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

USA 28 AIRFOIL (usa28-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: USA 28 AIRFOIL (usa28-il)
Reynolds number: 1,000,000
Max Cl/Cd: 88.89 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-usa28-il-1000000-n5.txt
Download as CSV file: xf-usa28-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: USA 28 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -16.750  -0.9259   0.08460   0.08182  -0.0587   1.0000   0.0092
 -16.500  -0.9575   0.07663   0.07375  -0.0627   1.0000   0.0093
 -16.250  -0.9879   0.06927   0.06628  -0.0663   1.0000   0.0091
 -16.000  -1.0278   0.06114   0.05803  -0.0702   1.0000   0.0089
 -15.750  -1.0680   0.05355   0.05031  -0.0736   1.0000   0.0088
 -15.500  -1.1212   0.04487   0.04150  -0.0775   1.0000   0.0086
 -15.250  -1.1671   0.03267   0.02898  -0.0900   0.9989   0.0083
 -15.000  -1.1643   0.02946   0.02559  -0.0922   0.9966   0.0085
 -14.750  -1.1556   0.02757   0.02358  -0.0924   0.9945   0.0088
 -14.500  -1.1449   0.02597   0.02189  -0.0918   0.9922   0.0093
 -14.250  -1.1301   0.02463   0.02044  -0.0914   0.9900   0.0097
 -14.000  -1.1112   0.02345   0.01918  -0.0915   0.9882   0.0103
 -13.750  -1.0887   0.02242   0.01806  -0.0919   0.9868   0.0107
 -13.500  -1.0635   0.02147   0.01702  -0.0927   0.9856   0.0112
 -13.250  -1.0469   0.02058   0.01607  -0.0916   0.9827   0.0119
 -13.000  -1.0272   0.01978   0.01522  -0.0909   0.9796   0.0127
 -12.750  -1.0024   0.01904   0.01441  -0.0911   0.9774   0.0135
 -12.500  -0.9755   0.01835   0.01365  -0.0917   0.9758   0.0143
 -12.250  -0.9587   0.01776   0.01304  -0.0900   0.9717   0.0154
 -12.000  -0.9373   0.01722   0.01247  -0.0892   0.9675   0.0165
 -11.500  -0.8982   0.01628   0.01143  -0.0866   0.9553   0.0182
 -11.250  -0.8809   0.01582   0.01094  -0.0847   0.9448   0.0191
 -11.000  -0.8550   0.01535   0.01044  -0.0846   0.9367   0.0201
 -10.750  -0.8238   0.01490   0.00995  -0.0856   0.9295   0.0212
 -10.500  -0.7869   0.01442   0.00942  -0.0878   0.9242   0.0222
 -10.250  -0.7456   0.01397   0.00889  -0.0910   0.9186   0.0230
 -10.000  -0.7007   0.01356   0.00841  -0.0949   0.9131   0.0234
  -9.750  -0.6558   0.01295   0.00772  -0.0992   0.9069   0.0249
  -9.500  -0.6095   0.01255   0.00727  -0.1036   0.8987   0.0261
  -9.250  -0.5626   0.01221   0.00685  -0.1081   0.8894   0.0271
  -9.000  -0.5239   0.01196   0.00649  -0.1107   0.8750   0.0281
  -8.750  -0.4943   0.01176   0.00617  -0.1113   0.8599   0.0287
  -8.500  -0.4687   0.01161   0.00592  -0.1109   0.8466   0.0291
  -8.250  -0.4446   0.01145   0.00570  -0.1102   0.8360   0.0295
  -8.000  -0.4229   0.01112   0.00528  -0.1090   0.8278   0.0305
  -7.750  -0.4003   0.01087   0.00496  -0.1080   0.8196   0.0313
  -7.500  -0.3773   0.01065   0.00468  -0.1070   0.8117   0.0323
  -7.250  -0.3541   0.01045   0.00443  -0.1061   0.8038   0.0331
  -7.000  -0.3306   0.01027   0.00420  -0.1052   0.7967   0.0340
  -6.750  -0.3070   0.01010   0.00397  -0.1042   0.7883   0.0346
  -6.500  -0.2834   0.00995   0.00376  -0.1033   0.7803   0.0356
  -6.250  -0.2598   0.00981   0.00356  -0.1024   0.7712   0.0361
  -6.000  -0.2360   0.00967   0.00336  -0.1015   0.7623   0.0371
  -5.750  -0.2132   0.00951   0.00315  -0.1004   0.7515   0.0390
  -5.500  -0.1902   0.00937   0.00297  -0.0993   0.7391   0.0412
  -5.250  -0.1674   0.00926   0.00281  -0.0982   0.7248   0.0440
  -5.000  -0.1447   0.00916   0.00265  -0.0970   0.7097   0.0471
  -4.750  -0.1225   0.00905   0.00249  -0.0957   0.6939   0.0525
  -4.500  -0.0998   0.00897   0.00235  -0.0946   0.6787   0.0578
  -4.250  -0.0768   0.00885   0.00220  -0.0935   0.6669   0.0660
  -4.000  -0.0534   0.00872   0.00205  -0.0925   0.6576   0.0770
  -3.750  -0.0310   0.00842   0.00190  -0.0915   0.6499   0.1196
  -3.500  -0.0065   0.00835   0.00184  -0.0907   0.6433   0.1333
  -3.250   0.0187   0.00829   0.00177  -0.0901   0.6367   0.1395
  -3.000   0.0438   0.00825   0.00171  -0.0894   0.6310   0.1463
  -2.750   0.0694   0.00823   0.00166  -0.0889   0.6264   0.1493
  -2.500   0.0950   0.00818   0.00160  -0.0883   0.6212   0.1538
  -2.250   0.1202   0.00813   0.00155  -0.0877   0.6164   0.1587
  -1.750   0.1711   0.00805   0.00147  -0.0865   0.6084   0.1705
  -1.500   0.1964   0.00798   0.00142  -0.0859   0.6037   0.1792
  -1.250   0.2207   0.00791   0.00138  -0.0851   0.5983   0.1948
  -1.000   0.2452   0.00781   0.00135  -0.0844   0.5932   0.2150
  -0.750   0.2698   0.00771   0.00132  -0.0836   0.5880   0.2416
  -0.500   0.2936   0.00764   0.00131  -0.0827   0.5818   0.2671
  -0.250   0.3183   0.00760   0.00132  -0.0820   0.5756   0.2871
   0.000   0.3430   0.00759   0.00133  -0.0812   0.5685   0.3007
   0.250   0.3673   0.00759   0.00135  -0.0804   0.5613   0.3124
   0.500   0.3916   0.00761   0.00136  -0.0796   0.5510   0.3202
   0.750   0.4148   0.00766   0.00138  -0.0785   0.5366   0.3273
   1.000   0.4356   0.00776   0.00140  -0.0769   0.5105   0.3327
   1.250   0.4528   0.00799   0.00147  -0.0746   0.4705   0.3379
   1.500   0.4729   0.00815   0.00155  -0.0729   0.4491   0.3442
   1.750   0.4946   0.00827   0.00163  -0.0715   0.4368   0.3498
   2.000   0.5163   0.00838   0.00171  -0.0702   0.4273   0.3549
   2.250   0.5393   0.00844   0.00177  -0.0691   0.4212   0.3594
   2.500   0.5621   0.00852   0.00184  -0.0680   0.4154   0.3633
   2.750   0.5844   0.00860   0.00192  -0.0667   0.4106   0.3675
   3.000   0.6077   0.00865   0.00200  -0.0657   0.4069   0.3713
   3.250   0.6310   0.00871   0.00207  -0.0647   0.4029   0.3747
   3.500   0.6538   0.00880   0.00216  -0.0636   0.3990   0.3777
   3.750   0.6759   0.00891   0.00226  -0.0624   0.3945   0.3807
   4.000   0.6989   0.00896   0.00236  -0.0613   0.3896   0.3850
   4.250   0.7208   0.00907   0.00246  -0.0601   0.3828   0.3889
   4.500   0.7423   0.00919   0.00258  -0.0587   0.3772   0.3933
   4.750   0.7655   0.00925   0.00268  -0.0577   0.3740   0.3971
   5.000   0.7881   0.00932   0.00280  -0.0566   0.3701   0.4015
   5.250   0.8086   0.00947   0.00293  -0.0551   0.3618   0.4061
   5.500   0.8317   0.00954   0.00304  -0.0541   0.3580   0.4093
   5.750   0.8525   0.00967   0.00318  -0.0526   0.3481   0.4148
   6.000   0.8729   0.00982   0.00332  -0.0511   0.3343   0.4204
   6.500   0.9069   0.01032   0.00369  -0.0469   0.2895   0.4330
   6.750   0.9188   0.01076   0.00399  -0.0439   0.2563   0.4392
   7.000   0.9249   0.01143   0.00444  -0.0398   0.2092   0.4466
   7.250   0.9329   0.01204   0.00488  -0.0361   0.1720   0.4559
   7.500   0.9422   0.01259   0.00532  -0.0328   0.1408   0.4709
   7.750   0.9513   0.01312   0.00579  -0.0295   0.1117   0.4996
   8.250   1.1069   0.01508   0.00833  -0.0549   0.0187   0.9953
   8.500   1.1343   0.01560   0.00884  -0.0555   0.0158   0.9984
   8.750   1.1671   0.01610   0.00935  -0.0572   0.0141   0.9999
   9.000   1.1824   0.01654   0.00980  -0.0552   0.0131   1.0000
   9.250   1.1953   0.01700   0.01028  -0.0527   0.0123   1.0000
   9.500   1.2070   0.01753   0.01083  -0.0501   0.0115   1.0000
   9.750   1.2208   0.01798   0.01132  -0.0479   0.0110   1.0000
  10.000   1.2337   0.01849   0.01186  -0.0456   0.0105   1.0000
  10.250   1.2460   0.01905   0.01245  -0.0433   0.0101   1.0000
  10.500   1.2579   0.01966   0.01309  -0.0410   0.0097   1.0000
  10.750   1.2690   0.02035   0.01380  -0.0388   0.0092   1.0000
  11.000   1.2793   0.02111   0.01461  -0.0365   0.0090   1.0000
  11.250   1.2878   0.02200   0.01554  -0.0341   0.0085   1.0000
  11.500   1.2990   0.02278   0.01637  -0.0321   0.0083   1.0000
  11.750   1.3089   0.02367   0.01730  -0.0301   0.0081   1.0000
  12.000   1.3190   0.02457   0.01825  -0.0282   0.0078   1.0000
  12.250   1.3276   0.02562   0.01935  -0.0263   0.0077   1.0000
  12.500   1.3374   0.02662   0.02040  -0.0246   0.0074   1.0000
  12.750   1.3457   0.02775   0.02158  -0.0229   0.0071   1.0000
  13.000   1.3528   0.02902   0.02291  -0.0211   0.0071   1.0000
  13.250   1.3606   0.03027   0.02419  -0.0196   0.0067   1.0000
  13.500   1.3667   0.03171   0.02569  -0.0180   0.0066   1.0000
  13.750   1.3716   0.03329   0.02732  -0.0165   0.0065   1.0000
  14.000   1.3722   0.03530   0.02940  -0.0149   0.0062   1.0000
  14.250   1.3787   0.03687   0.03103  -0.0137   0.0061   1.0000
  14.500   1.3824   0.03875   0.03299  -0.0126   0.0061   1.0000
  14.750   1.3881   0.04050   0.03480  -0.0117   0.0059   1.0000
  15.000   1.3905   0.04263   0.03701  -0.0107   0.0058   1.0000
  15.250   1.3908   0.04503   0.03950  -0.0099   0.0058   1.0000
  15.500   1.3954   0.04706   0.04159  -0.0093   0.0057   1.0000
  15.750   1.3965   0.04950   0.04411  -0.0087   0.0056   1.0000
  16.000   1.3965   0.05212   0.04680  -0.0082   0.0055   1.0000
  16.250   1.3959   0.05487   0.04963  -0.0079   0.0054   1.0000
  16.500   1.3963   0.05758   0.05242  -0.0076   0.0053   1.0000
  16.750   1.3940   0.06064   0.05556  -0.0076   0.0052   1.0000
  17.000   1.3909   0.06388   0.05889  -0.0076   0.0052   1.0000
  17.250   1.3888   0.06710   0.06218  -0.0077   0.0051   1.0000
  17.500   1.3827   0.07091   0.06609  -0.0081   0.0051   1.0000
  17.750   1.3834   0.07391   0.06915  -0.0085   0.0049   1.0000
  18.000   1.3769   0.07794   0.07328  -0.0092   0.0049   1.0000
  18.250   1.3721   0.08181   0.07722  -0.0100   0.0048   1.0000
  18.500   1.3662   0.08591   0.08142  -0.0109   0.0048   1.0000
  18.750   1.3617   0.08983   0.08542  -0.0119   0.0047   1.0000
  19.000   1.3518   0.09459   0.09026  -0.0131   0.0046   1.0000
  19.250   1.3446   0.09897   0.09473  -0.0144   0.0046   1.0000
<< Back to USA 28 AIRFOIL (usa28-il)

Polar data table (+)

Polar graphs


<< Back to USA 28 AIRFOIL (usa28-il)