Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

TSAGI 12% AIRFOIL (tsagi12-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: TSAGI 12% AIRFOIL (tsagi12-il)
Reynolds number: 200,000
Max Cl/Cd: 66.6 at α=7°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-tsagi12-il-200000.txt
Download as CSV file: xf-tsagi12-il-200000.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 =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.250  -0.4749   0.11199   0.10831  -0.0219   1.0000   0.0583
 -11.000  -0.4961   0.10576   0.10217  -0.0300   1.0000   0.0605
 -10.750  -0.5065   0.09993   0.09639  -0.0349   1.0000   0.0607
 -10.500  -0.5075   0.09445   0.09094  -0.0339   1.0000   0.0622
 -10.250  -0.4938   0.09287   0.08936  -0.0312   1.0000   0.0635
 -10.000  -0.4920   0.08945   0.08596  -0.0318   1.0000   0.0647
  -9.750  -0.4940   0.08554   0.08208  -0.0333   1.0000   0.0662
  -9.500  -0.5039   0.08032   0.07691  -0.0368   1.0000   0.0670
  -9.250  -0.5229   0.07444   0.07105  -0.0412   1.0000   0.0671
  -9.000  -0.5446   0.07003   0.06662  -0.0416   1.0000   0.0680
  -8.750  -0.5683   0.06662   0.06318  -0.0390   1.0000   0.0690
  -8.500  -0.5867   0.06312   0.05959  -0.0364   1.0000   0.0701
  -8.250  -0.6983   0.04424   0.03927  -0.0222   1.0000   0.0402
  -8.000  -0.6976   0.04086   0.03576  -0.0187   1.0000   0.0392
  -7.750  -0.7039   0.03775   0.03239  -0.0136   1.0000   0.0390
  -7.500  -0.7097   0.03514   0.02949  -0.0083   1.0000   0.0389
  -7.250  -0.7151   0.03292   0.02697  -0.0029   1.0000   0.0390
  -7.000  -0.7175   0.03129   0.02503   0.0021   0.9998   0.0394
  -6.750  -0.6870   0.02777   0.02109   0.0003   0.9940   0.0419
  -6.500  -0.6510   0.02615   0.01929  -0.0019   0.9874   0.0442
  -6.250  -0.6124   0.02413   0.01692  -0.0041   0.9824   0.0467
  -6.000  -0.5764   0.02263   0.01505  -0.0057   0.9747   0.0504
  -5.750  -0.5351   0.02105   0.01344  -0.0089   0.9704   0.0541
  -5.500  -0.4967   0.02014   0.01238  -0.0109   0.9621   0.0591
  -5.250  -0.4522   0.01863   0.01081  -0.0144   0.9571   0.0648
  -5.000  -0.4105   0.01779   0.00989  -0.0172   0.9490   0.0719
  -4.750  -0.3689   0.01643   0.00857  -0.0201   0.9421   0.0804
  -4.500  -0.3343   0.01543   0.00759  -0.0215   0.9316   0.0920
  -4.250  -0.3002   0.01451   0.00674  -0.0228   0.9215   0.1100
  -4.000  -0.2679   0.01383   0.00612  -0.0237   0.9102   0.1328
  -3.750  -0.2410   0.01330   0.00568  -0.0235   0.8962   0.1608
  -3.500  -0.2187   0.01264   0.00528  -0.0224   0.8819   0.2127
  -3.250  -0.2018   0.01186   0.00493  -0.0203   0.8678   0.3147
  -3.000  -0.1957   0.01083   0.00467  -0.0159   0.8536   0.4918
  -2.750  -0.1085   0.01025   0.00540  -0.0262   0.8492   0.8503
  -2.500  -0.0701   0.01074   0.00574  -0.0273   0.8366   0.8793
  -2.250  -0.0331   0.01126   0.00609  -0.0282   0.8243   0.8973
  -2.000   0.0128   0.01184   0.00649  -0.0309   0.8129   0.9117
  -1.750   0.0613   0.01231   0.00678  -0.0343   0.8015   0.9231
  -1.500   0.1083   0.01269   0.00700  -0.0376   0.7894   0.9351
  -1.250   0.1482   0.01292   0.00710  -0.0398   0.7767   0.9458
  -1.000   0.1936   0.01305   0.00711  -0.0431   0.7642   0.9547
  -0.750   0.2544   0.01325   0.00718  -0.0495   0.7516   0.9714
  -0.500   0.3320   0.01284   0.00664  -0.0595   0.7385   0.9889
  -0.250   0.3726   0.01255   0.00624  -0.0624   0.7252   0.9958
   0.000   0.4075   0.01227   0.00586  -0.0642   0.7123   1.0000
   0.250   0.4277   0.01222   0.00576  -0.0630   0.6990   1.0000
   0.500   0.4481   0.01219   0.00566  -0.0618   0.6859   1.0000
   0.750   0.4688   0.01218   0.00559  -0.0607   0.6729   1.0000
   1.000   0.4897   0.01218   0.00553  -0.0595   0.6604   1.0000
   1.250   0.5108   0.01220   0.00548  -0.0584   0.6480   1.0000
   1.500   0.5321   0.01224   0.00544  -0.0572   0.6360   1.0000
   1.750   0.5532   0.01227   0.00544  -0.0561   0.6232   1.0000
   2.000   0.5746   0.01231   0.00547  -0.0550   0.6107   1.0000
   2.250   0.5961   0.01238   0.00551  -0.0539   0.5990   1.0000
   2.500   0.6179   0.01245   0.00554  -0.0529   0.5879   1.0000
   2.750   0.6397   0.01253   0.00558  -0.0518   0.5771   1.0000
   3.000   0.6613   0.01261   0.00568  -0.0508   0.5656   1.0000
   3.250   0.6832   0.01270   0.00577  -0.0497   0.5552   1.0000
   3.500   0.7054   0.01281   0.00583  -0.0487   0.5459   1.0000
   3.750   0.7270   0.01290   0.00598  -0.0477   0.5348   1.0000
   4.000   0.7490   0.01302   0.00612  -0.0466   0.5251   1.0000
   4.250   0.7713   0.01316   0.00622  -0.0456   0.5161   1.0000
   4.500   0.7927   0.01326   0.00640  -0.0445   0.5052   1.0000
   4.750   0.8141   0.01339   0.00657  -0.0433   0.4943   1.0000
   5.000   0.8357   0.01354   0.00672  -0.0422   0.4839   1.0000
   5.250   0.8571   0.01369   0.00689  -0.0410   0.4730   1.0000
   5.500   0.8775   0.01382   0.00707  -0.0396   0.4598   1.0000
   5.750   0.8968   0.01395   0.00717  -0.0380   0.4427   1.0000
   6.000   0.9153   0.01406   0.00733  -0.0363   0.4232   1.0000
   6.250   0.9342   0.01422   0.00753  -0.0346   0.4057   1.0000
   6.500   0.9524   0.01439   0.00771  -0.0329   0.3856   1.0000
   6.750   0.9702   0.01458   0.00795  -0.0311   0.3636   1.0000
   7.000   0.9870   0.01482   0.00820  -0.0291   0.3378   1.0000
   7.250   1.0023   0.01515   0.00850  -0.0269   0.2986   1.0000
   7.500   1.0085   0.01607   0.00904  -0.0234   0.2234   1.0000
   7.750   0.9977   0.01829   0.01039  -0.0177   0.1015   1.0000
   8.000   0.9930   0.02004   0.01181  -0.0125   0.0625   1.0000
   8.250   0.9964   0.02113   0.01288  -0.0085   0.0523   1.0000
   8.500   0.9994   0.02213   0.01396  -0.0044   0.0476   1.0000
   8.750   1.0015   0.02307   0.01495  -0.0003   0.0441   1.0000
   9.000   0.9965   0.02416   0.01604   0.0048   0.0418   1.0000
   9.250   0.9883   0.02518   0.01712   0.0106   0.0398   1.0000
   9.500   0.9862   0.02616   0.01818   0.0150   0.0384   1.0000
   9.750   0.9854   0.02731   0.01939   0.0188   0.0372   1.0000
  10.000   0.9860   0.02859   0.02072   0.0221   0.0358   1.0000
  10.250   0.9882   0.02998   0.02213   0.0250   0.0346   1.0000
  10.500   0.9928   0.03151   0.02367   0.0274   0.0335   1.0000
  10.750   1.0038   0.03351   0.02567   0.0294   0.0318   1.0000
  11.000   1.0136   0.03474   0.02704   0.0313   0.0309   1.0000
  11.250   1.0256   0.03618   0.02859   0.0330   0.0300   1.0000
  11.500   1.0388   0.03781   0.03035   0.0345   0.0290   1.0000
  11.750   1.0523   0.03960   0.03229   0.0360   0.0285   1.0000
  12.000   1.0636   0.04157   0.03442   0.0375   0.0280   1.0000
  12.250   1.0725   0.04370   0.03672   0.0390   0.0275   1.0000
  12.500   1.0789   0.04601   0.03920   0.0405   0.0270   1.0000
  12.750   1.0811   0.04831   0.04167   0.0420   0.0267   1.0000
  13.000   1.0828   0.05076   0.04423   0.0433   0.0261   1.0000
  13.250   1.0822   0.05370   0.04734   0.0445   0.0258   1.0000
  13.500   1.0785   0.05717   0.05097   0.0455   0.0254   1.0000
  13.750   1.0683   0.06109   0.05511   0.0464   0.0252   1.0000
  14.000   1.0558   0.06392   0.05817   0.0469   0.0256   1.0000
  14.250   1.0425   0.06801   0.06245   0.0470   0.0254   1.0000
  14.500   1.0253   0.07205   0.06673   0.0463   0.0258   1.0000
  14.750   1.0047   0.07712   0.07203   0.0451   0.0259   1.0000
  15.000   0.9495   0.08708   0.08249   0.0401   0.0274   1.0000
  15.250   0.9186   0.09526   0.09090   0.0358   0.0279   1.0000
  15.500   0.8880   0.10420   0.10003   0.0307   0.0281   1.0000
  15.750   0.8485   0.11622   0.11222   0.0236   0.0293   1.0000
  16.000   0.8123   0.12897   0.12507   0.0163   0.0304   1.0000
  16.250   0.7963   0.13716   0.13326   0.0131   0.0317   1.0000
<< Back to TSAGI 12% AIRFOIL (tsagi12-il)

Polar data table (+)

Polar graphs


<< Back to TSAGI 12% AIRFOIL (tsagi12-il)