4868   0.01896   0.01506  -0.0665   0.9847   0.0087
  -6.750  -0.4542   0.01767   0.01354  -0.0680   0.9838   0.0093
  -6.500  -0.4198   0.01732   0.01306  -0.0696   0.9831   0.0096
  -6.250  -0.4001   0.01393   0.00929  -0.0690   0.9787   0.0107
  -6.000  -0.3689   0.01320   0.00850  -0.0700   0.9768   0.0113
  -5.750  -0.3364   0.01250   0.00773  -0.0713   0.9753   0.0120
  -5.500  -0.3025   0.01210   0.00728  -0.0727   0.9741   0.0133
  -5.250  -0.2690   0.01168   0.00680  -0.0740   0.9728   0.0140
  -5.000  -0.2358   0.01112   0.00615  -0.0753   0.9715   0.0146
  -4.750  -0.2084   0.00977   0.00467  -0.0755   0.9685   0.0155
  -4.500  -0.1831   0.00915   0.00399  -0.0750   0.9636   0.0166
  -4.250  -0.1537   0.00875   0.00356  -0.0753   0.9603   0.0181
  -4.000  -0.1242   0.00838   0.00314  -0.0757   0.9573   0.0192
  -3.750  -0.0984   0.00808   0.00280  -0.0752   0.9520   0.0201
  -3.500  -0.0714   0.00781   0.00248  -0.0749   0.9468   0.0209
  -3.250  -0.0433   0.00757   0.00218  -0.0748   0.9427   0.0216
  -3.000  -0.0176   0.00728   0.00188  -0.0742   0.9355   0.0275
  -2.750   0.0091   0.00690   0.00163  -0.0740   0.9296   0.0684
  -2.500   0.0349   0.00655   0.00146  -0.0736   0.9207   0.1204
  -2.250   0.0610   0.00613   0.00129  -0.0733   0.9114   0.2009
  -2.000   0.0862   0.00554   0.00110  -0.0730   0.8998   0.3393
  -1.750   0.1116   0.00510   0.00097  -0.0727   0.8864   0.4582
  -1.500   0.1375   0.00481   0.00092  -0.0723   0.8722   0.5545
  -0.750   0.2184   0.00463   0.00086  -0.0715   0.8339   0.6618
  -0.500   0.2457   0.00461   0.00086  -0.0712   0.8227   0.6860
  -0.250   0.2727   0.00459   0.00087  -0.0710   0.8115   0.7116
   0.000   0.2998   0.00459   0.00089  -0.0707   0.8003   0.7340
   0.250   0.3269   0.00460   0.00090  -0.0704   0.7886   0.7527
   0.750   0.3811   0.00463   0.00094  -0.0699   0.7632   0.7849
   1.000   0.4080   0.00465   0.00097  -0.0696   0.7487   0.7999
   1.250   0.4346   0.00469   0.00100  -0.0693   0.7330   0.8155
   1.500   0.4611   0.00471   0.00104  -0.0689   0.7164   0.8324
   1.750   0.4870   0.00475   0.00108  -0.0684   0.6958   0.8519
   2.000   0.5120   0.00481   0.00114  -0.0677   0.6709   0.8747
   2.250   0.5355   0.00489   0.00121  -0.0666   0.6399   0.9037
   2.500   0.5571   0.00505   0.00128  -0.0651   0.5925   0.9448
   2.750   0.5899   0.00552   0.00140  -0.0664   0.5011   0.9927
   3.000   0.6142   0.00600   0.00158  -0.0659   0.4280   1.0000
   3.250   0.6386   0.00637   0.00174  -0.0654   0.3781   1.0000
   3.500   0.6631   0.00674   0.00191  -0.0649   0.3313   1.0000
   3.750   0.6881   0.00707   0.00208  -0.0645   0.2938   1.0000
   4.000   0.7134   0.00737   0.00226  -0.0641   0.2637   1.0000
   4.250   0.7388   0.00766   0.00244  -0.0638   0.2366   1.0000
   4.500   0.7643   0.00794   0.00263  -0.0634   0.2128   1.0000
   4.750   0.7899   0.00820   0.00282  -0.0631   0.1922   1.0000
   5.000   0.8151   0.00851   0.00304  -0.0627   0.1680   1.0000
   5.250   0.8397   0.00889   0.00329  -0.0623   0.1379   1.0000
   5.500   0.8631   0.00940   0.00361  -0.0616   0.0999   1.0000
   6.000   0.9104   0.01037   0.00432  -0.0604   0.0516   1.0000
   6.250   0.9349   0.01075   0.00465  -0.0599   0.0413   1.0000
   6.500   0.9591   0.01117   0.00504  -0.0594   0.0321   1.0000
   6.750   0.9842   0.01147   0.00534  -0.0590   0.0277   1.0000
   7.000   1.0084   0.01187   0.00573  -0.0584   0.0221   1.0000
   7.250   1.0324   0.01228   0.00611  -0.0579   0.0171   1.0000
   7.500   1.0556   0.01280   0.00661  -0.0572   0.0116   1.0000
   7.750   1.0785   0.01337   0.00723  -0.0564   0.0089   1.0000
   8.000   1.1009   0.01398   0.00786  -0.0555   0.0073   1.0000
   8.250   1.1215   0.01481   0.00881  -0.0543   0.0065   1.0000
   8.500   1.1438   0.01539   0.00946  -0.0534   0.0061   1.0000
   8.750   1.1651   0.01605   0.01020  -0.0524   0.0057   1.0000
   9.000   1.1862   0.01672   0.01094  -0.0514   0.0053   1.0000
   9.250   1.2068   0.01740   0.01169  -0.0504   0.0050   1.0000
   9.500   1.2255   0.01826   0.01265  -0.0491   0.0047   1.0000
   9.750   1.2413   0.01942   0.01393  -0.0473   0.0045   1.0000
  10.000   1.2533   0.02096   0.01564  -0.0450   0.0043   1.0000
  10.250   1.2642   0.02257   0.01743  -0.0427   0.0042   1.0000
  10.500   1.2705   0.02471   0.01979  -0.0397   0.0041   1.0000
  10.750   1.2852   0.02566   0.02086  -0.0380   0.0041   1.0000
  11.000   1.2935   0.02700   0.02235  -0.0353   0.0040   1.0000
  11.250   1.2984   0.02844   0.02395  -0.0322   0.0040   1.0000
  11.500   1.3035   0.02978   0.02543  -0.0293   0.0040   1.0000
  11.750   1.3076   0.03118   0.02697  -0.0266   0.0039   1.0000
  12.000   1.3059   0.03317   0.02914  -0.0235   0.0039   1.0000
  12.250   1.3057   0.03501   0.03114  -0.0210   0.0038   1.0000
  12.500   1.3025   0.03722   0.03352  -0.0186   0.0037   1.0000
  12.750   1.2993   0.03952   0.03598  -0.0167   0.0037   1.0000
  13.000   1.2915   0.04247   0.03911  -0.0152   0.0036   1.0000
  13.250   1.2813   0.04594   0.04275  -0.0144   0.0036   1.0000
  13.500   1.2694   0.04993   0.04692  -0.0143   0.0036   1.0000
  13.750   1.2488   0.05559   0.05279  -0.0154   0.0036   1.0000
  14.000   1.2387   0.06034   0.05768  -0.0173   0.0035   1.0000
  14.250   1.2175   0.06761   0.06514  -0.0211   0.0035   1.0000
  14.500   1.1965   0.07591   0.07363  -0.0262   0.0036   1.0000
  14.750   1.1707   0.08630   0.08419  -0.0329   0.0037   1.0000
  15.000   1.1450   0.09745   0.09550  -0.0401   0.0037   1.0000
  15.250   1.1243   0.10772   0.10588  -0.0464   0.0037   1.0000
  15.500   1.0907   0.12152   0.11980  -0.0545   0.0038   1.0000
  15.750   1.0617   0.13471   0.13310  -0.0621   0.0039   1.0000
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