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I.S.A. 962 (isa962-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: I.S.A. 962 (isa962-il)
Reynolds number: 50,000
Max Cl/Cd: 39.35 at α=4.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-isa962-il-50000-n5.txt
Download as CSV file: xf-isa962-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: I.S.A. 962                                      
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.3205   0.10577   0.09879  -0.0286   1.0000   0.1271
  -8.750  -0.3389   0.10542   0.09862  -0.0291   1.0000   0.1278
  -8.500  -0.3510   0.10432   0.09768  -0.0307   1.0000   0.1283
  -8.250  -0.3372   0.09930   0.09269  -0.0264   1.0000   0.1296
  -8.000  -0.3335   0.09643   0.08988  -0.0239   1.0000   0.1312
  -7.750  -0.3353   0.09427   0.08780  -0.0221   1.0000   0.1329
  -7.500  -0.3393   0.09235   0.08596  -0.0207   1.0000   0.1348
  -7.250  -0.3441   0.09048   0.08416  -0.0197   1.0000   0.1369
  -7.000  -0.3490   0.08863   0.08238  -0.0197   1.0000   0.1397
  -6.750  -0.3556   0.08771   0.08140  -0.0271   1.0000   0.1441
  -6.500  -0.3409   0.08343   0.07718  -0.0273   0.9964   0.1452
  -6.250  -0.3191   0.07958   0.07334  -0.0275   0.9908   0.1484
  -5.500  -0.2048   0.06106   0.05393  -0.0562   0.9666   0.0869
  -5.250  -0.1716   0.05744   0.05017  -0.0602   0.9603   0.0829
  -5.000  -0.1400   0.05369   0.04621  -0.0643   0.9522   0.0800
  -4.750  -0.0978   0.04874   0.04079  -0.0709   0.9464   0.0764
  -4.500  -0.0645   0.04551   0.03719  -0.0742   0.9384   0.0761
  -4.250  -0.0271   0.04300   0.03443  -0.0777   0.9325   0.0774
  -4.000   0.0063   0.04057   0.03165  -0.0802   0.9249   0.0778
  -3.750   0.0450   0.03797   0.02858  -0.0832   0.9188   0.0773
  -3.500   0.0833   0.03583   0.02601  -0.0858   0.9129   0.0772
  -3.250   0.1169   0.03420   0.02403  -0.0873   0.9052   0.0776
  -3.000   0.1586   0.03262   0.02211  -0.0900   0.9005   0.0787
  -2.750   0.1883   0.03168   0.02092  -0.0906   0.8915   0.0814
  -2.500   0.2276   0.03059   0.01944  -0.0925   0.8857   0.0849
  -2.250   0.2578   0.02980   0.01851  -0.0928   0.8764   0.0873
  -2.000   0.2959   0.02888   0.01749  -0.0943   0.8692   0.0904
  -1.750   0.3266   0.02828   0.01672  -0.0943   0.8577   0.0941
  -1.500   0.3620   0.02757   0.01587  -0.0949   0.8468   0.1010
  -1.250   0.4003   0.02677   0.01494  -0.0958   0.8363   0.1127
  -1.000   0.4293   0.02613   0.01433  -0.0954   0.8224   0.1260
  -0.750   0.4578   0.02549   0.01388  -0.0951   0.8097   0.1574
  -0.500   0.4884   0.02448   0.01358  -0.0955   0.7998   0.2911
  -0.250   0.5205   0.02264   0.01322  -0.0954   0.7899   1.0000
   0.000   0.5467   0.02280   0.01310  -0.0946   0.7777   1.0000
   0.250   0.5756   0.02285   0.01293  -0.0942   0.7667   1.0000
   0.500   0.6055   0.02285   0.01274  -0.0939   0.7559   1.0000
   0.750   0.6309   0.02301   0.01277  -0.0931   0.7427   1.0000
   1.000   0.6578   0.02312   0.01275  -0.0924   0.7299   1.0000
   1.250   0.6863   0.02314   0.01265  -0.0919   0.7178   1.0000
   1.500   0.7153   0.02313   0.01254  -0.0913   0.7054   1.0000
   1.750   0.7409   0.02326   0.01259  -0.0904   0.6902   1.0000
   2.000   0.7669   0.02333   0.01258  -0.0895   0.6740   1.0000
   2.250   0.7932   0.02336   0.01253  -0.0884   0.6565   1.0000
   2.500   0.8196   0.02335   0.01241  -0.0873   0.6377   1.0000
   2.750   0.8423   0.02352   0.01252  -0.0859   0.6154   1.0000
   3.000   0.8661   0.02362   0.01254  -0.0846   0.5925   1.0000
   3.250   0.8905   0.02372   0.01251  -0.0833   0.5696   1.0000
   3.500   0.9122   0.02400   0.01274  -0.0819   0.5446   1.0000
   3.750   0.9356   0.02425   0.01288  -0.0807   0.5220   1.0000
   4.000   0.9577   0.02463   0.01320  -0.0795   0.4994   1.0000
   4.250   0.9797   0.02503   0.01353  -0.0783   0.4771   1.0000
   4.500   1.0019   0.02546   0.01386  -0.0771   0.4561   1.0000
   4.750   1.0228   0.02599   0.01431  -0.0758   0.4345   1.0000
   5.000   1.0432   0.02656   0.01480  -0.0745   0.4132   1.0000
   5.250   1.0634   0.02719   0.01532  -0.0732   0.3929   1.0000
   5.500   1.0832   0.02789   0.01589  -0.0720   0.3737   1.0000
   5.750   1.1022   0.02870   0.01663  -0.0707   0.3543   1.0000
   6.000   1.1208   0.02957   0.01743  -0.0694   0.3354   1.0000
   6.250   1.1392   0.03050   0.01832  -0.0681   0.3174   1.0000
   6.500   1.1577   0.03146   0.01925  -0.0669   0.3009   1.0000
   6.750   1.1759   0.03244   0.02020  -0.0657   0.2858   1.0000
   7.000   1.1937   0.03342   0.02114  -0.0645   0.2722   1.0000
   7.250   1.2108   0.03444   0.02228  -0.0632   0.2593   1.0000
   7.500   1.2280   0.03549   0.02340  -0.0620   0.2481   1.0000
   7.750   1.2451   0.03651   0.02442  -0.0608   0.2386   1.0000
   8.000   1.2616   0.03757   0.02555  -0.0595   0.2296   1.0000
   8.250   1.2784   0.03872   0.02681  -0.0584   0.2217   1.0000
   8.500   1.2947   0.03981   0.02792  -0.0571   0.2145   1.0000
   8.750   1.3102   0.04108   0.02930  -0.0559   0.2076   1.0000
   9.000   1.3258   0.04230   0.03059  -0.0547   0.2014   1.0000
   9.250   1.3432   0.04357   0.03191  -0.0537   0.1962   1.0000
   9.500   1.3551   0.04512   0.03368  -0.0522   0.1907   1.0000
   9.750   1.3709   0.04642   0.03501  -0.0511   0.1858   1.0000
  10.000   1.3859   0.04795   0.03662  -0.0500   0.1813   1.0000
  10.250   1.3925   0.04991   0.03889  -0.0482   0.1770   1.0000
  10.500   1.4031   0.05174   0.04088  -0.0469   0.1733   1.0000
  10.750   1.4211   0.05326   0.04244  -0.0462   0.1698   1.0000
  11.000   1.4315   0.05532   0.04465  -0.0450   0.1666   1.0000
  11.250   1.4238   0.05822   0.04791  -0.0426   0.1638   1.0000
  11.500   1.4170   0.06123   0.05121  -0.0407   0.1611   1.0000
  11.750   1.4125   0.06421   0.05443  -0.0392   0.1585   1.0000
  12.000   1.4135   0.06689   0.05728  -0.0381   0.1559   1.0000
  12.250   1.4225   0.06918   0.05966  -0.0373   0.1537   1.0000
  12.500   1.4215   0.07244   0.06308  -0.0365   0.1519   1.0000
  12.750   1.3806   0.07914   0.07014  -0.0361   0.1511   1.0000
  13.000   1.3173   0.08979   0.08113  -0.0386   0.1505   1.0000
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