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TSAGI 8% AIRFOIL (tsagi8-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: TSAGI 8% AIRFOIL (tsagi8-il)
Reynolds number: 50,000
Max Cl/Cd: 32.48 at α=5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-tsagi8-il-50000-n5.txt
Download as CSV file: xf-tsagi8-il-50000-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 =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.4610   0.09724   0.09089  -0.0110   1.0000   0.0480
  -9.250  -0.4631   0.09265   0.08630  -0.0130   1.0000   0.0450
  -9.000  -0.5580   0.09743   0.09072  -0.0118   1.0000   0.0453
  -8.750  -0.5553   0.09321   0.08654  -0.0125   1.0000   0.0440
  -8.500  -0.5563   0.08891   0.08230  -0.0147   1.0000   0.0430
  -8.250  -0.5604   0.08450   0.07794  -0.0168   1.0000   0.0420
  -8.000  -0.5649   0.08019   0.07366  -0.0183   1.0000   0.0410
  -7.750  -0.5678   0.07570   0.06915  -0.0199   1.0000   0.0399
  -7.500  -0.5700   0.07103   0.06441  -0.0211   1.0000   0.0388
  -7.250  -0.5719   0.06601   0.05924  -0.0218   1.0000   0.0377
  -6.750  -0.5677   0.05670   0.04918  -0.0210   1.0000   0.0355
  -6.500  -0.5608   0.05277   0.04493  -0.0197   1.0000   0.0356
  -6.250  -0.5521   0.04916   0.04121  -0.0186   1.0000   0.0366
  -6.000  -0.5402   0.04649   0.03841  -0.0173   1.0000   0.0388
  -5.750  -0.5281   0.04332   0.03488  -0.0156   1.0000   0.0403
  -5.500  -0.5144   0.04009   0.03120  -0.0138   1.0000   0.0412
  -5.250  -0.4987   0.03690   0.02745  -0.0117   1.0000   0.0419
  -5.000  -0.4805   0.03395   0.02398  -0.0098   1.0000   0.0430
  -4.750  -0.4596   0.03152   0.02091  -0.0079   1.0000   0.0460
  -4.500  -0.4399   0.02934   0.01863  -0.0068   1.0000   0.0510
  -4.250  -0.4156   0.02723   0.01617  -0.0055   1.0000   0.0556
  -4.000  -0.3909   0.02543   0.01417  -0.0045   1.0000   0.0638
  -3.750  -0.3648   0.02389   0.01243  -0.0036   1.0000   0.0759
  -3.500  -0.3391   0.02257   0.01099  -0.0031   1.0000   0.0950
  -3.250  -0.3148   0.02121   0.00960  -0.0023   1.0000   0.1216
  -3.000  -0.2947   0.01989   0.00851  -0.0010   1.0000   0.1722
  -2.750  -0.1651   0.01691   0.00803  -0.0167   1.0000   0.9604
  -2.500  -0.0904   0.01669   0.00709  -0.0263   1.0000   1.0000
  -2.250  -0.0733   0.01655   0.00669  -0.0248   1.0000   1.0000
  -2.000  -0.0568   0.01645   0.00640  -0.0232   1.0000   1.0000
  -1.750  -0.0413   0.01639   0.00617  -0.0213   1.0000   1.0000
  -1.500  -0.0270   0.01638   0.00603  -0.0193   1.0000   1.0000
  -1.250  -0.0140   0.01642   0.00593  -0.0172   1.0000   1.0000
  -1.000  -0.0030   0.01652   0.00594  -0.0147   1.0000   1.0000
  -0.750   0.0057   0.01669   0.00603  -0.0119   1.0000   1.0000
  -0.500   0.0122   0.01694   0.00620  -0.0089   1.0000   1.0000
  -0.250   0.0601   0.01706   0.00619  -0.0139   0.9804   1.0000
   0.000   0.1063   0.01718   0.00622  -0.0182   0.9625   1.0000
   0.250   0.1523   0.01725   0.00624  -0.0224   0.9449   1.0000
   0.500   0.1978   0.01729   0.00627  -0.0263   0.9275   1.0000
   0.750   0.2394   0.01733   0.00631  -0.0293   0.9087   1.0000
   1.000   0.2776   0.01737   0.00640  -0.0315   0.8889   1.0000
   1.250   0.3145   0.01742   0.00648  -0.0332   0.8701   1.0000
   1.500   0.3447   0.01754   0.00663  -0.0336   0.8492   1.0000
   1.750   0.3746   0.01765   0.00680  -0.0337   0.8298   1.0000
   2.000   0.4004   0.01783   0.00706  -0.0332   0.8096   1.0000
   2.250   0.4256   0.01801   0.00732  -0.0324   0.7900   1.0000
   2.500   0.4503   0.01820   0.00758  -0.0314   0.7716   1.0000
   2.750   0.4729   0.01846   0.00799  -0.0302   0.7517   1.0000
   3.000   0.4961   0.01870   0.00835  -0.0289   0.7329   1.0000
   3.250   0.5192   0.01895   0.00873  -0.0276   0.7147   1.0000
   3.500   0.5410   0.01925   0.00920  -0.0262   0.6949   1.0000
   3.750   0.5636   0.01953   0.00971  -0.0248   0.6757   1.0000
   4.000   0.5862   0.01982   0.01020  -0.0234   0.6560   1.0000
   4.250   0.6083   0.02013   0.01074  -0.0219   0.6344   1.0000
   4.500   0.6304   0.02042   0.01128  -0.0202   0.6118   1.0000
   4.750   0.6501   0.02058   0.01173  -0.0178   0.5805   1.0000
   5.000   0.6609   0.02035   0.01133  -0.0128   0.5048   1.0000
   5.250   0.6678   0.02076   0.01113  -0.0081   0.3674   1.0000
   5.500   0.6692   0.02346   0.01217  -0.0047   0.1262   1.0000
   5.750   0.6786   0.02603   0.01425  -0.0023   0.0766   1.0000
   6.000   0.6916   0.02778   0.01605  -0.0001   0.0600   1.0000
   6.250   0.7037   0.02963   0.01792   0.0022   0.0534   1.0000
   6.500   0.7201   0.03116   0.01973   0.0044   0.0466   1.0000
   6.750   0.7355   0.03309   0.02174   0.0062   0.0418   1.0000
   7.000   0.7583   0.03513   0.02406   0.0079   0.0393   1.0000
   7.250   0.7810   0.03743   0.02666   0.0093   0.0370   1.0000
   7.500   0.8000   0.03974   0.02918   0.0106   0.0343   1.0000
   7.750   0.8162   0.04275   0.03235   0.0119   0.0321   1.0000
   8.000   0.8305   0.04578   0.03589   0.0138   0.0314   1.0000
   8.250   0.8409   0.04906   0.03964   0.0157   0.0311   1.0000
   8.500   0.8471   0.05255   0.04357   0.0176   0.0309   1.0000
   8.750   0.8492   0.05612   0.04754   0.0196   0.0308   1.0000
   9.000   0.8477   0.05975   0.05151   0.0214   0.0309   1.0000
   9.250   0.8424   0.06337   0.05542   0.0231   0.0310   1.0000
   9.500   0.8319   0.06706   0.05936   0.0247   0.0309   1.0000
   9.750   0.8193   0.07043   0.06289   0.0261   0.0311   1.0000
  10.000   0.8036   0.07413   0.06671   0.0266   0.0312   1.0000
  10.250   0.7890   0.07829   0.07096   0.0256   0.0315   1.0000
  10.500   0.7741   0.08310   0.07586   0.0235   0.0317   1.0000
  10.750   0.7611   0.08843   0.08123   0.0206   0.0319   1.0000
  11.000   0.7496   0.09415   0.08698   0.0173   0.0321   1.0000
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