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USA 45 AIRFOIL (usa45-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: USA 45 AIRFOIL (usa45-il)
Reynolds number: 500,000
Max Cl/Cd: 89.87 at α=8°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-usa45-il-500000-n5.txt
Download as CSV file: xf-usa45-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: USA 45 AIRFOIL                                  
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -13.750  -0.8143   0.04338   0.04037  -0.0775   1.0000   0.0149
 -13.500  -0.8415   0.03834   0.03512  -0.0791   1.0000   0.0150
 -13.250  -0.8549   0.03570   0.03232  -0.0777   1.0000   0.0152
 -13.000  -0.8681   0.03362   0.03008  -0.0746   1.0000   0.0154
 -12.750  -0.8791   0.03215   0.02848  -0.0703   1.0000   0.0156
 -12.500  -0.8903   0.03072   0.02689  -0.0653   1.0000   0.0159
 -12.250  -0.8940   0.02929   0.02530  -0.0613   1.0000   0.0162
 -12.000  -0.8953   0.02783   0.02363  -0.0576   0.9998   0.0165
 -11.750  -0.8644   0.02680   0.02251  -0.0594   0.9954   0.0170
 -11.500  -0.8327   0.02641   0.02211  -0.0607   0.9901   0.0174
 -11.250  -0.8001   0.02582   0.02148  -0.0623   0.9845   0.0178
 -11.000  -0.7712   0.02517   0.02074  -0.0632   0.9762   0.0183
 -10.750  -0.7417   0.02421   0.01964  -0.0644   0.9689   0.0189
 -10.500  -0.7115   0.02309   0.01834  -0.0657   0.9615   0.0196
 -10.250  -0.6828   0.02193   0.01695  -0.0667   0.9526   0.0202
 -10.000  -0.6497   0.02110   0.01599  -0.0683   0.9429   0.0208
  -9.750  -0.6172   0.02048   0.01531  -0.0697   0.9298   0.0213
  -9.500  -0.5853   0.02006   0.01482  -0.0708   0.9126   0.0218
  -9.250  -0.5582   0.01952   0.01415  -0.0709   0.8916   0.0224
  -9.000  -0.5339   0.01896   0.01342  -0.0703   0.8673   0.0229
  -8.750  -0.5112   0.01850   0.01276  -0.0693   0.8424   0.0236
  -8.500  -0.4893   0.01809   0.01214  -0.0681   0.8170   0.0243
  -8.250  -0.4674   0.01771   0.01155  -0.0669   0.7921   0.0247
  -8.000  -0.4461   0.01726   0.01090  -0.0656   0.7667   0.0251
  -7.750  -0.4260   0.01658   0.01007  -0.0643   0.7401   0.0257
  -7.500  -0.4041   0.01627   0.00963  -0.0631   0.7141   0.0263
  -7.250  -0.3817   0.01596   0.00919  -0.0620   0.6893   0.0269
  -7.000  -0.3591   0.01565   0.00873  -0.0609   0.6652   0.0274
  -6.750  -0.3365   0.01533   0.00826  -0.0598   0.6398   0.0279
  -6.500  -0.3134   0.01508   0.00786  -0.0588   0.6142   0.0286
  -6.250  -0.2903   0.01482   0.00743  -0.0578   0.5885   0.0292
  -6.000  -0.2669   0.01455   0.00701  -0.0569   0.5647   0.0297
  -5.750  -0.2433   0.01431   0.00662  -0.0560   0.5424   0.0301
  -5.500  -0.2195   0.01409   0.00627  -0.0551   0.5215   0.0304
  -5.250  -0.1969   0.01368   0.00574  -0.0540   0.5022   0.0311
  -5.000  -0.1736   0.01339   0.00537  -0.0531   0.4845   0.0318
  -4.750  -0.1495   0.01319   0.00508  -0.0523   0.4695   0.0326
  -4.500  -0.1250   0.01300   0.00481  -0.0516   0.4574   0.0332
  -4.250  -0.1001   0.01281   0.00455  -0.0509   0.4471   0.0338
  -4.000  -0.0751   0.01264   0.00430  -0.0502   0.4384   0.0345
  -3.750  -0.0499   0.01249   0.00408  -0.0496   0.4296   0.0352
  -3.500  -0.0246   0.01235   0.00388  -0.0489   0.4217   0.0359
  -3.250   0.0010   0.01224   0.00370  -0.0484   0.4145   0.0366
  -3.000   0.0262   0.01211   0.00351  -0.0477   0.4083   0.0379
  -2.750   0.0519   0.01196   0.00334  -0.0472   0.4027   0.0397
  -2.500   0.0777   0.01186   0.00321  -0.0467   0.3972   0.0417
  -2.250   0.1034   0.01179   0.00309  -0.0461   0.3922   0.0439
  -2.000   0.1294   0.01168   0.00299  -0.0456   0.3873   0.0493
  -1.750   0.1550   0.01157   0.00291  -0.0451   0.3820   0.0624
  -1.250   0.2059   0.01136   0.00277  -0.0440   0.3730   0.1015
  -1.000   0.2307   0.01116   0.00272  -0.0434   0.3689   0.1459
  -0.750   0.2552   0.01099   0.00269  -0.0428   0.3648   0.2000
  -0.250   0.3031   0.01057   0.00264  -0.0413   0.3577   0.3310
   0.000   0.3258   0.01027   0.00263  -0.0404   0.3539   0.4258
   0.250   0.3448   0.00982   0.00262  -0.0387   0.3502   0.5679
   0.500   0.3610   0.00940   0.00268  -0.0362   0.3468   0.7141
   0.750   0.3808   0.00916   0.00280  -0.0341   0.3438   0.8243
   1.000   0.4103   0.00914   0.00292  -0.0341   0.3407   0.8845
   1.250   0.4482   0.00924   0.00305  -0.0360   0.3371   0.9183
   1.500   0.4898   0.00942   0.00318  -0.0388   0.3334   0.9419
   1.750   0.5301   0.00961   0.00330  -0.0413   0.3298   0.9532
   2.000   0.5660   0.00974   0.00340  -0.0430   0.3267   0.9612
   2.250   0.6033   0.00989   0.00351  -0.0449   0.3232   0.9680
   2.500   0.6394   0.01004   0.00362  -0.0467   0.3201   0.9742
   2.750   0.6759   0.01020   0.00373  -0.0485   0.3170   0.9785
   3.000   0.7064   0.01036   0.00383  -0.0492   0.3140   0.9828
   3.250   0.7402   0.01047   0.00393  -0.0506   0.3114   0.9852
   3.500   0.7742   0.01058   0.00402  -0.0520   0.3083   0.9877
   3.750   0.8072   0.01070   0.00412  -0.0532   0.3055   0.9906
   4.000   0.8391   0.01085   0.00425  -0.0542   0.3028   0.9936
   4.250   0.8724   0.01100   0.00436  -0.0556   0.3000   0.9959
   4.500   0.9057   0.01115   0.00449  -0.0569   0.2973   0.9983
   4.750   0.9384   0.01126   0.00462  -0.0581   0.2947   1.0000
   5.000   0.9591   0.01138   0.00474  -0.0568   0.2924   1.0000
   5.250   0.9797   0.01152   0.00488  -0.0555   0.2899   1.0000
   5.500   1.0000   0.01166   0.00502  -0.0541   0.2873   1.0000
   5.750   1.0200   0.01184   0.00517  -0.0527   0.2847   1.0000
   6.000   1.0406   0.01200   0.00534  -0.0514   0.2821   1.0000
   6.250   1.0620   0.01212   0.00549  -0.0502   0.2789   1.0000
   6.500   1.0830   0.01227   0.00565  -0.0490   0.2748   1.0000
   6.750   1.1031   0.01246   0.00582  -0.0477   0.2708   1.0000
   7.000   1.1234   0.01265   0.00601  -0.0464   0.2669   1.0000
   7.250   1.1447   0.01280   0.00618  -0.0452   0.2619   1.0000
   7.500   1.1648   0.01300   0.00638  -0.0439   0.2572   1.0000
   7.750   1.1843   0.01323   0.00660  -0.0425   0.2531   1.0000
   8.000   1.2052   0.01341   0.00681  -0.0413   0.2474   1.0000
   8.250   1.2238   0.01367   0.00704  -0.0398   0.2407   1.0000
   8.500   1.2435   0.01390   0.00729  -0.0385   0.2345   1.0000
   8.750   1.2614   0.01419   0.00757  -0.0369   0.2271   1.0000
   9.000   1.2791   0.01449   0.00787  -0.0353   0.2187   1.0000
   9.250   1.2946   0.01487   0.00821  -0.0334   0.2090   1.0000
   9.500   1.3058   0.01533   0.00861  -0.0307   0.1958   1.0000
   9.750   1.3123   0.01598   0.00916  -0.0273   0.1765   1.0000
  10.000   1.3157   0.01684   0.00990  -0.0237   0.1561   1.0000
  10.250   1.3165   0.01791   0.01084  -0.0200   0.1341   1.0000
  10.500   1.3165   0.01910   0.01193  -0.0165   0.1146   1.0000
  10.750   1.3129   0.02058   0.01330  -0.0129   0.0947   1.0000
  11.000   1.2892   0.02340   0.01592  -0.0081   0.0516   1.0000
  11.250   1.2707   0.02641   0.01889  -0.0049   0.0230   1.0000
  11.500   1.2719   0.02829   0.02083  -0.0036   0.0186   1.0000
  11.750   1.2753   0.03016   0.02278  -0.0028   0.0169   1.0000
  12.000   1.2776   0.03227   0.02498  -0.0022   0.0157   1.0000
  12.250   1.2790   0.03462   0.02742  -0.0019   0.0149   1.0000
  12.500   1.2803   0.03712   0.03003  -0.0019   0.0143   1.0000
  12.750   1.2797   0.03994   0.03295  -0.0021   0.0137   1.0000
  13.000   1.2756   0.04329   0.03641  -0.0025   0.0132   1.0000
  13.250   1.2703   0.04689   0.04011  -0.0031   0.0129   1.0000
  13.500   1.2622   0.05090   0.04424  -0.0038   0.0126   1.0000
  13.750   1.2536   0.05503   0.04849  -0.0047   0.0124   1.0000
  14.000   1.2414   0.05971   0.05328  -0.0057   0.0121   1.0000
  14.250   1.2274   0.06463   0.05832  -0.0068   0.0118   1.0000
  14.500   1.2193   0.06884   0.06264  -0.0077   0.0115   1.0000
  14.750   1.2073   0.07363   0.06753  -0.0089   0.0116   1.0000
  15.000   1.1966   0.07829   0.07230  -0.0100   0.0115   1.0000
  15.250   1.1884   0.08268   0.07678  -0.0111   0.0112   1.0000
  15.500   1.1794   0.08726   0.08145  -0.0124   0.0109   1.0000
  15.750   1.1714   0.09170   0.08599  -0.0135   0.0108   1.0000
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