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TSAGI 12% AIRFOIL (tsagi12-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: TSAGI 12% AIRFOIL (tsagi12-il)
Reynolds number: 50,000
Max Cl/Cd: 31.39 at α=8.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-tsagi12-il-50000.txt
Download as CSV file: xf-tsagi12-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: TSAGI 12% AIRFOIL                               
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.250  -0.4664   0.13028   0.12305  -0.0092   1.0000   0.2335
 -11.000  -0.4490   0.12527   0.11803  -0.0087   1.0000   0.2418
 -10.750  -0.4747   0.12483   0.11773  -0.0108   1.0000   0.2497
 -10.500  -0.4457   0.11887   0.11171  -0.0094   1.0000   0.2612
 -10.250  -0.4416   0.11523   0.10811  -0.0096   1.0000   0.2703
 -10.000  -0.4665   0.11439   0.10741  -0.0110   1.0000   0.2802
  -9.750  -0.4574   0.11061   0.10365  -0.0103   1.0000   0.2952
  -9.500  -0.4512   0.10713   0.10021  -0.0096   1.0000   0.3103
  -9.250  -0.4489   0.10396   0.09709  -0.0090   1.0000   0.3256
  -9.000  -0.4459   0.10070   0.09388  -0.0082   1.0000   0.3410
  -8.750  -0.4462   0.09757   0.09082  -0.0074   1.0000   0.3568
  -8.500  -0.4152   0.09272   0.08589  -0.0059   1.0000   0.3772
  -8.250  -0.4205   0.09061   0.08385  -0.0042   1.0000   0.4009
  -8.000  -0.4010   0.08667   0.07991  -0.0028   1.0000   0.4235
  -7.750  -0.4146   0.08501   0.07837  -0.0004   1.0000   0.4484
  -7.500  -0.3957   0.08092   0.07427   0.0004   1.0000   0.4661
  -7.250  -0.5926   0.06510   0.05844  -0.0207   1.0000   0.1883
  -7.000  -0.5939   0.05971   0.05290  -0.0190   1.0000   0.1690
  -6.750  -0.6079   0.05540   0.04821  -0.0153   1.0000   0.1563
  -6.500  -0.6103   0.05183   0.04441  -0.0119   1.0000   0.1508
  -6.250  -0.6226   0.04865   0.04055  -0.0065   1.0000   0.1438
  -6.000  -0.6213   0.04592   0.03755  -0.0028   1.0000   0.1434
  -5.750  -0.6208   0.04361   0.03485   0.0013   1.0000   0.1440
  -5.500  -0.6139   0.04120   0.03238   0.0042   1.0000   0.1474
  -5.250  -0.6067   0.03904   0.02993   0.0074   1.0000   0.1490
  -5.000  -0.5974   0.03701   0.02757   0.0103   1.0000   0.1510
  -4.750  -0.5873   0.03534   0.02551   0.0132   1.0000   0.1564
  -4.500  -0.5742   0.03359   0.02348   0.0156   1.0000   0.1623
  -4.250  -0.5575   0.03203   0.02171   0.0174   1.0000   0.1689
  -4.000  -0.5400   0.03063   0.02008   0.0190   1.0000   0.1787
  -3.750  -0.5210   0.02942   0.01873   0.0204   1.0000   0.1926
  -3.500  -0.0663   0.02331   0.01479  -0.0418   1.0000   1.0000
  -3.250  -0.0713   0.02336   0.01474  -0.0381   1.0000   1.0000
  -3.000  -0.0814   0.02363   0.01492  -0.0336   1.0000   1.0000
  -2.750  -0.0917   0.02398   0.01518  -0.0291   1.0000   1.0000
  -2.500  -0.0995   0.02434   0.01542  -0.0250   1.0000   1.0000
  -2.250  -0.1048   0.02471   0.01566  -0.0212   1.0000   1.0000
  -2.000  -0.1078   0.02507   0.01590  -0.0178   1.0000   1.0000
  -1.750  -0.1089   0.02546   0.01616  -0.0147   1.0000   1.0000
  -1.500  -0.1084   0.02586   0.01643  -0.0118   1.0000   1.0000
  -1.250  -0.0630   0.02637   0.01670  -0.0172   0.9882   1.0000
  -1.000  -0.0049   0.02690   0.01701  -0.0247   0.9722   1.0000
  -0.750   0.0514   0.02735   0.01727  -0.0316   0.9564   1.0000
  -0.500   0.1049   0.02772   0.01750  -0.0377   0.9408   1.0000
  -0.250   0.1563   0.02803   0.01770  -0.0432   0.9253   1.0000
   0.000   0.2062   0.02830   0.01788  -0.0482   0.9100   1.0000
   0.250   0.2547   0.02852   0.01805  -0.0528   0.8949   1.0000
   0.500   0.3027   0.02871   0.01820  -0.0571   0.8800   1.0000
   0.750   0.3441   0.02894   0.01841  -0.0601   0.8651   1.0000
   1.000   0.3792   0.02925   0.01871  -0.0618   0.8503   1.0000
   1.250   0.4096   0.02965   0.01910  -0.0627   0.8356   1.0000
   1.500   0.4361   0.03012   0.01958  -0.0628   0.8210   1.0000
   1.750   0.4589   0.03069   0.02016  -0.0623   0.8068   1.0000
   2.000   0.4780   0.03139   0.02089  -0.0613   0.7931   1.0000
   2.250   0.4961   0.03213   0.02165  -0.0600   0.7798   1.0000
   2.500   0.5154   0.03287   0.02241  -0.0590   0.7675   1.0000
   2.750   0.5458   0.03321   0.02282  -0.0592   0.7565   1.0000
   3.000   0.5582   0.03419   0.02383  -0.0571   0.7440   1.0000
   3.250   0.5625   0.03549   0.02516  -0.0542   0.7314   1.0000
   3.500   0.5708   0.03670   0.02641  -0.0517   0.7198   1.0000
   3.750   0.5931   0.03739   0.02716  -0.0508   0.7092   1.0000
   4.000   0.6103   0.03828   0.02814  -0.0494   0.6984   1.0000
   4.250   0.6066   0.04005   0.02994  -0.0457   0.6863   1.0000
   4.500   0.6108   0.04154   0.03147  -0.0430   0.6751   1.0000
   4.750   0.6404   0.04198   0.03204  -0.0427   0.6651   1.0000
   5.000   0.6447   0.04351   0.03362  -0.0400   0.6536   1.0000
   5.250   0.6323   0.04583   0.03597  -0.0358   0.6420   1.0000
   5.500   0.6393   0.04735   0.03755  -0.0335   0.6309   1.0000
   5.750   0.6735   0.04759   0.03797  -0.0334   0.6199   1.0000
   6.000   0.6716   0.04954   0.03996  -0.0303   0.6081   1.0000
   6.250   0.6422   0.05261   0.04295  -0.0250   0.5972   1.0000
   6.500   0.6488   0.05423   0.04465  -0.0228   0.5855   1.0000
   6.750   0.6704   0.05522   0.04581  -0.0217   0.5732   1.0000
   7.000   0.7014   0.05565   0.04646  -0.0210   0.5600   1.0000
   7.250   0.6994   0.05767   0.04854  -0.0182   0.5472   1.0000
   7.500   0.6777   0.06095   0.05178  -0.0149   0.5352   1.0000
   7.750   0.7516   0.05828   0.04962  -0.0151   0.5164   1.0000
   8.000   0.7501   0.06001   0.05141  -0.0120   0.5001   1.0000
   8.250   0.7433   0.06215   0.05360  -0.0089   0.4830   1.0000
   8.500   1.0120   0.03224   0.02449  -0.0063   0.3664   1.0000
   8.750   0.9982   0.03197   0.02408   0.0015   0.3068   1.0000
   9.000   0.9767   0.03319   0.02466   0.0092   0.2432   1.0000
   9.250   0.9567   0.03539   0.02617   0.0157   0.1990   1.0000
   9.500   0.9448   0.03758   0.02795   0.0209   0.1710   1.0000
   9.750   0.9474   0.03987   0.02995   0.0242   0.1483   1.0000
  10.000   0.9608   0.04206   0.03201   0.0262   0.1302   1.0000
  10.250   1.0169   0.04537   0.03501   0.0234   0.1123   1.0000
  10.500   1.0283   0.04789   0.03796   0.0255   0.1070   1.0000
  10.750   1.0611   0.05137   0.04137   0.0247   0.0990   1.0000
  11.000   1.0600   0.05408   0.04452   0.0278   0.0974   1.0000
  11.250   1.0581   0.05720   0.04801   0.0307   0.0964   1.0000
  11.500   1.0488   0.06029   0.05141   0.0342   0.0959   1.0000
  11.750   1.0355   0.06339   0.05477   0.0375   0.0958   1.0000
  12.000   1.0183   0.06673   0.05836   0.0402   0.0960   1.0000
  12.250   0.9984   0.07047   0.06232   0.0421   0.0963   1.0000
  12.500   0.9754   0.07477   0.06681   0.0430   0.0967   1.0000
  12.750   0.9518   0.07955   0.07176   0.0428   0.0973   1.0000
  13.000   0.9286   0.08496   0.07729   0.0418   0.0980   1.0000
  13.250   0.9094   0.09083   0.08326   0.0404   0.0989   1.0000
  13.500   0.7909   0.11150   0.10402   0.0251   0.1104   1.0000
  13.750   0.7748   0.11988   0.11236   0.0217   0.1118   1.0000
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