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USA 27 mod. AIRFOIL (usa27m2-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: USA 27 mod. AIRFOIL (usa27m2-il)
Reynolds number: 1,000,000
Max Cl/Cd: 102.54 at α=6.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-usa27m2-il-1000000-n5.txt
Download as CSV file: xf-usa27m2-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: USA 27 mod. 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
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.4085   0.03368   0.03102  -0.1222   0.9418   0.0185
 -10.000  -0.4165   0.02880   0.02563  -0.1209   0.9313   0.0186
  -9.750  -0.4135   0.02592   0.02243  -0.1190   0.9222   0.0188
  -9.500  -0.3977   0.02434   0.02067  -0.1181   0.9154   0.0189
  -9.250  -0.3803   0.02323   0.01943  -0.1169   0.9075   0.0190
  -9.000  -0.3605   0.02223   0.01828  -0.1161   0.9004   0.0191
  -8.750  -0.3403   0.02143   0.01736  -0.1152   0.8921   0.0192
  -8.500  -0.3187   0.02074   0.01654  -0.1144   0.8825   0.0193
  -8.250  -0.2975   0.02009   0.01577  -0.1134   0.8697   0.0195
  -8.000  -0.2764   0.01943   0.01497  -0.1124   0.8565   0.0196
  -7.750  -0.2555   0.01867   0.01405  -0.1114   0.8456   0.0197
  -7.500  -0.2343   0.01794   0.01316  -0.1103   0.8353   0.0199
  -7.250  -0.2124   0.01722   0.01231  -0.1093   0.8257   0.0200
  -7.000  -0.1905   0.01654   0.01148  -0.1083   0.8161   0.0202
  -6.750  -0.1682   0.01589   0.01069  -0.1073   0.8047   0.0204
  -6.500  -0.1458   0.01529   0.00994  -0.1063   0.7921   0.0205
  -6.250  -0.1233   0.01473   0.00924  -0.1052   0.7780   0.0207
  -6.000  -0.1010   0.01423   0.00859  -0.1041   0.7610   0.0208
  -5.750  -0.0794   0.01379   0.00799  -0.1028   0.7374   0.0210
  -5.500  -0.0599   0.01349   0.00747  -0.1010   0.6990   0.0211
  -5.250  -0.0406   0.01324   0.00702  -0.0991   0.6634   0.0212
  -5.000  -0.0188   0.01296   0.00658  -0.0979   0.6427   0.0213
  -4.750   0.0043   0.01265   0.00617  -0.0969   0.6290   0.0215
  -4.500   0.0279   0.01237   0.00579  -0.0959   0.6179   0.0216
  -4.250   0.0523   0.01212   0.00548  -0.0952   0.6081   0.0218
  -4.000   0.0767   0.01194   0.00522  -0.0944   0.5987   0.0220
  -3.750   0.1013   0.01176   0.00497  -0.0936   0.5886   0.0221
  -3.500   0.1258   0.01155   0.00471  -0.0929   0.5792   0.0222
  -3.250   0.1492   0.01118   0.00429  -0.0920   0.5693   0.0224
  -3.000   0.1732   0.01089   0.00396  -0.0911   0.5599   0.0226
  -2.750   0.1970   0.01071   0.00373  -0.0903   0.5486   0.0228
  -2.500   0.2212   0.01057   0.00355  -0.0894   0.5349   0.0231
  -2.250   0.2450   0.01047   0.00339  -0.0885   0.5184   0.0233
  -2.000   0.2680   0.01043   0.00326  -0.0875   0.4971   0.0235
  -1.750   0.2905   0.01043   0.00314  -0.0864   0.4722   0.0238
  -1.500   0.3129   0.01045   0.00305  -0.0852   0.4504   0.0241
  -1.250   0.3362   0.01045   0.00297  -0.0842   0.4333   0.0243
  -1.000   0.3598   0.01044   0.00289  -0.0833   0.4187   0.0246
  -0.750   0.3836   0.01044   0.00282  -0.0825   0.4049   0.0249
  -0.500   0.4075   0.01044   0.00277  -0.0816   0.3923   0.0252
  -0.250   0.4315   0.01045   0.00272  -0.0808   0.3820   0.0255
   0.000   0.4566   0.01042   0.00267  -0.0802   0.3755   0.0258
   0.250   0.4813   0.01043   0.00264  -0.0795   0.3689   0.0261
   0.500   0.5059   0.01039   0.00259  -0.0788   0.3637   0.0267
   0.750   0.5307   0.01036   0.00254  -0.0782   0.3586   0.0274
   1.000   0.5554   0.01037   0.00253  -0.0775   0.3532   0.0280
   1.250   0.5799   0.01039   0.00253  -0.0768   0.3478   0.0287
   1.500   0.6049   0.01041   0.00254  -0.0763   0.3427   0.0294
   1.750   0.6295   0.01046   0.00256  -0.0756   0.3369   0.0302
   2.000   0.6538   0.01052   0.00259  -0.0749   0.3316   0.0310
   2.250   0.6790   0.01054   0.00262  -0.0744   0.3285   0.0330
   2.750   0.7251   0.01032   0.00274  -0.0726   0.3198   0.1912
   3.000   0.7482   0.01031   0.00284  -0.0717   0.3159   0.2415
   3.250   0.7721   0.01033   0.00293  -0.0710   0.3133   0.2698
   3.750   0.8200   0.01038   0.00312  -0.0696   0.3074   0.3244
   4.000   0.8435   0.01042   0.00323  -0.0688   0.3041   0.3574
   4.250   0.8662   0.01039   0.00334  -0.0679   0.3007   0.4262
   4.500   0.8914   0.00944   0.00378  -0.0675   0.2975   0.9643
   4.750   0.9297   0.00966   0.00399  -0.0700   0.2933   0.9807
   5.000   0.9663   0.00988   0.00418  -0.0721   0.2882   0.9854
   5.250   1.0010   0.01010   0.00437  -0.0739   0.2839   0.9886
   5.500   1.0327   0.01028   0.00453  -0.0750   0.2806   0.9917
   5.750   1.0638   0.01047   0.00470  -0.0760   0.2738   0.9939
   6.000   1.0979   0.01074   0.00490  -0.0778   0.2643   0.9957
   6.250   1.1290   0.01101   0.00511  -0.0789   0.2530   0.9974
   6.500   1.1588   0.01131   0.00534  -0.0798   0.2393   0.9990
   6.750   1.1802   0.01176   0.00564  -0.0789   0.2147   1.0000
   7.000   1.1838   0.01223   0.00597  -0.0743   0.1906   1.0000
   7.250   1.1920   0.01262   0.00628  -0.0706   0.1764   1.0000
   7.500   1.2033   0.01295   0.00656  -0.0675   0.1683   1.0000
   7.750   1.2176   0.01321   0.00681  -0.0651   0.1634   1.0000
   8.000   1.2322   0.01350   0.00709  -0.0628   0.1585   1.0000
   8.250   1.2457   0.01387   0.00742  -0.0603   0.1521   1.0000
   8.500   1.2619   0.01415   0.00771  -0.0584   0.1474   1.0000
   8.750   1.2763   0.01455   0.00807  -0.0562   0.1404   1.0000
   9.000   1.2917   0.01494   0.00844  -0.0542   0.1334   1.0000
   9.250   1.3050   0.01548   0.00890  -0.0521   0.1216   1.0000
   9.500   1.3049   0.01673   0.00990  -0.0479   0.0843   1.0000
   9.750   1.2955   0.01855   0.01147  -0.0426   0.0398   1.0000
  10.000   1.2982   0.01981   0.01267  -0.0393   0.0174   1.0000
  10.250   1.3117   0.02049   0.01337  -0.0376   0.0154   1.0000
  10.500   1.3256   0.02117   0.01408  -0.0360   0.0142   1.0000
  10.750   1.3397   0.02186   0.01481  -0.0346   0.0136   1.0000
  11.000   1.3530   0.02261   0.01559  -0.0331   0.0129   1.0000
  11.250   1.3653   0.02346   0.01647  -0.0315   0.0123   1.0000
  11.500   1.3765   0.02440   0.01745  -0.0300   0.0117   1.0000
  11.750   1.3875   0.02539   0.01848  -0.0285   0.0112   1.0000
  12.000   1.3989   0.02636   0.01949  -0.0271   0.0108   1.0000
  12.250   1.4097   0.02741   0.02059  -0.0258   0.0105   1.0000
  12.500   1.4198   0.02855   0.02178  -0.0245   0.0102   1.0000
  12.750   1.4287   0.02981   0.02309  -0.0232   0.0099   1.0000
  13.000   1.4367   0.03118   0.02451  -0.0219   0.0095   1.0000
  13.250   1.4437   0.03269   0.02607  -0.0207   0.0093   1.0000
  13.500   1.4493   0.03439   0.02783  -0.0195   0.0090   1.0000
  13.750   1.4528   0.03635   0.02986  -0.0184   0.0087   1.0000
  14.000   1.4577   0.03825   0.03183  -0.0176   0.0086   1.0000
  14.250   1.4625   0.04025   0.03390  -0.0168   0.0084   1.0000
  14.500   1.4665   0.04242   0.03614  -0.0163   0.0083   1.0000
  14.750   1.4695   0.04477   0.03856  -0.0159   0.0081   1.0000
  15.000   1.4713   0.04731   0.04117  -0.0155   0.0079   1.0000
  15.250   1.4719   0.05004   0.04398  -0.0153   0.0077   1.0000
  15.500   1.4716   0.05294   0.04695  -0.0152   0.0076   1.0000
  15.750   1.4700   0.05603   0.05013  -0.0152   0.0074   1.0000
  16.000   1.4669   0.05935   0.05353  -0.0153   0.0073   1.0000
  16.250   1.4621   0.06293   0.05719  -0.0155   0.0072   1.0000
  16.500   1.4559   0.06676   0.06112  -0.0158   0.0071   1.0000
  16.750   1.4486   0.07085   0.06529  -0.0163   0.0070   1.0000
  17.000   1.4402   0.07513   0.06967  -0.0170   0.0069   1.0000
  17.250   1.4300   0.07971   0.07435  -0.0177   0.0068   1.0000
  17.500   1.4189   0.08452   0.07927  -0.0187   0.0067   1.0000
  17.750   1.4069   0.08951   0.08436  -0.0198   0.0067   1.0000
  18.000   1.3938   0.09468   0.08963  -0.0210   0.0066   1.0000
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