Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

TRAINER60 (trainer60-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: TRAINER60 (trainer60-il)
Reynolds number: 200,000
Max Cl/Cd: 50.93 at α=9.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-trainer60-il-200000-n5.txt
Download as CSV file: xf-trainer60-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: TRAINER60                                       
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -16.250  -1.1582   0.08986   0.08340   0.0070   1.0000   0.0454
 -16.000  -1.1656   0.08508   0.07857   0.0050   1.0000   0.0461
 -15.750  -1.1727   0.08037   0.07378   0.0031   1.0000   0.0469
 -15.500  -1.1791   0.07582   0.06915   0.0013   1.0000   0.0478
 -15.250  -1.1848   0.07147   0.06471  -0.0003   1.0000   0.0490
 -15.000  -1.1890   0.06741   0.06054  -0.0017   1.0000   0.0501
 -14.750  -1.1953   0.06323   0.05627  -0.0032   1.0000   0.0513
 -14.500  -1.2022   0.05909   0.05206  -0.0045   1.0000   0.0524
 -14.250  -1.2071   0.05527   0.04816  -0.0057   1.0000   0.0538
 -14.000  -1.2094   0.05183   0.04462  -0.0066   1.0000   0.0558
 -13.750  -1.2120   0.04838   0.04109  -0.0075   1.0000   0.0575
 -13.500  -1.2144   0.04502   0.03767  -0.0084   1.0000   0.0598
 -13.250  -1.2132   0.04210   0.03468  -0.0090   1.0000   0.0625
 -13.000  -1.2133   0.03911   0.03164  -0.0096   1.0000   0.0656
 -12.750  -1.2107   0.03652   0.02899  -0.0099   1.0000   0.0695
 -12.500  -1.2087   0.03400   0.02644  -0.0100   1.0000   0.0739
 -12.250  -1.2055   0.03173   0.02415  -0.0097   1.0000   0.0800
 -12.000  -1.2020   0.02970   0.02212  -0.0091   1.0000   0.0877
 -11.750  -1.1978   0.02790   0.02035  -0.0081   1.0000   0.0972
 -11.500  -1.1921   0.02641   0.01891  -0.0067   1.0000   0.1088
 -11.250  -1.1841   0.02527   0.01780  -0.0049   1.0000   0.1200
 -11.000  -1.1733   0.02436   0.01690  -0.0030   1.0000   0.1304
 -10.750  -1.1578   0.02359   0.01612  -0.0018   1.0000   0.1401
 -10.500  -1.1396   0.02292   0.01543  -0.0008   1.0000   0.1493
 -10.250  -1.1216   0.02225   0.01477   0.0003   1.0000   0.1564
 -10.000  -1.1004   0.02174   0.01419   0.0010   1.0000   0.1639
  -9.750  -1.0811   0.02113   0.01360   0.0020   1.0000   0.1703
  -9.250  -1.0439   0.02003   0.01246   0.0048   0.9802   0.1819
  -9.000  -0.9983   0.01949   0.01188   0.0004   0.9594   0.1902
  -8.750  -0.9512   0.01898   0.01129  -0.0041   0.9468   0.1980
  -8.500  -0.9082   0.01845   0.01073  -0.0079   0.9353   0.2069
  -8.250  -0.8721   0.01804   0.01030  -0.0102   0.9235   0.2176
  -8.000  -0.8415   0.01769   0.00992  -0.0111   0.9113   0.2285
  -7.750  -0.8159   0.01731   0.00957  -0.0110   0.8981   0.2361
  -7.500  -0.7925   0.01697   0.00922  -0.0102   0.8834   0.2426
  -7.250  -0.7696   0.01666   0.00886  -0.0092   0.8668   0.2489
  -7.000  -0.7482   0.01627   0.00851  -0.0080   0.8481   0.2562
  -6.750  -0.7250   0.01596   0.00817  -0.0070   0.8283   0.2647
  -6.500  -0.7019   0.01564   0.00783  -0.0059   0.8084   0.2733
  -6.250  -0.6777   0.01538   0.00750  -0.0051   0.7897   0.2844
  -6.000  -0.6538   0.01511   0.00721  -0.0042   0.7720   0.2959
  -5.750  -0.6289   0.01489   0.00695  -0.0035   0.7558   0.3084
  -5.500  -0.6033   0.01471   0.00670  -0.0029   0.7420   0.3213
  -5.250  -0.5774   0.01452   0.00649  -0.0024   0.7287   0.3332
  -5.000  -0.5510   0.01439   0.00628  -0.0020   0.7168   0.3454
  -4.750  -0.5255   0.01425   0.00612  -0.0013   0.7048   0.3578
  -4.500  -0.4991   0.01413   0.00595  -0.0008   0.6946   0.3687
  -4.250  -0.4728   0.01402   0.00581  -0.0004   0.6843   0.3794
  -3.750  -0.4195   0.01381   0.00555   0.0005   0.6659   0.3982
  -3.500  -0.3925   0.01375   0.00541   0.0009   0.6563   0.4077
  -3.250  -0.3662   0.01365   0.00532   0.0014   0.6473   0.4172
  -3.000  -0.3392   0.01359   0.00522   0.0018   0.6375   0.4269
  -2.750  -0.3127   0.01352   0.00514   0.0024   0.6291   0.4353
  -2.500  -0.2855   0.01345   0.00508   0.0027   0.6205   0.4442
  -2.250  -0.2584   0.01340   0.00501   0.0031   0.6114   0.4526
  -2.000  -0.2316   0.01337   0.00496   0.0036   0.6031   0.4621
  -1.750  -0.2041   0.01332   0.00491   0.0039   0.5933   0.4714
  -1.500  -0.1772   0.01329   0.00488   0.0044   0.5840   0.4799
  -1.250  -0.1496   0.01327   0.00485   0.0047   0.5754   0.4891
  -1.000  -0.1223   0.01325   0.00484   0.0050   0.5663   0.4977
  -0.750  -0.0951   0.01326   0.00482   0.0054   0.5583   0.5077
  -0.500  -0.0677   0.01325   0.00485   0.0058   0.5491   0.5189
  -0.250  -0.0408   0.01328   0.00486   0.0062   0.5398   0.5311
   0.000  -0.0136   0.01330   0.00488   0.0066   0.5308   0.5417
   0.250   0.0138   0.01331   0.00489   0.0070   0.5199   0.5507
   0.500   0.0412   0.01336   0.00485   0.0073   0.5088   0.5591
   0.750   0.0686   0.01335   0.00486   0.0077   0.4961   0.5660
   1.000   0.0962   0.01338   0.00487   0.0080   0.4857   0.5737
   1.250   0.1241   0.01344   0.00488   0.0082   0.4760   0.5811
   1.500   0.1519   0.01348   0.00491   0.0084   0.4681   0.5880
   1.750   0.1803   0.01350   0.00498   0.0085   0.4594   0.5957
   2.000   0.2082   0.01357   0.00502   0.0087   0.4511   0.6037
   2.250   0.2366   0.01362   0.00509   0.0088   0.4433   0.6104
   2.500   0.2649   0.01365   0.00517   0.0089   0.4349   0.6176
   2.750   0.2928   0.01375   0.00523   0.0090   0.4266   0.6255
   3.000   0.3215   0.01380   0.00534   0.0090   0.4181   0.6332
   3.250   0.3499   0.01386   0.00545   0.0090   0.4094   0.6416
   3.500   0.3781   0.01396   0.00556   0.0091   0.4014   0.6505
   3.750   0.4069   0.01403   0.00570   0.0091   0.3918   0.6588
   4.000   0.4349   0.01415   0.00582   0.0091   0.3823   0.6679
   4.500   0.4921   0.01436   0.00615   0.0090   0.3614   0.6893
   4.750   0.5217   0.01448   0.00634   0.0088   0.3499   0.7018
   5.000   0.5508   0.01463   0.00655   0.0086   0.3380   0.7150
   5.250   0.5799   0.01481   0.00676   0.0083   0.3237   0.7290
   5.500   0.6090   0.01500   0.00701   0.0081   0.3089   0.7453
   5.750   0.6378   0.01523   0.00728   0.0079   0.2947   0.7623
   6.000   0.6658   0.01550   0.00758   0.0078   0.2811   0.7798
   6.250   0.6926   0.01580   0.00792   0.0080   0.2685   0.7987
   6.500   0.7178   0.01611   0.00827   0.0085   0.2580   0.8182
   6.750   0.7412   0.01648   0.00865   0.0093   0.2484   0.8384
   7.000   0.7647   0.01682   0.00902   0.0102   0.2409   0.8580
   7.250   0.7869   0.01721   0.00940   0.0113   0.2332   0.8763
   7.500   0.8090   0.01763   0.00980   0.0122   0.2257   0.8921
   7.750   0.8325   0.01802   0.01019   0.0128   0.2170   0.9056
   8.000   0.8577   0.01846   0.01059   0.0129   0.2088   0.9178
   8.250   0.8887   0.01883   0.01098   0.0118   0.2003   0.9284
   8.500   0.9245   0.01930   0.01144   0.0095   0.1918   0.9374
   8.750   0.9662   0.01972   0.01193   0.0059   0.1831   0.9446
   9.000   1.0105   0.02025   0.01250   0.0017   0.1759   0.9517
   9.250   1.0579   0.02077   0.01311  -0.0030   0.1680   0.9591
   9.750   1.1172   0.02213   0.01453  -0.0051   0.1540   1.0000
  10.000   1.1390   0.02278   0.01518  -0.0047   0.1475   1.0000
  10.250   1.1610   0.02342   0.01585  -0.0043   0.1390   1.0000
  10.500   1.1817   0.02415   0.01660  -0.0039   0.1300   1.0000
  10.750   1.2003   0.02502   0.01746  -0.0033   0.1185   1.0000
  11.000   1.2158   0.02610   0.01849  -0.0025   0.1053   1.0000
  11.250   1.2234   0.02744   0.01976  -0.0008   0.0919   1.0000
  11.500   1.2273   0.02909   0.02137   0.0007   0.0815   1.0000
  11.750   1.2310   0.03104   0.02331   0.0016   0.0740   1.0000
  12.000   1.2346   0.03321   0.02549   0.0020   0.0689   1.0000
  12.250   1.2393   0.03547   0.02781   0.0020   0.0650   1.0000
  12.500   1.2411   0.03819   0.03056   0.0017   0.0618   1.0000
  12.750   1.2447   0.04082   0.03327   0.0013   0.0593   1.0000
  13.000   1.2451   0.04387   0.03639   0.0006   0.0572   1.0000
  13.250   1.2434   0.04723   0.03981  -0.0002   0.0557   1.0000
  13.500   1.2441   0.05035   0.04303  -0.0010   0.0541   1.0000
  13.750   1.2424   0.05380   0.04658  -0.0020   0.0527   1.0000
  14.000   1.2383   0.05759   0.05046  -0.0031   0.0516   1.0000
  14.250   1.2320   0.06172   0.05467  -0.0045   0.0506   1.0000
  14.500   1.2247   0.06604   0.05905  -0.0059   0.0498   1.0000
  14.750   1.2211   0.06995   0.06307  -0.0072   0.0489   1.0000
  15.000   1.2168   0.07409   0.06731  -0.0086   0.0481   1.0000
  15.250   1.2118   0.07838   0.07170  -0.0102   0.0473   1.0000
  15.500   1.2069   0.08274   0.07614  -0.0118   0.0467   1.0000
  15.750   1.2016   0.08722   0.08069  -0.0135   0.0460   1.0000
  16.000   1.1961   0.09172   0.08524  -0.0152   0.0453   1.0000
<< Back to TRAINER60 (trainer60-il)

Polar data table (+)

Polar graphs


<< Back to TRAINER60 (trainer60-il)