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USA 27 mod. AIRFOIL (usa27m2-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: USA 27 mod. AIRFOIL (usa27m2-il)
Reynolds number: 100,000
Max Cl/Cd: 48.6 at α=6.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-usa27m2-il-100000-n5.txt
Download as CSV file: xf-usa27m2-il-100000-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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.2854   0.10250   0.09779  -0.0424   0.9869   0.0826
  -8.250  -0.2929   0.09859   0.09392  -0.0500   0.9792   0.0862
  -8.000  -0.3080   0.09382   0.08913  -0.0601   0.9668   0.0871
  -7.500  -0.2737   0.08551   0.08083  -0.0623   0.9600   0.0885
  -7.000  -0.2755   0.06860   0.06357  -0.0721   0.9412   0.0557
  -6.500  -0.2708   0.05329   0.04754  -0.0770   0.9243   0.0484
  -6.250  -0.2519   0.05005   0.04415  -0.0779   0.9187   0.0479
  -6.000  -0.2359   0.04654   0.04039  -0.0782   0.9125   0.0474
  -5.750  -0.2225   0.04320   0.03671  -0.0775   0.9046   0.0469
  -5.500  -0.1979   0.03957   0.03259  -0.0786   0.9005   0.0468
  -5.250  -0.1849   0.03716   0.02974  -0.0767   0.8902   0.0472
  -5.000  -0.1536   0.03452   0.02658  -0.0778   0.8852   0.0476
  -4.750  -0.1326   0.03268   0.02440  -0.0766   0.8745   0.0477
  -4.500  -0.0956   0.03053   0.02186  -0.0782   0.8689   0.0475
  -4.250  -0.0724   0.02908   0.02013  -0.0770   0.8578   0.0475
  -4.000  -0.0350   0.02745   0.01821  -0.0785   0.8526   0.0476
  -3.750  -0.0120   0.02641   0.01698  -0.0773   0.8422   0.0478
  -3.500   0.0250   0.02516   0.01552  -0.0786   0.8365   0.0480
  -3.250   0.0497   0.02432   0.01455  -0.0777   0.8258   0.0483
  -3.000   0.0860   0.02322   0.01339  -0.0790   0.8194   0.0493
  -2.750   0.1097   0.02255   0.01273  -0.0781   0.8076   0.0506
  -2.500   0.1424   0.02178   0.01191  -0.0787   0.7989   0.0521
  -2.250   0.1699   0.02116   0.01123  -0.0783   0.7872   0.0530
  -2.000   0.1955   0.02064   0.01066  -0.0776   0.7742   0.0538
  -1.750   0.2239   0.02012   0.01007  -0.0773   0.7614   0.0547
  -1.500   0.2538   0.01965   0.00949  -0.0773   0.7484   0.0558
  -1.250   0.2837   0.01916   0.00894  -0.0774   0.7345   0.0574
  -1.000   0.3132   0.01876   0.00846  -0.0774   0.7193   0.0597
  -0.750   0.3434   0.01843   0.00802  -0.0775   0.7032   0.0638
   0.000   0.4368   0.01723   0.00722  -0.0787   0.6540   0.2394
   0.250   0.4652   0.01719   0.00719  -0.0787   0.6380   0.2933
   0.500   0.4923   0.01720   0.00712  -0.0784   0.6221   0.3251
   0.750   0.5181   0.01718   0.00707  -0.0779   0.6064   0.3621
   1.000   0.5418   0.01710   0.00701  -0.0771   0.5909   0.4013
   1.500   0.7163   0.01672   0.00761  -0.1011   0.5480   1.0000
   1.750   0.7362   0.01693   0.00767  -0.0996   0.5339   1.0000
   2.000   0.7556   0.01715   0.00775  -0.0979   0.5200   1.0000
   2.250   0.7752   0.01737   0.00784  -0.0963   0.5073   1.0000
   2.500   0.7948   0.01761   0.00793  -0.0947   0.4959   1.0000
   2.750   0.8145   0.01787   0.00805  -0.0931   0.4853   1.0000
   3.000   0.8340   0.01812   0.00820  -0.0916   0.4753   1.0000
   3.500   0.8735   0.01868   0.00856  -0.0885   0.4580   1.0000
   4.000   0.9127   0.01928   0.00898  -0.0855   0.4422   1.0000
   4.250   0.9325   0.01961   0.00919  -0.0840   0.4349   1.0000
   4.500   0.9513   0.01992   0.00947  -0.0824   0.4271   1.0000
   4.750   0.9706   0.02025   0.00972  -0.0809   0.4202   1.0000
   5.000   0.9906   0.02059   0.01002  -0.0795   0.4141   1.0000
   5.250   1.0094   0.02092   0.01035  -0.0779   0.4076   1.0000
   5.500   1.0294   0.02128   0.01063  -0.0766   0.4018   1.0000
   5.750   1.0481   0.02163   0.01098  -0.0750   0.3958   1.0000
   6.000   1.0661   0.02198   0.01136  -0.0733   0.3896   1.0000
   6.250   1.0861   0.02235   0.01168  -0.0720   0.3845   1.0000
   6.500   1.1045   0.02273   0.01209  -0.0704   0.3793   1.0000
   6.750   1.1221   0.02310   0.01253  -0.0687   0.3739   1.0000
   7.000   1.1409   0.02348   0.01290  -0.0672   0.3688   1.0000
   7.250   1.1599   0.02389   0.01331  -0.0658   0.3639   1.0000
   7.500   1.1753   0.02429   0.01381  -0.0637   0.3582   1.0000
   7.750   1.1923   0.02468   0.01425  -0.0620   0.3529   1.0000
   8.000   1.2117   0.02511   0.01464  -0.0607   0.3483   1.0000
   8.250   1.2250   0.02556   0.01524  -0.0583   0.3427   1.0000
   8.500   1.2395   0.02599   0.01576  -0.0562   0.3374   1.0000
   8.750   1.2566   0.02642   0.01618  -0.0545   0.3327   1.0000
   9.000   1.2688   0.02693   0.01681  -0.0521   0.3272   1.0000
   9.250   1.2810   0.02743   0.01743  -0.0497   0.3214   1.0000
   9.500   1.2959   0.02791   0.01792  -0.0478   0.3163   1.0000
   9.750   1.3060   0.02850   0.01866  -0.0452   0.3100   1.0000
  10.000   1.3141   0.02906   0.01930  -0.0424   0.3025   1.0000
  10.250   1.3216   0.02968   0.01997  -0.0396   0.2947   1.0000
  10.500   1.3267   0.03037   0.02075  -0.0366   0.2857   1.0000
  10.750   1.3317   0.03117   0.02165  -0.0338   0.2766   1.0000
  11.000   1.3369   0.03200   0.02252  -0.0312   0.2681   1.0000
  11.250   1.3424   0.03300   0.02367  -0.0288   0.2591   1.0000
  11.500   1.3467   0.03406   0.02476  -0.0264   0.2507   1.0000
  11.750   1.3502   0.03529   0.02610  -0.0242   0.2413   1.0000
  12.000   1.3538   0.03662   0.02752  -0.0221   0.2329   1.0000
  12.250   1.3566   0.03807   0.02904  -0.0202   0.2254   1.0000
  12.500   1.3590   0.03969   0.03076  -0.0184   0.2177   1.0000
  12.750   1.3577   0.04158   0.03266  -0.0166   0.2099   1.0000
  13.000   1.3561   0.04370   0.03487  -0.0151   0.2012   1.0000
  13.250   1.3521   0.04610   0.03730  -0.0137   0.1939   1.0000
  13.500   1.3490   0.04863   0.03992  -0.0126   0.1873   1.0000
  13.750   1.3435   0.05147   0.04279  -0.0116   0.1818   1.0000
  14.000   1.3394   0.05444   0.04590  -0.0110   0.1761   1.0000
  14.250   1.3318   0.05788   0.04941  -0.0106   0.1702   1.0000
  14.500   1.3225   0.06166   0.05325  -0.0105   0.1644   1.0000
  14.750   1.3125   0.06578   0.05752  -0.0108   0.1581   1.0000
  15.000   1.3011   0.07012   0.06192  -0.0111   0.1529   1.0000
  15.250   1.2909   0.07458   0.06653  -0.0118   0.1478   1.0000
  15.500   1.2792   0.07939   0.07150  -0.0127   0.1424   1.0000
  15.750   1.2668   0.08431   0.07650  -0.0137   0.1373   1.0000
  16.000   1.2548   0.08949   0.08189  -0.0150   0.1309   1.0000
  16.250   1.2414   0.09486   0.08738  -0.0165   0.1241   1.0000
  16.500   1.2305   0.10001   0.09271  -0.0179   0.1167   1.0000
  16.750   1.2193   0.10525   0.09807  -0.0195   0.1081   1.0000
  17.000   1.2074   0.11056   0.10344  -0.0212   0.0967   1.0000
  17.250   1.1927   0.11633   0.10915  -0.0232   0.0841   1.0000
  17.500   1.1751   0.12272   0.11546  -0.0256   0.0686   1.0000
  17.750   1.1535   0.12994   0.12255  -0.0285   0.0469   1.0000
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