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TSAGI 8% AIRFOIL (tsagi8-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: TSAGI 8% AIRFOIL (tsagi8-il)
Reynolds number: 200,000
Max Cl/Cd: 55.41 at α=3.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-tsagi8-il-200000-n5.txt
Download as CSV file: xf-tsagi8-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: TSAGI 8% 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.5594   0.08431   0.08093  -0.0114   1.0000   0.0111
  -8.500  -0.5657   0.07937   0.07605  -0.0149   1.0000   0.0107
  -8.250  -0.5754   0.07455   0.07125  -0.0181   1.0000   0.0107
  -8.000  -0.5829   0.06983   0.06651  -0.0198   1.0000   0.0106
  -7.750  -0.5948   0.06180   0.05837  -0.0221   1.0000   0.0092
  -7.500  -0.5913   0.05859   0.05507  -0.0222   1.0000   0.0097
  -7.250  -0.5891   0.05408   0.05042  -0.0219   1.0000   0.0100
  -7.000  -0.5842   0.04992   0.04608  -0.0212   1.0000   0.0104
  -6.750  -0.5797   0.04510   0.04100  -0.0197   1.0000   0.0104
  -6.500  -0.5720   0.04112   0.03676  -0.0178   1.0000   0.0110
  -6.250  -0.5655   0.03646   0.03172  -0.0152   1.0000   0.0109
  -6.000  -0.5580   0.03199   0.02679  -0.0120   1.0000   0.0108
  -5.750  -0.5476   0.02829   0.02261  -0.0089   1.0000   0.0108
  -5.500  -0.5341   0.02527   0.01912  -0.0061   1.0000   0.0109
  -5.250  -0.5179   0.02281   0.01623  -0.0037   1.0000   0.0113
  -5.000  -0.4997   0.02079   0.01385  -0.0015   1.0000   0.0119
  -4.750  -0.4803   0.01926   0.01204   0.0003   1.0000   0.0127
  -4.500  -0.4599   0.01847   0.01102   0.0019   1.0000   0.0142
  -4.250  -0.4367   0.01651   0.00882   0.0029   0.9981   0.0154
  -4.000  -0.4042   0.01507   0.00726   0.0018   0.9906   0.0178
  -3.750  -0.3701   0.01431   0.00640   0.0004   0.9823   0.0226
  -3.500  -0.3370   0.01344   0.00542  -0.0008   0.9732   0.0280
  -3.250  -0.3032   0.01278   0.00472  -0.0022   0.9631   0.0411
  -3.000  -0.2691   0.01223   0.00418  -0.0036   0.9522   0.0615
  -2.750  -0.2361   0.01166   0.00375  -0.0049   0.9394   0.1030
  -2.500  -0.2037   0.01110   0.00336  -0.0061   0.9253   0.1613
  -2.250  -0.1740   0.01049   0.00305  -0.0068   0.9090   0.2578
  -2.000  -0.1516   0.00948   0.00276  -0.0060   0.8908   0.4515
  -1.750  -0.1099   0.00817   0.00294  -0.0080   0.8801   0.8494
  -1.500  -0.0504   0.00835   0.00301  -0.0140   0.8675   0.9089
  -1.250  -0.0092   0.00849   0.00298  -0.0164   0.8491   0.9292
  -1.000   0.0351   0.00881   0.00314  -0.0192   0.8311   0.9546
  -0.750   0.0867   0.00904   0.00321  -0.0239   0.8133   0.9709
  -0.500   0.1344   0.00914   0.00316  -0.0280   0.7946   0.9831
  -0.250   0.1760   0.00914   0.00303  -0.0310   0.7754   0.9906
   0.000   0.2114   0.00913   0.00290  -0.0327   0.7567   0.9955
   0.250   0.2447   0.00909   0.00276  -0.0340   0.7382   0.9990
   0.500   0.2707   0.00910   0.00269  -0.0338   0.7205   1.0000
   0.750   0.2935   0.00914   0.00266  -0.0328   0.7037   1.0000
   1.000   0.3165   0.00919   0.00263  -0.0319   0.6877   1.0000
   1.250   0.3395   0.00924   0.00263  -0.0310   0.6720   1.0000
   1.500   0.3628   0.00929   0.00265  -0.0301   0.6563   1.0000
   1.750   0.3861   0.00936   0.00270  -0.0292   0.6407   1.0000
   2.000   0.4095   0.00943   0.00275  -0.0284   0.6250   1.0000
   2.250   0.4330   0.00951   0.00283  -0.0275   0.6094   1.0000
   2.500   0.4564   0.00960   0.00293  -0.0267   0.5930   1.0000
   2.750   0.4798   0.00971   0.00304  -0.0258   0.5757   1.0000
   3.000   0.5031   0.00982   0.00316  -0.0249   0.5569   1.0000
   3.250   0.5264   0.00994   0.00330  -0.0240   0.5362   1.0000
   3.500   0.5493   0.01010   0.00347  -0.0230   0.5110   1.0000
   3.750   0.5713   0.01031   0.00362  -0.0219   0.4757   1.0000
   4.000   0.5914   0.01068   0.00377  -0.0204   0.4125   1.0000
   4.250   0.6088   0.01141   0.00400  -0.0187   0.3015   1.0000
   4.500   0.6237   0.01267   0.00454  -0.0171   0.1516   1.0000
   4.750   0.6386   0.01406   0.00537  -0.0153   0.0429   1.0000
   5.000   0.6580   0.01486   0.00614  -0.0138   0.0253   1.0000
   5.250   0.6778   0.01555   0.00695  -0.0123   0.0198   1.0000
   5.500   0.6973   0.01626   0.00780  -0.0108   0.0170   1.0000
   5.750   0.7150   0.01719   0.00886  -0.0090   0.0151   1.0000
   6.000   0.7289   0.01864   0.01042  -0.0067   0.0132   1.0000
   6.250   0.7462   0.01970   0.01162  -0.0049   0.0119   1.0000
   6.500   0.7633   0.02097   0.01302  -0.0029   0.0112   1.0000
   6.750   0.7808   0.02239   0.01458  -0.0011   0.0108   1.0000
   7.000   0.7987   0.02406   0.01643   0.0007   0.0102   1.0000
   7.250   0.8166   0.02591   0.01851   0.0025   0.0099   1.0000
   7.500   0.8336   0.02780   0.02065   0.0043   0.0095   1.0000
   7.750   0.8494   0.02917   0.02219   0.0059   0.0086   1.0000
   8.000   0.8626   0.03090   0.02408   0.0076   0.0080   1.0000
   8.500   0.8761   0.03728   0.03117   0.0127   0.0074   1.0000
   8.750   0.8803   0.04007   0.03433   0.0154   0.0074   1.0000
   9.000   0.8804   0.04313   0.03773   0.0182   0.0074   1.0000
   9.250   0.8765   0.04626   0.04115   0.0211   0.0074   1.0000
   9.500   0.8679   0.04941   0.04459   0.0240   0.0073   1.0000
   9.750   0.8551   0.05216   0.04752   0.0272   0.0074   1.0000
  10.000   0.8393   0.05527   0.05078   0.0294   0.0074   1.0000
  10.250   0.8239   0.05881   0.05448   0.0299   0.0074   1.0000
  10.500   0.8078   0.06317   0.05900   0.0288   0.0075   1.0000
  10.750   0.7909   0.06828   0.06424   0.0261   0.0075   1.0000
  11.000   0.6972   0.06212   0.05836   0.0276   0.0076   1.0000
  11.250   0.6818   0.06824   0.06460   0.0245   0.0077   1.0000
  11.500   0.6625   0.07597   0.07245   0.0204   0.0078   1.0000
  11.750   0.6386   0.08606   0.08265   0.0151   0.0081   1.0000
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