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S2046 (s2046-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: S2046 (s2046-il)
Reynolds number: 100,000
Max Cl/Cd: 55.89 at α=4°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s2046-il-100000-n5.txt
Download as CSV file: xf-s2046-il-100000-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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.4679   0.07716   0.07207  -0.0402   1.0000   0.0294
  -8.500  -0.4760   0.07239   0.06738  -0.0422   1.0000   0.0293
  -8.250  -0.4874   0.06695   0.06202  -0.0451   1.0000   0.0291
  -8.000  -0.4984   0.05984   0.05491  -0.0517   1.0000   0.0287
  -7.750  -0.5078   0.05385   0.04878  -0.0558   1.0000   0.0285
  -7.500  -0.5125   0.04826   0.04294  -0.0585   1.0000   0.0284
  -7.250  -0.5109   0.04301   0.03731  -0.0605   1.0000   0.0283
  -7.000  -0.5027   0.03825   0.03206  -0.0618   1.0000   0.0283
  -6.750  -0.4889   0.03416   0.02743  -0.0626   1.0000   0.0285
  -6.500  -0.4712   0.03077   0.02348  -0.0629   1.0000   0.0290
  -6.250  -0.4510   0.02815   0.02039  -0.0629   1.0000   0.0295
  -6.000  -0.4306   0.02613   0.01816  -0.0626   1.0000   0.0303
  -5.750  -0.4092   0.02467   0.01651  -0.0623   1.0000   0.0314
  -5.500  -0.3873   0.02355   0.01522  -0.0618   1.0000   0.0334
  -5.250  -0.3647   0.02247   0.01391  -0.0613   1.0000   0.0364
  -5.000  -0.3404   0.02124   0.01249  -0.0610   0.9996   0.0390
  -4.750  -0.3061   0.02015   0.01137  -0.0628   0.9957   0.0427
  -4.500  -0.2717   0.01912   0.01015  -0.0643   0.9916   0.0489
  -4.250  -0.2373   0.01836   0.00934  -0.0661   0.9871   0.0607
  -4.000  -0.2013   0.01777   0.00882  -0.0682   0.9831   0.0780
  -3.750  -0.1685   0.01742   0.00844  -0.0696   0.9773   0.1004
  -3.500  -0.1335   0.01689   0.00795  -0.0714   0.9725   0.1197
  -3.250  -0.0987   0.01643   0.00749  -0.0731   0.9678   0.1407
  -3.000  -0.0657   0.01596   0.00710  -0.0744   0.9617   0.1661
  -2.750  -0.0292   0.01544   0.00674  -0.0765   0.9572   0.2118
  -2.500   0.0035   0.01481   0.00650  -0.0780   0.9512   0.3023
  -2.250   0.0366   0.01430   0.00651  -0.0793   0.9454   0.4425
  -2.000   0.0730   0.01414   0.00653  -0.0808   0.9408   0.5301
  -1.750   0.1029   0.01407   0.00655  -0.0809   0.9326   0.5820
  -1.500   0.1394   0.01400   0.00651  -0.0822   0.9274   0.6240
  -1.250   0.1690   0.01395   0.00648  -0.0822   0.9183   0.6578
  -1.000   0.2041   0.01386   0.00641  -0.0830   0.9116   0.6930
  -0.750   0.2333   0.01376   0.00638  -0.0826   0.9017   0.7268
  -0.500   0.2618   0.01365   0.00631  -0.0820   0.8916   0.7590
  -0.250   0.2926   0.01349   0.00617  -0.0819   0.8825   0.7857
   0.000   0.3209   0.01335   0.00604  -0.0814   0.8715   0.8069
   0.250   0.3479   0.01321   0.00591  -0.0807   0.8595   0.8277
   0.500   0.3750   0.01303   0.00577  -0.0799   0.8479   0.8507
   0.750   0.4030   0.01283   0.00561  -0.0793   0.8363   0.8790
   1.000   0.4362   0.01259   0.00542  -0.0798   0.8246   0.9241
   1.250   0.4720   0.01248   0.00528  -0.0811   0.8112   1.0000
   1.500   0.5023   0.01250   0.00524  -0.0814   0.7964   1.0000
   1.750   0.5316   0.01254   0.00525  -0.0815   0.7800   1.0000
   2.000   0.5604   0.01259   0.00526  -0.0814   0.7622   1.0000
   2.250   0.5890   0.01265   0.00527  -0.0812   0.7433   1.0000
   2.500   0.6177   0.01271   0.00528  -0.0810   0.7232   1.0000
   2.750   0.6450   0.01281   0.00536  -0.0805   0.6996   1.0000
   3.000   0.6723   0.01294   0.00542  -0.0801   0.6742   1.0000
   3.250   0.6992   0.01309   0.00550  -0.0795   0.6456   1.0000
   3.500   0.7256   0.01329   0.00563  -0.0789   0.6132   1.0000
   3.750   0.7514   0.01355   0.00576  -0.0781   0.5772   1.0000
   4.000   0.7763   0.01389   0.00593  -0.0773   0.5363   1.0000
   4.250   0.8003   0.01432   0.00615  -0.0763   0.4926   1.0000
   4.500   0.8237   0.01483   0.00647  -0.0754   0.4491   1.0000
   4.750   0.8470   0.01537   0.00682  -0.0746   0.4091   1.0000
   5.000   0.8703   0.01594   0.00722  -0.0738   0.3729   1.0000
   5.250   0.8936   0.01650   0.00766  -0.0730   0.3385   1.0000
   5.500   0.9167   0.01709   0.00817  -0.0723   0.3046   1.0000
   5.750   0.9394   0.01771   0.00868  -0.0716   0.2705   1.0000
   6.000   0.9620   0.01838   0.00924  -0.0708   0.2352   1.0000
   6.250   0.9836   0.01916   0.00986  -0.0700   0.1970   1.0000
   6.500   1.0048   0.02003   0.01059  -0.0692   0.1606   1.0000
   6.750   1.0254   0.02100   0.01142  -0.0683   0.1330   1.0000
   7.000   1.0453   0.02205   0.01233  -0.0673   0.1135   1.0000
   7.500   1.0856   0.02405   0.01437  -0.0653   0.0907   1.0000
   7.750   1.1046   0.02514   0.01551  -0.0642   0.0833   1.0000
   8.000   1.1237   0.02620   0.01662  -0.0631   0.0764   1.0000
   8.250   1.1419   0.02740   0.01788  -0.0619   0.0715   1.0000
   8.500   1.1609   0.02857   0.01918  -0.0607   0.0672   1.0000
   8.750   1.1785   0.02984   0.02047  -0.0595   0.0633   1.0000
   9.000   1.1964   0.03123   0.02199  -0.0584   0.0597   1.0000
   9.250   1.2150   0.03255   0.02350  -0.0572   0.0561   1.0000
   9.500   1.2326   0.03400   0.02505  -0.0561   0.0534   1.0000
   9.750   1.2487   0.03562   0.02669  -0.0550   0.0508   1.0000
  10.000   1.2651   0.03732   0.02864  -0.0538   0.0480   1.0000
  10.250   1.2804   0.03907   0.03066  -0.0524   0.0455   1.0000
  10.500   1.2939   0.04086   0.03264  -0.0510   0.0433   1.0000
  10.750   1.3053   0.04250   0.03439  -0.0496   0.0412   1.0000
  11.000   1.3148   0.04476   0.03674  -0.0481   0.0393   1.0000
  11.250   1.3183   0.04695   0.03934  -0.0457   0.0377   1.0000
  11.500   1.3190   0.04944   0.04216  -0.0434   0.0363   1.0000
  11.750   1.3169   0.05191   0.04491  -0.0412   0.0348   1.0000
  12.000   1.3136   0.05434   0.04754  -0.0395   0.0336   1.0000
  12.250   1.3107   0.05676   0.05012  -0.0381   0.0325   1.0000
  12.500   1.3079   0.05939   0.05284  -0.0373   0.0315   1.0000
  12.750   1.3024   0.06284   0.05640  -0.0367   0.0307   1.0000
  13.000   1.2881   0.06739   0.06124  -0.0368   0.0304   1.0000
  13.250   1.2702   0.07267   0.06683  -0.0379   0.0301   1.0000
  13.500   1.2501   0.07872   0.07318  -0.0401   0.0299   1.0000
  13.750   1.2280   0.08570   0.08043  -0.0435   0.0298   1.0000
  14.000   1.2040   0.09374   0.08870  -0.0482   0.0299   1.0000
  14.250   1.1784   0.10295   0.09812  -0.0542   0.0301   1.0000
  14.500   1.1513   0.11349   0.10883  -0.0613   0.0303   1.0000
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