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I.S.A. 960 (isa960-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: I.S.A. 960 (isa960-il)
Reynolds number: 100,000
Max Cl/Cd: 49.75 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-isa960-il-100000-n5.txt
Download as CSV file: xf-isa960-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: I.S.A. 960                                      
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.3361   0.09252   0.08802  -0.0355   1.0000   0.0319
  -9.000  -0.3432   0.08999   0.08559  -0.0347   1.0000   0.0315
  -8.750  -0.3553   0.08794   0.08365  -0.0328   1.0000   0.0312
  -8.500  -0.3685   0.08589   0.08172  -0.0310   1.0000   0.0309
  -8.250  -0.3609   0.08121   0.07706  -0.0359   0.9947   0.0306
  -8.000  -0.3389   0.07461   0.07042  -0.0452   0.9849   0.0303
  -7.750  -0.3153   0.06748   0.06322  -0.0551   0.9747   0.0302
  -7.500  -0.2896   0.05964   0.05524  -0.0653   0.9645   0.0308
  -7.250  -0.2633   0.04952   0.04482  -0.0763   0.9545   0.0322
  -7.000  -0.2371   0.03404   0.02816  -0.0878   0.9482   0.0332
  -6.750  -0.2058   0.02828   0.02151  -0.0914   0.9393   0.0347
  -6.500  -0.1706   0.02680   0.01986  -0.0935   0.9288   0.0382
  -6.250  -0.1333   0.02395   0.01636  -0.0958   0.9202   0.0423
  -6.000  -0.1018   0.02241   0.01452  -0.0966   0.9086   0.0458
  -5.750  -0.0688   0.02156   0.01345  -0.0974   0.8949   0.0516
  -5.500  -0.0376   0.02057   0.01225  -0.0977   0.8788   0.0564
  -5.250  -0.0079   0.01981   0.01118  -0.0977   0.8619   0.0648
  -5.000   0.0199   0.01909   0.01031  -0.0973   0.8459   0.0731
  -4.750   0.0468   0.01845   0.00956  -0.0969   0.8299   0.0844
  -4.500   0.0738   0.01807   0.00908  -0.0965   0.8127   0.0976
  -4.250   0.1014   0.01776   0.00862  -0.0961   0.7945   0.1082
  -4.000   0.1295   0.01751   0.00814  -0.0957   0.7753   0.1183
  -3.750   0.1577   0.01737   0.00776  -0.0954   0.7558   0.1284
  -3.500   0.1853   0.01734   0.00757  -0.0951   0.7363   0.1413
  -3.250   0.2124   0.01710   0.00718  -0.0947   0.7167   0.1499
  -3.000   0.2392   0.01681   0.00667  -0.0941   0.6932   0.1557
  -2.750   0.2654   0.01652   0.00624  -0.0935   0.6667   0.1611
  -2.500   0.2917   0.01626   0.00590  -0.0931   0.6428   0.1680
  -2.250   0.3180   0.01604   0.00557  -0.0926   0.6176   0.1766
  -2.000   0.3442   0.01589   0.00531  -0.0921   0.5888   0.1878
  -1.750   0.3698   0.01580   0.00508  -0.0915   0.5567   0.2021
  -1.500   0.3949   0.01580   0.00491  -0.0909   0.5240   0.2201
  -1.250   0.4202   0.01581   0.00481  -0.0904   0.4932   0.2434
  -1.000   0.4459   0.01581   0.00474  -0.0900   0.4646   0.2795
  -0.750   0.4714   0.01563   0.00472  -0.0897   0.4385   0.3610
  -0.500   0.4997   0.01433   0.00471  -0.0893   0.4069   1.0000
  -0.250   0.5202   0.01513   0.00482  -0.0882   0.3043   1.0000
   0.000   0.5436   0.01568   0.00495  -0.0875   0.2669   1.0000
   0.250   0.5687   0.01601   0.00506  -0.0871   0.2531   1.0000
   0.500   0.5942   0.01628   0.00518  -0.0867   0.2453   1.0000
   0.750   0.6200   0.01652   0.00530  -0.0864   0.2403   1.0000
   1.000   0.6456   0.01676   0.00544  -0.0861   0.2359   1.0000
   1.250   0.6712   0.01700   0.00561  -0.0857   0.2324   1.0000
   1.500   0.6970   0.01722   0.00577  -0.0854   0.2293   1.0000
   1.750   0.7226   0.01745   0.00596  -0.0851   0.2264   1.0000
   2.000   0.7480   0.01770   0.00618  -0.0847   0.2237   1.0000
   2.250   0.7733   0.01795   0.00641  -0.0844   0.2214   1.0000
   2.500   0.7984   0.01822   0.00666  -0.0840   0.2193   1.0000
   2.750   0.8237   0.01846   0.00693  -0.0836   0.2176   1.0000
   3.000   0.8489   0.01871   0.00721  -0.0833   0.2158   1.0000
   3.250   0.8739   0.01898   0.00750  -0.0829   0.2139   1.0000
   3.500   0.8985   0.01928   0.00784  -0.0825   0.2101   1.0000
   3.750   0.9229   0.01958   0.00818  -0.0820   0.2076   1.0000
   4.000   0.9470   0.01991   0.00855  -0.0815   0.2054   1.0000
   4.250   0.9710   0.02024   0.00896  -0.0810   0.2033   1.0000
   4.500   0.9953   0.02054   0.00935  -0.0805   0.2005   1.0000
   4.750   1.0192   0.02086   0.00976  -0.0800   0.1968   1.0000
   5.000   1.0427   0.02121   0.01021  -0.0795   0.1932   1.0000
   5.250   1.0658   0.02160   0.01070  -0.0788   0.1898   1.0000
   5.500   1.0890   0.02196   0.01118  -0.0783   0.1840   1.0000
   5.750   1.1119   0.02235   0.01170  -0.0776   0.1763   1.0000
   6.000   1.1339   0.02279   0.01224  -0.0769   0.1667   1.0000
   6.250   1.1548   0.02331   0.01282  -0.0760   0.1605   1.0000
   6.500   1.1754   0.02384   0.01341  -0.0751   0.1572   1.0000
   6.750   1.1957   0.02437   0.01403  -0.0742   0.1552   1.0000
   7.000   1.2157   0.02492   0.01469  -0.0732   0.1540   1.0000
   7.250   1.2351   0.02549   0.01537  -0.0721   0.1531   1.0000
   7.500   1.2536   0.02612   0.01613  -0.0710   0.1518   1.0000
   7.750   1.2683   0.02695   0.01692  -0.0694   0.1468   1.0000
   8.000   1.2775   0.02809   0.01795  -0.0672   0.1402   1.0000
   8.250   1.2822   0.02954   0.01932  -0.0644   0.1339   1.0000
   8.500   1.2898   0.03091   0.02071  -0.0621   0.1288   1.0000
   8.750   1.2979   0.03234   0.02218  -0.0600   0.1245   1.0000
   9.000   1.3071   0.03386   0.02371  -0.0581   0.1203   1.0000
   9.250   1.3165   0.03537   0.02535  -0.0564   0.1146   1.0000
   9.500   1.3253   0.03700   0.02708  -0.0547   0.1085   1.0000
   9.750   1.3341   0.03862   0.02877  -0.0532   0.1023   1.0000
  10.000   1.3384   0.03992   0.03050  -0.0514   0.0965   1.0000
  10.250   1.3589   0.04000   0.03138  -0.0510   0.0579   1.0000
  10.500   1.3581   0.04220   0.03327  -0.0498   0.0397   1.0000
  10.750   1.3561   0.04482   0.03593  -0.0482   0.0310   1.0000
  11.000   1.3550   0.04746   0.03864  -0.0469   0.0270   1.0000
  11.250   1.3521   0.05038   0.04165  -0.0459   0.0250   1.0000
  11.500   1.3490   0.05343   0.04484  -0.0451   0.0238   1.0000
  11.750   1.3450   0.05671   0.04831  -0.0446   0.0228   1.0000
  12.000   1.3392   0.06032   0.05211  -0.0444   0.0221   1.0000
  12.250   1.3316   0.06430   0.05631  -0.0446   0.0213   1.0000
  12.500   1.3223   0.06868   0.06088  -0.0451   0.0207   1.0000
  12.750   1.3113   0.07349   0.06587  -0.0460   0.0203   1.0000
  13.000   1.2990   0.07879   0.07135  -0.0474   0.0198   1.0000
  13.250   1.2854   0.08458   0.07732  -0.0492   0.0195   1.0000
  13.500   1.2712   0.09072   0.08362  -0.0514   0.0192   1.0000
  13.750   1.2566   0.09716   0.09023  -0.0538   0.0190   1.0000
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