Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

USA 45 AIRFOIL (usa45-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: USA 45 AIRFOIL (usa45-il)
Reynolds number: 1,000,000
Max Cl/Cd: 115.91 at α=8.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-usa45-il-1000000.txt
Download as CSV file: xf-usa45-il-1000000.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 =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -15.250  -0.2583   0.14732   0.14575  -0.0210   1.0000   0.0152
 -15.000  -0.2553   0.14579   0.14423  -0.0220   1.0000   0.0155
 -14.750  -0.9293   0.04003   0.03728  -0.0799   1.0000   0.0151
 -14.500  -0.9075   0.03995   0.03727  -0.0797   1.0000   0.0154
 -14.250  -0.9055   0.03780   0.03506  -0.0804   1.0000   0.0155
 -14.000  -0.9218   0.03443   0.03153  -0.0801   1.0000   0.0156
 -13.750  -0.9145   0.03347   0.03053  -0.0789   1.0000   0.0158
 -13.500  -0.9121   0.03232   0.02932  -0.0770   1.0000   0.0159
 -13.250  -0.9121   0.03125   0.02818  -0.0743   1.0000   0.0161
 -13.000  -0.9209   0.03002   0.02684  -0.0699   1.0000   0.0163
 -12.750  -0.9283   0.02909   0.02582  -0.0649   1.0000   0.0164
 -12.500  -0.9257   0.02827   0.02492  -0.0613   1.0000   0.0167
 -12.250  -0.9262   0.02732   0.02386  -0.0572   1.0000   0.0169
 -12.000  -0.9239   0.02659   0.02304  -0.0534   1.0000   0.0171
 -11.750  -0.8924   0.02553   0.02183  -0.0552   0.9979   0.0175
 -11.500  -0.8645   0.02378   0.01986  -0.0568   0.9946   0.0179
 -11.250  -0.8379   0.02254   0.01856  -0.0577   0.9909   0.0184
 -11.000  -0.8070   0.02203   0.01803  -0.0588   0.9875   0.0187
 -10.750  -0.7725   0.02188   0.01789  -0.0603   0.9847   0.0191
 -10.500  -0.7402   0.02125   0.01719  -0.0617   0.9820   0.0195
 -10.250  -0.7119   0.02081   0.01669  -0.0621   0.9756   0.0201
 -10.000  -0.6796   0.02003   0.01581  -0.0634   0.9715   0.0206
  -9.750  -0.6467   0.01943   0.01509  -0.0647   0.9661   0.0211
  -9.500  -0.6121   0.01905   0.01460  -0.0662   0.9582   0.0214
  -9.250  -0.5845   0.01718   0.01259  -0.0672   0.9469   0.0222
  -9.000  -0.5528   0.01673   0.01210  -0.0682   0.9335   0.0227
  -8.750  -0.5243   0.01644   0.01173  -0.0683   0.9150   0.0232
  -8.500  -0.4992   0.01609   0.01127  -0.0678   0.8930   0.0238
  -8.250  -0.4761   0.01574   0.01079  -0.0667   0.8689   0.0243
  -8.000  -0.4538   0.01539   0.01028  -0.0655   0.8445   0.0249
  -7.750  -0.4314   0.01506   0.00979  -0.0643   0.8204   0.0253
  -7.500  -0.4085   0.01495   0.00951  -0.0631   0.7946   0.0256
  -7.250  -0.3890   0.01389   0.00828  -0.0616   0.7691   0.0264
  -7.000  -0.3674   0.01345   0.00773  -0.0603   0.7423   0.0270
  -6.750  -0.3446   0.01318   0.00735  -0.0592   0.7154   0.0275
  -6.500  -0.3214   0.01292   0.00697  -0.0582   0.6900   0.0280
  -6.250  -0.2982   0.01268   0.00661  -0.0571   0.6638   0.0286
  -6.000  -0.2745   0.01246   0.00626  -0.0562   0.6372   0.0292
  -5.750  -0.2507   0.01231   0.00597  -0.0553   0.6093   0.0299
  -5.500  -0.2269   0.01212   0.00565  -0.0543   0.5816   0.0303
  -5.250  -0.2023   0.01199   0.00539  -0.0535   0.5550   0.0306
  -5.000  -0.1797   0.01163   0.00489  -0.0524   0.5308   0.0312
  -4.750  -0.1574   0.01121   0.00437  -0.0513   0.5089   0.0320
  -4.500  -0.1333   0.01101   0.00408  -0.0504   0.4889   0.0328
  -4.250  -0.1085   0.01088   0.00387  -0.0497   0.4715   0.0336
  -4.000  -0.0835   0.01073   0.00364  -0.0490   0.4575   0.0343
  -3.750  -0.0582   0.01060   0.00344  -0.0483   0.4461   0.0351
  -3.500  -0.0327   0.01050   0.00326  -0.0477   0.4359   0.0358
  -3.250  -0.0065   0.01039   0.00310  -0.0472   0.4279   0.0365
  -3.000   0.0186   0.01023   0.00287  -0.0465   0.4198   0.0376
  -2.750   0.0444   0.01007   0.00269  -0.0460   0.4135   0.0396
  -2.500   0.0704   0.00998   0.00257  -0.0455   0.4067   0.0414
  -2.250   0.0967   0.00991   0.00246  -0.0450   0.4004   0.0433
  -2.000   0.1229   0.00979   0.00234  -0.0445   0.3949   0.0481
  -1.750   0.1482   0.00966   0.00226  -0.0439   0.3894   0.0661
  -1.500   0.1734   0.00948   0.00218  -0.0433   0.3846   0.1004
  -1.250   0.1978   0.00921   0.00212  -0.0426   0.3803   0.1617
  -1.000   0.2224   0.00902   0.00208  -0.0419   0.3757   0.2177
  -0.750   0.2460   0.00882   0.00206  -0.0411   0.3705   0.2858
  -0.500   0.2692   0.00848   0.00203  -0.0402   0.3675   0.3876
  -0.250   0.2892   0.00800   0.00200  -0.0387   0.3634   0.5328
   0.000   0.3081   0.00762   0.00200  -0.0368   0.3595   0.6641
   0.250   0.3275   0.00741   0.00205  -0.0349   0.3552   0.7570
   0.500   0.3492   0.00725   0.00212  -0.0333   0.3525   0.8285
   0.750   0.3742   0.00719   0.00219  -0.0324   0.3493   0.8771
   1.000   0.4030   0.00722   0.00227  -0.0323   0.3457   0.9135
   1.250   0.4349   0.00733   0.00237  -0.0330   0.3417   0.9384
   1.500   0.4712   0.00747   0.00249  -0.0347   0.3377   0.9526
   1.750   0.5120   0.00760   0.00259  -0.0373   0.3346   0.9618
   2.000   0.5478   0.00775   0.00271  -0.0389   0.3312   0.9702
   2.250   0.5884   0.00792   0.00282  -0.0415   0.3276   0.9729
   2.500   0.6262   0.00814   0.00296  -0.0436   0.3233   0.9765
   2.750   0.6597   0.00824   0.00306  -0.0448   0.3212   0.9811
   3.000   0.6987   0.00835   0.00315  -0.0471   0.3182   0.9836
   3.250   0.7392   0.00848   0.00324  -0.0499   0.3150   0.9856
   3.500   0.7755   0.00862   0.00333  -0.0518   0.3117   0.9878
   3.750   0.8090   0.00878   0.00345  -0.0531   0.3078   0.9901
   4.000   0.8423   0.00886   0.00353  -0.0543   0.3059   0.9924
   4.250   0.8764   0.00894   0.00361  -0.0557   0.3034   0.9942
   4.500   0.9119   0.00902   0.00367  -0.0575   0.3004   0.9956
   4.750   0.9467   0.00914   0.00375  -0.0592   0.2971   0.9973
   5.000   0.9806   0.00931   0.00389  -0.0607   0.2929   0.9990
   5.250   1.0139   0.00935   0.00394  -0.0620   0.2904   1.0000
   5.500   1.0351   0.00941   0.00402  -0.0608   0.2875   1.0000
   5.750   1.0557   0.00951   0.00411  -0.0594   0.2842   1.0000
   6.000   1.0755   0.00966   0.00423  -0.0580   0.2805   1.0000
   6.250   1.0959   0.00979   0.00436  -0.0566   0.2770   1.0000
   6.500   1.1177   0.00986   0.00444  -0.0555   0.2736   1.0000
   6.750   1.1386   0.00998   0.00456  -0.0542   0.2703   1.0000
   7.000   1.1588   0.01014   0.00471  -0.0528   0.2666   1.0000
   7.250   1.1790   0.01031   0.00488  -0.0514   0.2629   1.0000
   7.500   1.2010   0.01040   0.00500  -0.0504   0.2596   1.0000
   7.750   1.2220   0.01055   0.00514  -0.0492   0.2549   1.0000
   8.000   1.2416   0.01077   0.00533  -0.0478   0.2496   1.0000
   8.250   1.2634   0.01090   0.00548  -0.0467   0.2445   1.0000
   8.500   1.2836   0.01109   0.00566  -0.0454   0.2388   1.0000
   8.750   1.3036   0.01131   0.00587  -0.0441   0.2319   1.0000
   9.000   1.3226   0.01158   0.00610  -0.0426   0.2233   1.0000
   9.250   1.3398   0.01193   0.00639  -0.0409   0.2095   1.0000
   9.500   1.3522   0.01252   0.00683  -0.0384   0.1859   1.0000
   9.750   1.3576   0.01344   0.00754  -0.0349   0.1558   1.0000
  10.000   1.3536   0.01458   0.00845  -0.0297   0.1231   1.0000
  10.500   1.3198   0.01801   0.01141  -0.0165   0.0427   1.0000
  10.750   1.3122   0.01965   0.01301  -0.0122   0.0204   1.0000
  11.000   1.3205   0.02058   0.01398  -0.0102   0.0179   1.0000
  11.250   1.3283   0.02162   0.01506  -0.0084   0.0167   1.0000
  11.500   1.3359   0.02275   0.01626  -0.0068   0.0156   1.0000
  11.750   1.3442   0.02393   0.01750  -0.0055   0.0150   1.0000
  12.000   1.3511   0.02531   0.01894  -0.0044   0.0145   1.0000
  12.250   1.3554   0.02699   0.02070  -0.0034   0.0139   1.0000
  12.500   1.3588   0.02890   0.02268  -0.0026   0.0135   1.0000
  12.750   1.3552   0.03163   0.02552  -0.0020   0.0129   1.0000
  13.000   1.3539   0.03435   0.02834  -0.0019   0.0127   1.0000
  13.250   1.3555   0.03689   0.03097  -0.0020   0.0125   1.0000
  13.500   1.3529   0.04003   0.03420  -0.0024   0.0122   1.0000
  13.750   1.3477   0.04357   0.03785  -0.0029   0.0122   1.0000
  14.000   1.3393   0.04761   0.04199  -0.0037   0.0119   1.0000
  14.250   1.3323   0.05153   0.04601  -0.0045   0.0116   1.0000
  14.500   1.3186   0.05636   0.05096  -0.0055   0.0116   1.0000
  14.750   1.3069   0.06099   0.05568  -0.0066   0.0114   1.0000
  15.000   1.2933   0.06589   0.06068  -0.0077   0.0112   1.0000
  15.250   1.2782   0.07104   0.06595  -0.0089   0.0113   1.0000
  15.500   1.2646   0.07608   0.07108  -0.0102   0.0112   1.0000
  15.750   1.2508   0.08120   0.07629  -0.0115   0.0111   1.0000
  16.000   1.2385   0.08620   0.08138  -0.0129   0.0110   1.0000
<< Back to USA 45 AIRFOIL (usa45-il)

Polar data table (+)

Polar graphs


<< Back to USA 45 AIRFOIL (usa45-il)