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S2046 (s2046-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: S2046 (s2046-il)
Reynolds number: 200,000
Max Cl/Cd: 70.61 at α=3°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s2046-il-200000-n5.txt
Download as CSV file: xf-s2046-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S2046                                           
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.4850   0.08047   0.07675  -0.0360   1.0000   0.0170
  -9.250  -0.4952   0.07473   0.07106  -0.0387   1.0000   0.0169
  -9.000  -0.5101   0.06843   0.06484  -0.0418   1.0000   0.0168
  -8.500  -0.5745   0.04564   0.04186  -0.0604   1.0000   0.0161
  -8.250  -0.5865   0.03863   0.03437  -0.0636   1.0000   0.0161
  -8.000  -0.5844   0.03352   0.02872  -0.0648   1.0000   0.0162
  -7.750  -0.5738   0.02982   0.02451  -0.0651   1.0000   0.0164
  -7.500  -0.5583   0.02708   0.02132  -0.0650   1.0000   0.0167
  -7.250  -0.5286   0.02470   0.01847  -0.0670   0.9973   0.0170
  -7.000  -0.4969   0.02271   0.01627  -0.0693   0.9943   0.0180
  -6.750  -0.4652   0.02153   0.01493  -0.0710   0.9908   0.0189
  -6.500  -0.4328   0.02018   0.01337  -0.0726   0.9872   0.0197
  -6.250  -0.3994   0.01887   0.01185  -0.0743   0.9843   0.0203
  -6.000  -0.3671   0.01775   0.01055  -0.0756   0.9808   0.0210
  -5.750  -0.3355   0.01680   0.00945  -0.0767   0.9765   0.0219
  -5.500  -0.3019   0.01588   0.00842  -0.0782   0.9730   0.0230
  -5.250  -0.2668   0.01514   0.00763  -0.0800   0.9703   0.0250
  -5.000  -0.2358   0.01458   0.00698  -0.0809   0.9652   0.0277
  -4.750  -0.2026   0.01400   0.00640  -0.0822   0.9610   0.0335
  -4.500  -0.1675   0.01343   0.00583  -0.0838   0.9578   0.0441
  -4.250  -0.1341   0.01301   0.00541  -0.0851   0.9538   0.0579
  -4.000  -0.1032   0.01270   0.00508  -0.0858   0.9479   0.0703
  -3.750  -0.0695   0.01239   0.00483  -0.0871   0.9437   0.0894
  -3.500  -0.0370   0.01206   0.00457  -0.0882   0.9389   0.1094
  -3.250  -0.0062   0.01176   0.00428  -0.0888   0.9325   0.1274
  -3.000   0.0275   0.01142   0.00399  -0.0900   0.9280   0.1501
  -2.750   0.0574   0.01109   0.00376  -0.0905   0.9209   0.1835
  -2.500   0.0893   0.01066   0.00353  -0.0914   0.9149   0.2447
  -2.250   0.1191   0.01016   0.00338  -0.0920   0.9074   0.3436
  -2.000   0.1495   0.00979   0.00331  -0.0924   0.8997   0.4410
  -1.750   0.1774   0.00962   0.00327  -0.0922   0.8890   0.5007
  -1.500   0.2056   0.00950   0.00321  -0.0919   0.8781   0.5414
  -1.250   0.2337   0.00942   0.00316  -0.0915   0.8672   0.5731
  -1.000   0.2615   0.00935   0.00311  -0.0911   0.8561   0.5992
  -0.750   0.2887   0.00930   0.00307  -0.0906   0.8443   0.6230
  -0.500   0.3158   0.00926   0.00306  -0.0901   0.8328   0.6500
  -0.250   0.3425   0.00922   0.00307  -0.0894   0.8213   0.6796
   0.000   0.3691   0.00919   0.00307  -0.0887   0.8094   0.7056
   0.250   0.3958   0.00917   0.00306  -0.0881   0.7969   0.7250
   0.500   0.4225   0.00916   0.00305  -0.0875   0.7833   0.7404
   0.750   0.4492   0.00915   0.00304  -0.0869   0.7689   0.7552
   1.000   0.4757   0.00916   0.00304  -0.0863   0.7536   0.7703
   1.250   0.5019   0.00916   0.00304  -0.0856   0.7369   0.7860
   1.500   0.5276   0.00917   0.00306  -0.0848   0.7186   0.8031
   1.750   0.5530   0.00919   0.00307  -0.0840   0.6985   0.8220
   2.000   0.5781   0.00921   0.00308  -0.0830   0.6766   0.8441
   2.250   0.6024   0.00922   0.00308  -0.0819   0.6521   0.8743
   2.500   0.6313   0.00919   0.00307  -0.0817   0.6231   0.9602
   2.750   0.6581   0.00941   0.00314  -0.0814   0.5905   1.0000
   3.000   0.6842   0.00969   0.00325  -0.0809   0.5534   1.0000
   3.250   0.7093   0.01005   0.00341  -0.0804   0.5121   1.0000
   3.500   0.7337   0.01048   0.00360  -0.0797   0.4657   1.0000
   3.750   0.7579   0.01095   0.00383  -0.0791   0.4213   1.0000
   4.000   0.7824   0.01140   0.00409  -0.0786   0.3844   1.0000
   4.250   0.8074   0.01182   0.00438  -0.0781   0.3518   1.0000
   4.500   0.8323   0.01224   0.00468  -0.0777   0.3219   1.0000
   4.750   0.8573   0.01267   0.00499  -0.0772   0.2938   1.0000
   5.000   0.8821   0.01311   0.00533  -0.0768   0.2660   1.0000
   5.250   0.9065   0.01359   0.00570  -0.0763   0.2353   1.0000
   5.500   0.9306   0.01412   0.00610  -0.0758   0.2027   1.0000
   5.750   0.9540   0.01473   0.00654  -0.0753   0.1689   1.0000
   6.000   0.9771   0.01539   0.00705  -0.0747   0.1361   1.0000
   6.250   1.0000   0.01607   0.00760  -0.0740   0.1121   1.0000
   6.500   1.0232   0.01671   0.00820  -0.0734   0.0952   1.0000
   6.750   1.0462   0.01737   0.00882  -0.0728   0.0827   1.0000
   7.000   1.0687   0.01807   0.00948  -0.0720   0.0733   1.0000
   7.250   1.0917   0.01867   0.01015  -0.0713   0.0666   1.0000
   7.500   1.1131   0.01946   0.01094  -0.0705   0.0613   1.0000
   7.750   1.1356   0.02009   0.01167  -0.0697   0.0570   1.0000
   8.000   1.1569   0.02083   0.01244  -0.0688   0.0528   1.0000
   8.250   1.1765   0.02175   0.01339  -0.0678   0.0495   1.0000
   8.500   1.1975   0.02249   0.01426  -0.0668   0.0470   1.0000
   8.750   1.2178   0.02329   0.01516  -0.0658   0.0442   1.0000
   9.000   1.2369   0.02416   0.01608  -0.0647   0.0416   1.0000
   9.250   1.2532   0.02535   0.01731  -0.0633   0.0393   1.0000
   9.500   1.2721   0.02624   0.01836  -0.0621   0.0377   1.0000
   9.750   1.2901   0.02716   0.01940  -0.0609   0.0356   1.0000
  10.000   1.3073   0.02805   0.02039  -0.0596   0.0335   1.0000
  10.250   1.3218   0.02913   0.02154  -0.0581   0.0316   1.0000
  10.500   1.3343   0.03047   0.02298  -0.0564   0.0300   1.0000
  10.750   1.3478   0.03146   0.02416  -0.0546   0.0284   1.0000
  11.000   1.3592   0.03252   0.02536  -0.0527   0.0267   1.0000
  11.250   1.3690   0.03362   0.02656  -0.0507   0.0253   1.0000
  11.500   1.3764   0.03488   0.02790  -0.0488   0.0241   1.0000
  11.750   1.3804   0.03666   0.02977  -0.0467   0.0230   1.0000
  12.000   1.3874   0.03824   0.03158  -0.0449   0.0219   1.0000
  12.250   1.3919   0.04011   0.03367  -0.0433   0.0209   1.0000
  12.500   1.3950   0.04212   0.03585  -0.0418   0.0200   1.0000
  12.750   1.3971   0.04423   0.03810  -0.0406   0.0192   1.0000
  13.000   1.3980   0.04652   0.04053  -0.0397   0.0185   1.0000
  13.250   1.3965   0.04921   0.04334  -0.0391   0.0180   1.0000
  13.500   1.3910   0.05258   0.04682  -0.0389   0.0174   1.0000
  13.750   1.3868   0.05611   0.05059  -0.0390   0.0169   1.0000
  14.000   1.3805   0.06010   0.05482  -0.0396   0.0164   1.0000
  14.250   1.3723   0.06458   0.05952  -0.0407   0.0159   1.0000
  14.500   1.3626   0.06955   0.06470  -0.0425   0.0155   1.0000
  14.750   1.3511   0.07514   0.07050  -0.0450   0.0152   1.0000
  15.000   1.3380   0.08135   0.07691  -0.0481   0.0149   1.0000
  15.250   1.3229   0.08836   0.08412  -0.0520   0.0148   1.0000
  15.500   1.3052   0.09630   0.09227  -0.0566   0.0147   1.0000
  15.750   1.2847   0.10532   0.10149  -0.0620   0.0146   1.0000
  16.000   1.2593   0.11592   0.11231  -0.0686   0.0147   1.0000
  16.250   1.2249   0.12946   0.12609  -0.0772   0.0151   1.0000
  16.500   1.1696   0.15010   0.14698  -0.0904   0.0161   1.0000
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