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USA 27 mod. AIRFOIL (usa27m2-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: USA 27 mod. AIRFOIL (usa27m2-il)
Reynolds number: 200,000
Max Cl/Cd: 62.9 at α=7.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-usa27m2-il-200000-n5.txt
Download as CSV file: xf-usa27m2-il-200000-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 =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.2304   0.09952   0.09589  -0.0597   0.9824   0.0440
  -9.250  -0.2213   0.09611   0.09248  -0.0622   0.9781   0.0452
  -9.000  -0.2374   0.08741   0.08381  -0.0768   0.9697   0.0485
  -8.750  -0.2190   0.08549   0.08189  -0.0743   0.9673   0.0491
  -8.500  -0.2022   0.08315   0.07956  -0.0751   0.9639   0.0499
  -8.250  -0.1871   0.07980   0.07620  -0.0786   0.9607   0.0510
  -8.000  -0.2454   0.05745   0.05349  -0.0960   0.9389   0.0360
  -7.750  -0.2292   0.05581   0.05187  -0.0964   0.9351   0.0363
  -7.500  -0.2076   0.05438   0.05042  -0.0977   0.9325   0.0367
  -7.250  -0.2109   0.04759   0.04337  -0.0984   0.9230   0.0350
  -7.000  -0.2046   0.04132   0.03663  -0.0999   0.9177   0.0349
  -6.750  -0.1993   0.03771   0.03268  -0.0982   0.9101   0.0348
  -6.500  -0.1855   0.03447   0.02908  -0.0974   0.9040   0.0344
  -6.250  -0.1624   0.03131   0.02548  -0.0979   0.9002   0.0341
  -6.000  -0.1512   0.02936   0.02320  -0.0952   0.8899   0.0340
  -5.750  -0.1223   0.02711   0.02056  -0.0958   0.8847   0.0339
  -5.500  -0.1051   0.02564   0.01882  -0.0938   0.8745   0.0340
  -5.250  -0.0739   0.02399   0.01685  -0.0946   0.8685   0.0340
  -5.000  -0.0531   0.02291   0.01552  -0.0931   0.8578   0.0344
  -4.750  -0.0193   0.02173   0.01403  -0.0942   0.8513   0.0350
  -4.500   0.0023   0.02093   0.01304  -0.0928   0.8407   0.0353
  -4.250   0.0341   0.01996   0.01187  -0.0934   0.8335   0.0354
  -4.000   0.0594   0.01921   0.01097  -0.0927   0.8230   0.0355
  -3.750   0.0881   0.01847   0.01010  -0.0927   0.8130   0.0356
  -3.500   0.1183   0.01779   0.00929  -0.0930   0.8022   0.0358
  -3.250   0.1441   0.01726   0.00866  -0.0924   0.7892   0.0360
  -3.000   0.1708   0.01658   0.00796  -0.0920   0.7756   0.0363
  -2.750   0.1973   0.01601   0.00736  -0.0916   0.7599   0.0366
  -2.500   0.2235   0.01554   0.00684  -0.0911   0.7415   0.0370
  -2.250   0.2495   0.01515   0.00639  -0.0906   0.7210   0.0375
  -2.000   0.2748   0.01485   0.00600  -0.0899   0.6990   0.0385
  -1.750   0.2997   0.01464   0.00567  -0.0892   0.6786   0.0397
  -1.500   0.3239   0.01449   0.00538  -0.0883   0.6604   0.0406
  -1.250   0.3477   0.01439   0.00514  -0.0873   0.6439   0.0412
  -1.000   0.3715   0.01433   0.00494  -0.0864   0.6285   0.0417
  -0.750   0.3950   0.01426   0.00476  -0.0854   0.6139   0.0425
  -0.500   0.4183   0.01422   0.00460  -0.0843   0.5996   0.0436
  -0.250   0.4415   0.01420   0.00449  -0.0833   0.5852   0.0450
   0.000   0.4646   0.01418   0.00441  -0.0822   0.5709   0.0469
   0.250   0.4874   0.01416   0.00435  -0.0811   0.5562   0.0502
   0.500   0.5086   0.01398   0.00428  -0.0798   0.5410   0.0850
   0.750   0.5278   0.01370   0.00438  -0.0782   0.5251   0.2118
   1.000   0.5488   0.01373   0.00444  -0.0768   0.5084   0.2501
   1.250   0.5697   0.01382   0.00449  -0.0754   0.4918   0.2771
   1.500   0.5901   0.01390   0.00456  -0.0740   0.4766   0.3076
   1.750   0.6107   0.01402   0.00463  -0.0725   0.4627   0.3317
   2.000   0.6303   0.01408   0.00471  -0.0710   0.4503   0.3745
   2.250   0.6470   0.01366   0.00475  -0.0690   0.4394   0.5331
   2.750   0.8210   0.01425   0.00596  -0.0941   0.4099   0.9973
   3.000   0.8508   0.01450   0.00610  -0.0948   0.4028   1.0000
   3.250   0.8696   0.01470   0.00624  -0.0930   0.3972   1.0000
   3.500   0.8885   0.01489   0.00639  -0.0913   0.3910   1.0000
   3.750   0.9063   0.01512   0.00654  -0.0894   0.3852   1.0000
   4.000   0.9249   0.01533   0.00670  -0.0877   0.3802   1.0000
   4.250   0.9440   0.01552   0.00688  -0.0860   0.3756   1.0000
   4.500   0.9623   0.01573   0.00706  -0.0842   0.3712   1.0000
   4.750   0.9801   0.01598   0.00725  -0.0824   0.3670   1.0000
   5.000   0.9987   0.01618   0.00746  -0.0806   0.3626   1.0000
   5.250   1.0163   0.01638   0.00766  -0.0787   0.3571   1.0000
   5.500   1.0329   0.01663   0.00786  -0.0766   0.3519   1.0000
   5.750   1.0500   0.01689   0.00809  -0.0746   0.3479   1.0000
   6.000   1.0678   0.01708   0.00833  -0.0728   0.3437   1.0000
   6.250   1.0841   0.01729   0.00856  -0.0707   0.3394   1.0000
   6.500   1.0997   0.01753   0.00879  -0.0684   0.3356   1.0000
   6.750   1.1152   0.01782   0.00905  -0.0662   0.3321   1.0000
   7.000   1.1323   0.01804   0.00933  -0.0643   0.3283   1.0000
   7.250   1.1491   0.01827   0.00961  -0.0623   0.3241   1.0000
   7.500   1.1654   0.01855   0.00991  -0.0603   0.3199   1.0000
   7.750   1.1812   0.01887   0.01023  -0.0583   0.3160   1.0000
   8.000   1.1985   0.01916   0.01057  -0.0566   0.3118   1.0000
   8.250   1.2149   0.01945   0.01093  -0.0547   0.3061   1.0000
   8.500   1.2289   0.01982   0.01128  -0.0525   0.3000   1.0000
   8.750   1.2439   0.02015   0.01169  -0.0505   0.2920   1.0000
   9.000   1.2560   0.02059   0.01211  -0.0481   0.2832   1.0000
   9.250   1.2709   0.02098   0.01257  -0.0463   0.2733   1.0000
   9.500   1.2840   0.02148   0.01307  -0.0442   0.2641   1.0000
   9.750   1.2970   0.02201   0.01363  -0.0423   0.2538   1.0000
  10.000   1.3102   0.02258   0.01423  -0.0404   0.2424   1.0000
  10.250   1.3205   0.02330   0.01493  -0.0382   0.2281   1.0000
  10.500   1.3288   0.02418   0.01575  -0.0359   0.2125   1.0000
  10.750   1.3364   0.02516   0.01670  -0.0336   0.1994   1.0000
  11.000   1.3439   0.02621   0.01773  -0.0315   0.1895   1.0000
  11.250   1.3497   0.02742   0.01891  -0.0293   0.1808   1.0000
  11.500   1.3568   0.02860   0.02011  -0.0274   0.1726   1.0000
  11.750   1.3607   0.03004   0.02155  -0.0253   0.1641   1.0000
  12.000   1.3648   0.03153   0.02306  -0.0234   0.1549   1.0000
  12.250   1.3703   0.03299   0.02456  -0.0217   0.1471   1.0000
  12.500   1.3740   0.03465   0.02625  -0.0201   0.1382   1.0000
  12.750   1.3794   0.03625   0.02790  -0.0187   0.1272   1.0000
  13.000   1.3750   0.03872   0.03029  -0.0170   0.1039   1.0000
  13.250   1.3542   0.04289   0.03423  -0.0150   0.0760   1.0000
  13.500   1.3290   0.04787   0.03907  -0.0135   0.0415   1.0000
  13.750   1.3104   0.05256   0.04373  -0.0128   0.0283   1.0000
  14.000   1.3014   0.05643   0.04769  -0.0126   0.0249   1.0000
  14.250   1.2947   0.06014   0.05151  -0.0125   0.0232   1.0000
  14.750   1.2825   0.06775   0.05938  -0.0129   0.0212   1.0000
  15.000   1.2764   0.07170   0.06346  -0.0134   0.0205   1.0000
  15.250   1.2693   0.07587   0.06777  -0.0140   0.0200   1.0000
  15.500   1.2612   0.08027   0.07232  -0.0148   0.0196   1.0000
  15.750   1.2523   0.08488   0.07707  -0.0158   0.0192   1.0000
  16.000   1.2426   0.08969   0.08202  -0.0169   0.0189   1.0000
  16.250   1.2320   0.09470   0.08717  -0.0181   0.0186   1.0000
  16.500   1.2209   0.09988   0.09250  -0.0196   0.0184   1.0000
  16.750   1.2092   0.10525   0.09801  -0.0211   0.0181   1.0000
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