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USA 27 AIRFOIL (usa27-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: USA 27 AIRFOIL (usa27-il)
Reynolds number: 500,000
Max Cl/Cd: 92.03 at α=5.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-usa27-il-500000-n5.txt
Download as CSV file: xf-usa27-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: USA 27 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
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.2608   0.10114   0.09881  -0.0513   0.9910   0.0142
  -9.750  -0.2526   0.09688   0.09454  -0.0546   0.9888   0.0146
  -9.500  -0.2529   0.08946   0.08713  -0.0610   0.9861   0.0157
  -9.250  -0.2362   0.08721   0.08488  -0.0634   0.9844   0.0160
  -9.000  -0.2241   0.08468   0.08235  -0.0656   0.9802   0.0163
  -8.750  -0.2111   0.08124   0.07891  -0.0693   0.9770   0.0168
  -8.500  -0.1984   0.07692   0.07459  -0.0744   0.9742   0.0171
  -8.250  -0.1933   0.07274   0.07042  -0.0784   0.9654   0.0175
  -8.000  -0.1870   0.06788   0.06554  -0.0842   0.9561   0.0178
  -7.750  -0.1876   0.05608   0.05361  -0.0968   0.9436   0.0193
  -7.500  -0.1693   0.05389   0.05137  -0.0988   0.9370   0.0196
  -7.250  -0.1519   0.05110   0.04852  -0.1010   0.9282   0.0198
  -7.000  -0.1326   0.04742   0.04473  -0.1040   0.9189   0.0201
  -6.750  -0.1170   0.04313   0.04028  -0.1061   0.9064   0.0205
  -6.500  -0.1021   0.03715   0.03405  -0.1083   0.8941   0.0210
  -6.250  -0.0928   0.02968   0.02603  -0.1088   0.8823   0.0221
  -6.000  -0.0801   0.02532   0.02110  -0.1076   0.8699   0.0225
  -5.750  -0.0624   0.02276   0.01807  -0.1063   0.8569   0.0229
  -5.500  -0.0425   0.02122   0.01605  -0.1049   0.8442   0.0235
  -5.250  -0.0223   0.01956   0.01421  -0.1040   0.8329   0.0240
  -5.000   0.0005   0.01854   0.01301  -0.1033   0.8217   0.0242
  -4.750   0.0239   0.01765   0.01195  -0.1026   0.8100   0.0244
  -4.500   0.0474   0.01684   0.01094  -0.1017   0.7965   0.0247
  -4.250   0.0709   0.01610   0.01003  -0.1009   0.7806   0.0249
  -4.000   0.0945   0.01544   0.00917  -0.1000   0.7618   0.0251
  -3.750   0.1178   0.01484   0.00837  -0.0990   0.7386   0.0253
  -3.500   0.1404   0.01435   0.00765  -0.0978   0.7100   0.0255
  -3.250   0.1624   0.01397   0.00704  -0.0964   0.6804   0.0258
  -2.500   0.2327   0.01300   0.00557  -0.0935   0.6270   0.0267
  -2.250   0.2575   0.01266   0.00513  -0.0928   0.6162   0.0269
  -2.000   0.2822   0.01237   0.00475  -0.0921   0.6063   0.0271
  -1.750   0.3072   0.01210   0.00442  -0.0914   0.5964   0.0274
  -1.500   0.3322   0.01188   0.00413  -0.0908   0.5865   0.0277
  -1.250   0.3568   0.01171   0.00389  -0.0900   0.5759   0.0280
  -1.000   0.3819   0.01154   0.00368  -0.0894   0.5644   0.0282
  -0.750   0.4067   0.01141   0.00350  -0.0888   0.5529   0.0284
  -0.500   0.4313   0.01130   0.00334  -0.0881   0.5407   0.0286
  -0.250   0.4550   0.01110   0.00310  -0.0872   0.5266   0.0290
   0.000   0.4784   0.01096   0.00290  -0.0863   0.5082   0.0298
   0.250   0.5016   0.01094   0.00279  -0.0854   0.4870   0.0306
   0.750   0.5480   0.01102   0.00267  -0.0835   0.4484   0.0316
   1.000   0.5718   0.01108   0.00264  -0.0827   0.4330   0.0321
   1.500   0.6207   0.01119   0.00263  -0.0813   0.4104   0.0336
   1.750   0.6453   0.01127   0.00265  -0.0807   0.4021   0.0345
   2.000   0.6704   0.01132   0.00267  -0.0802   0.3942   0.0354
   2.250   0.6950   0.01141   0.00272  -0.0795   0.3864   0.0376
   2.750   0.7422   0.01122   0.00294  -0.0781   0.3725   0.2275
   3.000   0.7667   0.01120   0.00307  -0.0776   0.3667   0.2932
   3.250   0.7908   0.01120   0.00321  -0.0770   0.3599   0.3568
   3.750   0.8842   0.01041   0.00384  -0.0857   0.3456   0.9902
   4.000   0.9427   0.01069   0.00405  -0.0928   0.3387   1.0000
   4.250   0.9641   0.01082   0.00416  -0.0916   0.3337   1.0000
   4.500   0.9850   0.01096   0.00430  -0.0902   0.3292   1.0000
   4.750   1.0051   0.01113   0.00444  -0.0887   0.3248   1.0000
   5.000   1.0260   0.01127   0.00458  -0.0874   0.3204   1.0000
   5.250   1.0466   0.01142   0.00473  -0.0860   0.3152   1.0000
   5.500   1.0657   0.01163   0.00490  -0.0844   0.3085   1.0000
   5.750   1.0859   0.01180   0.00505  -0.0829   0.2997   1.0000
   6.000   1.1047   0.01202   0.00524  -0.0812   0.2898   1.0000
   6.250   1.1235   0.01224   0.00543  -0.0796   0.2793   1.0000
   6.500   1.1421   0.01247   0.00563  -0.0779   0.2673   1.0000
   6.750   1.1597   0.01276   0.00585  -0.0760   0.2526   1.0000
   7.000   1.1740   0.01319   0.00615  -0.0736   0.2258   1.0000
   7.250   1.1820   0.01392   0.00662  -0.0701   0.1868   1.0000
   7.500   1.1938   0.01451   0.00709  -0.0674   0.1673   1.0000
   7.750   1.2087   0.01499   0.00751  -0.0652   0.1552   1.0000
   8.000   1.2238   0.01549   0.00796  -0.0632   0.1421   1.0000
   8.250   1.2369   0.01613   0.00849  -0.0609   0.1221   1.0000
   8.500   1.2328   0.01779   0.00972  -0.0560   0.0597   1.0000
   8.750   1.2335   0.01921   0.01097  -0.0520   0.0190   1.0000
   9.000   1.2488   0.01978   0.01159  -0.0503   0.0168   1.0000
   9.250   1.2630   0.02043   0.01229  -0.0485   0.0153   1.0000
   9.500   1.2764   0.02115   0.01308  -0.0466   0.0139   1.0000
   9.750   1.2910   0.02180   0.01380  -0.0450   0.0133   1.0000
  10.000   1.3045   0.02253   0.01460  -0.0433   0.0125   1.0000
  10.250   1.3170   0.02335   0.01549  -0.0416   0.0118   1.0000
  10.500   1.3282   0.02428   0.01649  -0.0398   0.0113   1.0000
  10.750   1.3373   0.02538   0.01767  -0.0379   0.0108   1.0000
  11.000   1.3430   0.02676   0.01916  -0.0358   0.0103   1.0000
  11.250   1.3528   0.02788   0.02036  -0.0342   0.0101   1.0000
  11.500   1.3614   0.02914   0.02169  -0.0326   0.0097   1.0000
  11.750   1.3689   0.03053   0.02317  -0.0311   0.0094   1.0000
  12.000   1.3752   0.03206   0.02479  -0.0297   0.0090   1.0000
  12.250   1.3804   0.03376   0.02657  -0.0283   0.0087   1.0000
  12.500   1.3842   0.03566   0.02855  -0.0271   0.0084   1.0000
  12.750   1.3864   0.03779   0.03078  -0.0260   0.0082   1.0000
  13.000   1.3869   0.04020   0.03328  -0.0251   0.0080   1.0000
  13.250   1.3852   0.04300   0.03619  -0.0244   0.0078   1.0000
  13.500   1.3801   0.04635   0.03965  -0.0239   0.0077   1.0000
  13.750   1.3713   0.05031   0.04374  -0.0238   0.0075   1.0000
  14.000   1.3683   0.05371   0.04726  -0.0239   0.0075   1.0000
  14.250   1.3637   0.05739   0.05106  -0.0241   0.0074   1.0000
  14.500   1.3574   0.06135   0.05513  -0.0245   0.0073   1.0000
  14.750   1.3501   0.06555   0.05945  -0.0251   0.0072   1.0000
  15.000   1.3419   0.06999   0.06400  -0.0258   0.0071   1.0000
  15.250   1.3329   0.07460   0.06873  -0.0267   0.0070   1.0000
  15.500   1.3236   0.07934   0.07359  -0.0277   0.0069   1.0000
  15.750   1.3146   0.08412   0.07848  -0.0287   0.0069   1.0000
  16.000   1.3059   0.08892   0.08338  -0.0299   0.0068   1.0000
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