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I.S.A. 961 (isa961-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: I.S.A. 961 (isa961-il)
Reynolds number: 100,000
Max Cl/Cd: 53.94 at α=5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-isa961-il-100000-n5.txt
Download as CSV file: xf-isa961-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: I.S.A. 961                                      
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.3329   0.09245   0.08783  -0.0331   1.0000   0.0256
  -8.750  -0.3416   0.09019   0.08568  -0.0318   1.0000   0.0253
  -8.500  -0.3553   0.08839   0.08399  -0.0295   1.0000   0.0251
  -8.250  -0.3680   0.08636   0.08206  -0.0277   1.0000   0.0249
  -8.000  -0.3788   0.08401   0.07979  -0.0267   1.0000   0.0247
  -7.750  -0.3707   0.07940   0.07521  -0.0314   0.9961   0.0247
  -7.500  -0.3484   0.07303   0.06879  -0.0403   0.9890   0.0251
  -7.250  -0.3238   0.06595   0.06162  -0.0498   0.9816   0.0256
  -7.000  -0.2955   0.05813   0.05365  -0.0596   0.9750   0.0258
  -6.750  -0.2669   0.04922   0.04446  -0.0687   0.9677   0.0257
  -6.500  -0.2370   0.03376   0.02790  -0.0796   0.9615   0.0255
  -6.250  -0.2062   0.02764   0.02070  -0.0828   0.9566   0.0264
  -6.000  -0.1714   0.02492   0.01743  -0.0850   0.9531   0.0283
  -5.750  -0.1406   0.02391   0.01628  -0.0860   0.9472   0.0318
  -5.500  -0.1069   0.02219   0.01414  -0.0873   0.9425   0.0357
  -5.250  -0.0698   0.02134   0.01317  -0.0892   0.9388   0.0419
  -5.000  -0.0373   0.02086   0.01255  -0.0900   0.9329   0.0557
  -4.750  -0.0031   0.02051   0.01200  -0.0911   0.9273   0.0744
  -4.500   0.0339   0.02036   0.01160  -0.0930   0.9232   0.0925
  -4.250   0.0637   0.02047   0.01162  -0.0934   0.9154   0.1065
  -4.000   0.0995   0.02014   0.01129  -0.0949   0.9094   0.1145
  -3.750   0.1323   0.01947   0.01038  -0.0955   0.9010   0.1184
  -3.500   0.1676   0.01885   0.00967  -0.0966   0.8936   0.1227
  -3.250   0.1973   0.01848   0.00923  -0.0967   0.8841   0.1280
  -3.000   0.2312   0.01798   0.00857  -0.0975   0.8776   0.1331
  -2.750   0.2585   0.01761   0.00822  -0.0972   0.8677   0.1376
  -2.500   0.2894   0.01722   0.00778  -0.0974   0.8596   0.1446
  -2.250   0.3182   0.01685   0.00739  -0.0972   0.8491   0.1532
  -2.000   0.3455   0.01654   0.00709  -0.0968   0.8370   0.1669
  -1.750   0.3733   0.01621   0.00678  -0.0964   0.8244   0.1847
  -1.500   0.4007   0.01589   0.00646  -0.0958   0.8098   0.2060
  -1.250   0.4281   0.01558   0.00616  -0.0952   0.7925   0.2311
  -1.000   0.4559   0.01526   0.00586  -0.0947   0.7737   0.2649
  -0.750   0.4825   0.01495   0.00564  -0.0941   0.7538   0.3225
  -0.500   0.5191   0.01323   0.00547  -0.0953   0.7350   1.0000
  -0.250   0.5458   0.01329   0.00533  -0.0947   0.7181   1.0000
   0.000   0.5724   0.01336   0.00522  -0.0941   0.7001   1.0000
   0.250   0.5988   0.01345   0.00512  -0.0935   0.6806   1.0000
   0.500   0.6244   0.01358   0.00509  -0.0928   0.6587   1.0000
   0.750   0.6502   0.01372   0.00505  -0.0921   0.6364   1.0000
   1.000   0.6755   0.01389   0.00508  -0.0915   0.6133   1.0000
   1.250   0.7009   0.01409   0.00513  -0.0908   0.5915   1.0000
   1.500   0.7260   0.01431   0.00521  -0.0902   0.5692   1.0000
   1.750   0.7509   0.01455   0.00532  -0.0895   0.5467   1.0000
   2.000   0.7756   0.01482   0.00547  -0.0888   0.5244   1.0000
   2.250   0.8000   0.01511   0.00563  -0.0882   0.5028   1.0000
   2.500   0.8241   0.01543   0.00582  -0.0874   0.4815   1.0000
   2.750   0.8475   0.01580   0.00606  -0.0866   0.4573   1.0000
   3.000   0.8703   0.01621   0.00630  -0.0857   0.4319   1.0000
   3.250   0.8925   0.01667   0.00658  -0.0848   0.4067   1.0000
   3.500   0.9150   0.01710   0.00691  -0.0840   0.3817   1.0000
   3.750   0.9375   0.01754   0.00724  -0.0832   0.3609   1.0000
   4.000   0.9606   0.01794   0.00759  -0.0825   0.3438   1.0000
   4.250   0.9839   0.01833   0.00798  -0.0818   0.3305   1.0000
   4.500   1.0072   0.01872   0.00837  -0.0812   0.3185   1.0000
   4.750   1.0304   0.01912   0.00878  -0.0805   0.3073   1.0000
   5.000   1.0534   0.01953   0.00921  -0.0799   0.2969   1.0000
   5.250   1.0757   0.01998   0.00969  -0.0791   0.2865   1.0000
   5.500   1.0982   0.02041   0.01017  -0.0784   0.2758   1.0000
   5.750   1.1202   0.02088   0.01067  -0.0776   0.2656   1.0000
   6.250   1.1635   0.02185   0.01179  -0.0760   0.2468   1.0000
   6.500   1.1842   0.02237   0.01237  -0.0751   0.2367   1.0000
   6.750   1.2041   0.02295   0.01299  -0.0740   0.2258   1.0000
   7.000   1.2248   0.02347   0.01363  -0.0731   0.2154   1.0000
   7.250   1.2447   0.02404   0.01430  -0.0721   0.2062   1.0000
   7.500   1.2635   0.02465   0.01505  -0.0710   0.1953   1.0000
   7.750   1.2814   0.02532   0.01576  -0.0697   0.1719   1.0000
   8.000   1.2914   0.02648   0.01664  -0.0677   0.1411   1.0000
   8.250   1.3003   0.02777   0.01776  -0.0654   0.1260   1.0000
   8.500   1.3099   0.02887   0.01888  -0.0632   0.1176   1.0000
   8.750   1.3210   0.02987   0.01998  -0.0611   0.1108   1.0000
   9.000   1.3316   0.03094   0.02116  -0.0591   0.1025   1.0000
   9.250   1.3461   0.03174   0.02218  -0.0576   0.0944   1.0000
   9.750   1.3548   0.03497   0.02527  -0.0532   0.0577   1.0000
  10.000   1.3531   0.03714   0.02748  -0.0507   0.0520   1.0000
  10.250   1.3592   0.03873   0.02928  -0.0490   0.0472   1.0000
  10.750   1.3716   0.04208   0.03310  -0.0460   0.0345   1.0000
  11.000   1.3685   0.04471   0.03572  -0.0445   0.0228   1.0000
  11.250   1.3623   0.04781   0.03880  -0.0432   0.0208   1.0000
  11.500   1.3556   0.05114   0.04223  -0.0423   0.0194   1.0000
  11.750   1.3485   0.05472   0.04597  -0.0418   0.0185   1.0000
  12.000   1.3407   0.05859   0.05001  -0.0417   0.0180   1.0000
  12.250   1.3317   0.06283   0.05447  -0.0421   0.0177   1.0000
  12.500   1.3211   0.06754   0.05939  -0.0429   0.0175   1.0000
  12.750   1.3087   0.07274   0.06480  -0.0441   0.0173   1.0000
  13.000   1.2952   0.07842   0.07068  -0.0458   0.0172   1.0000
  13.250   1.2808   0.08453   0.07700  -0.0479   0.0171   1.0000
  13.500   1.2657   0.09097   0.08363  -0.0502   0.0170   1.0000
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