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USA 27 mod. AIRFOIL (usa27m2-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: USA 27 mod. AIRFOIL (usa27m2-il)
Reynolds number: 1,000,000
Max Cl/Cd: 110.03 at α=6.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-usa27m2-il-1000000.txt
Download as CSV file: xf-usa27m2-il-1000000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.1803   0.05994   0.05816  -0.1110   0.9707   0.0247
  -8.750  -0.1774   0.05695   0.05515  -0.1124   0.9611   0.0248
  -8.500  -0.1694   0.05356   0.05171  -0.1148   0.9535   0.0250
  -8.250  -0.1606   0.04998   0.04806  -0.1170   0.9452   0.0252
  -8.000  -0.1542   0.04588   0.04387  -0.1185   0.9345   0.0254
  -7.750  -0.1561   0.03735   0.03505  -0.1215   0.9231   0.0260
  -7.500  -0.1499   0.03318   0.03058  -0.1213   0.9137   0.0266
  -7.250  -0.1449   0.02951   0.02650  -0.1194   0.9033   0.0281
  -7.000  -0.1317   0.02861   0.02507  -0.1172   0.8947   0.0288
  -6.750  -0.1321   0.02365   0.01962  -0.1142   0.8849   0.0293
  -6.500  -0.1116   0.02203   0.01798  -0.1134   0.8766   0.0297
  -6.250  -0.0901   0.02093   0.01680  -0.1126   0.8680   0.0300
  -6.000  -0.0687   0.02002   0.01582  -0.1117   0.8598   0.0305
  -5.750  -0.0468   0.01917   0.01484  -0.1108   0.8518   0.0311
  -5.500  -0.0252   0.01833   0.01384  -0.1096   0.8439   0.0321
  -5.250   0.0008   0.01926   0.01452  -0.1086   0.8352   0.0338
  -5.000   0.0159   0.01633   0.01134  -0.1067   0.8264   0.0351
  -4.750   0.0397   0.01555   0.01051  -0.1060   0.8165   0.0357
  -4.500   0.0631   0.01493   0.00983  -0.1052   0.8052   0.0364
  -4.250   0.0868   0.01444   0.00923  -0.1042   0.7931   0.0375
  -4.000   0.1107   0.01424   0.00888  -0.1031   0.7794   0.0389
  -3.750   0.1348   0.01237   0.00653  -0.1012   0.7637   0.0293
  -3.500   0.1578   0.01185   0.00591  -0.1001   0.7418   0.0293
  -3.250   0.1791   0.01156   0.00547  -0.0985   0.7118   0.0292
  -3.000   0.1992   0.01134   0.00509  -0.0968   0.6797   0.0292
  -2.250   0.2645   0.01040   0.00389  -0.0927   0.6250   0.0296
  -2.000   0.2876   0.01016   0.00361  -0.0916   0.6133   0.0299
  -1.750   0.3106   0.01000   0.00339  -0.0906   0.6023   0.0302
  -1.500   0.3348   0.00982   0.00320  -0.0897   0.5918   0.0304
  -1.250   0.3585   0.00970   0.00302  -0.0888   0.5811   0.0307
  -1.000   0.3818   0.00961   0.00288  -0.0877   0.5678   0.0310
  -0.750   0.4051   0.00953   0.00274  -0.0867   0.5523   0.0313
  -0.500   0.4283   0.00949   0.00263  -0.0857   0.5339   0.0319
  -0.250   0.4511   0.00948   0.00254  -0.0845   0.5120   0.0326
   0.000   0.4725   0.00955   0.00248  -0.0832   0.4858   0.0332
   0.250   0.4942   0.00963   0.00244  -0.0819   0.4606   0.0337
   0.500   0.5161   0.00971   0.00241  -0.0806   0.4398   0.0343
   0.750   0.5386   0.00976   0.00237  -0.0795   0.4238   0.0355
   1.000   0.5621   0.00981   0.00236  -0.0785   0.4120   0.0370
   1.250   0.5856   0.00988   0.00237  -0.0776   0.4021   0.0387
   1.500   0.6102   0.00990   0.00238  -0.0769   0.3943   0.0431
   1.750   0.6298   0.00961   0.00245  -0.0754   0.3867   0.1937
   2.000   0.6532   0.00952   0.00255  -0.0746   0.3809   0.2679
   2.250   0.6771   0.00954   0.00265  -0.0738   0.3746   0.3070
   2.500   0.7008   0.00960   0.00274  -0.0731   0.3686   0.3383
   2.750   0.7254   0.00958   0.00282  -0.0725   0.3641   0.3761
   3.000   0.7393   0.00886   0.00289  -0.0699   0.3597   0.7019
   3.250   0.7732   0.00861   0.00334  -0.0710   0.3535   0.9646
   3.500   0.8152   0.00886   0.00357  -0.0741   0.3482   0.9798
   3.750   0.8736   0.00921   0.00384  -0.0810   0.3415   0.9863
   4.000   0.9212   0.00949   0.00406  -0.0856   0.3360   0.9908
   4.250   0.9595   0.00965   0.00421  -0.0880   0.3327   0.9937
   4.500   1.0048   0.00981   0.00434  -0.0921   0.3283   0.9955
   4.750   1.0459   0.01000   0.00448  -0.0953   0.3232   0.9975
   5.000   1.0853   0.01016   0.00461  -0.0981   0.3189   0.9993
   5.250   1.1141   0.01025   0.00472  -0.0985   0.3157   1.0000
   5.500   1.1323   0.01037   0.00483  -0.0966   0.3120   1.0000
   5.750   1.1486   0.01053   0.00496  -0.0944   0.3064   1.0000
   6.000   1.1657   0.01065   0.00508  -0.0923   0.3023   1.0000
   6.250   1.1828   0.01075   0.00518  -0.0901   0.2986   1.0000
   6.500   1.1953   0.01087   0.00530  -0.0871   0.2938   1.0000
   6.750   1.2045   0.01103   0.00543  -0.0833   0.2882   1.0000
   7.000   1.2186   0.01111   0.00553  -0.0806   0.2840   1.0000
   7.250   1.2321   0.01125   0.00566  -0.0777   0.2786   1.0000
   7.500   1.2446   0.01144   0.00583  -0.0748   0.2723   1.0000
   7.750   1.2601   0.01159   0.00598  -0.0724   0.2648   1.0000
   8.000   1.2737   0.01184   0.00618  -0.0698   0.2543   1.0000
   8.250   1.2866   0.01215   0.00642  -0.0671   0.2397   1.0000
   8.500   1.2967   0.01262   0.00676  -0.0640   0.2162   1.0000
   8.750   1.3031   0.01330   0.00726  -0.0603   0.1895   1.0000
   9.000   1.3144   0.01382   0.00770  -0.0576   0.1766   1.0000
   9.250   1.3280   0.01429   0.00814  -0.0553   0.1675   1.0000
   9.500   1.3411   0.01482   0.00861  -0.0531   0.1589   1.0000
   9.750   1.3570   0.01525   0.00904  -0.0513   0.1515   1.0000
  10.000   1.3703   0.01583   0.00957  -0.0492   0.1418   1.0000
  10.250   1.3817   0.01654   0.01018  -0.0470   0.1244   1.0000
  10.500   1.3734   0.01834   0.01163  -0.0420   0.0783   1.0000
  10.750   1.3524   0.02097   0.01398  -0.0357   0.0252   1.0000
  11.000   1.3599   0.02206   0.01508  -0.0334   0.0193   1.0000
  11.250   1.3700   0.02304   0.01610  -0.0315   0.0175   1.0000
  11.500   1.3814   0.02395   0.01706  -0.0299   0.0167   1.0000
  11.750   1.3918   0.02495   0.01811  -0.0283   0.0159   1.0000
  12.000   1.4007   0.02609   0.01930  -0.0266   0.0153   1.0000
  12.250   1.4078   0.02740   0.02068  -0.0249   0.0147   1.0000
  12.500   1.4123   0.02897   0.02232  -0.0231   0.0141   1.0000
  12.750   1.4209   0.03026   0.02367  -0.0217   0.0138   1.0000
  13.000   1.4281   0.03172   0.02519  -0.0204   0.0135   1.0000
  13.250   1.4340   0.03335   0.02689  -0.0192   0.0132   1.0000
  13.500   1.4388   0.03516   0.02877  -0.0180   0.0129   1.0000
  13.750   1.4423   0.03714   0.03083  -0.0170   0.0126   1.0000
  14.000   1.4444   0.03936   0.03312  -0.0161   0.0123   1.0000
  14.250   1.4447   0.04188   0.03573  -0.0153   0.0121   1.0000
  14.500   1.4415   0.04491   0.03884  -0.0147   0.0118   1.0000
  14.750   1.4331   0.04862   0.04267  -0.0143   0.0115   1.0000
  15.000   1.4235   0.05263   0.04680  -0.0141   0.0113   1.0000
  15.250   1.4225   0.05570   0.04996  -0.0141   0.0112   1.0000
  15.500   1.4185   0.05919   0.05355  -0.0142   0.0111   1.0000
  15.750   1.4125   0.06298   0.05743  -0.0145   0.0110   1.0000
  16.000   1.4052   0.06704   0.06159  -0.0149   0.0109   1.0000
  16.250   1.3964   0.07141   0.06606  -0.0155   0.0108   1.0000
  16.500   1.3863   0.07602   0.07077  -0.0163   0.0107   1.0000
  16.750   1.3756   0.08077   0.07563  -0.0171   0.0106   1.0000
  17.000   1.3639   0.08575   0.08072  -0.0182   0.0105   1.0000
  17.250   1.3522   0.09080   0.08587  -0.0193   0.0104   1.0000
  17.500   1.3402   0.09590   0.09106  -0.0205   0.0103   1.0000
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