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TRAINER60 (trainer60-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: TRAINER60 (trainer60-il)
Reynolds number: 50,000
Max Cl/Cd: 24.51 at α=7.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-trainer60-il-50000-n5.txt
Download as CSV file: xf-trainer60-il-50000-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 =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -13.500  -0.7776   0.10770   0.09913   0.0001   1.0000   0.1582
 -13.250  -0.8174   0.09670   0.08810  -0.0051   1.0000   0.1686
 -13.000  -0.9330   0.07445   0.06558  -0.0162   1.0000   0.1786
 -12.750  -0.8626   0.08235   0.07365  -0.0112   1.0000   0.1858
 -12.500  -0.9523   0.06600   0.05700  -0.0188   1.0000   0.1931
 -12.250  -0.9479   0.06381   0.05480  -0.0190   1.0000   0.2005
 -12.000  -0.9612   0.05951   0.05039  -0.0201   1.0000   0.2078
 -11.750  -1.0008   0.05277   0.04336  -0.0215   1.0000   0.2134
 -11.500  -0.9667   0.05399   0.04476  -0.0202   1.0000   0.2225
 -11.250  -0.9955   0.04915   0.03967  -0.0199   1.0000   0.2287
 -11.000  -0.9729   0.04912   0.03977  -0.0190   1.0000   0.2371
 -10.750  -0.9822   0.04664   0.03717  -0.0173   1.0000   0.2445
 -10.500  -0.9790   0.04518   0.03568  -0.0155   1.0000   0.2519
 -10.250  -0.9647   0.04449   0.03500  -0.0142   1.0000   0.2601
 -10.000  -0.9715   0.04211   0.03241  -0.0120   1.0000   0.2677
  -9.750  -0.9426   0.04220   0.03264  -0.0115   1.0000   0.2751
  -9.500  -0.9396   0.04038   0.03064  -0.0098   1.0000   0.2829
  -9.250  -0.9213   0.03950   0.02975  -0.0088   1.0000   0.2894
  -9.000  -0.9022   0.03873   0.02898  -0.0079   1.0000   0.2963
  -8.750  -0.8977   0.03689   0.02689  -0.0062   1.0000   0.3043
  -8.500  -0.8712   0.03654   0.02667  -0.0057   1.0000   0.3103
  -8.250  -0.8542   0.03561   0.02568  -0.0046   1.0000   0.3177
  -8.000  -0.8412   0.03438   0.02434  -0.0033   1.0000   0.3258
  -7.750  -0.8179   0.03394   0.02398  -0.0025   1.0000   0.3326
  -7.500  -0.8047   0.03284   0.02277  -0.0011   1.0000   0.3417
  -7.250  -0.7841   0.03231   0.02230  -0.0001   1.0000   0.3493
  -7.000  -0.7674   0.03167   0.02165   0.0013   1.0000   0.3582
  -6.750  -0.7534   0.03094   0.02092   0.0030   1.0000   0.3675
  -6.500  -0.7371   0.03059   0.02065   0.0047   1.0000   0.3759
  -6.250  -0.7302   0.02988   0.01987   0.0071   1.0000   0.3862
  -6.000  -0.7089   0.02963   0.01974   0.0077   0.9807   0.3949
  -5.750  -0.6615   0.02909   0.01910   0.0034   0.9675   0.4099
  -5.500  -0.6123   0.02870   0.01862  -0.0010   0.9552   0.4249
  -5.250  -0.5626   0.02861   0.01855  -0.0050   0.9418   0.4378
  -5.000  -0.5202   0.02832   0.01815  -0.0081   0.9264   0.4522
  -4.750  -0.4812   0.02834   0.01812  -0.0101   0.9102   0.4648
  -4.500  -0.4542   0.02835   0.01810  -0.0099   0.8901   0.4760
  -4.250  -0.4296   0.02829   0.01796  -0.0093   0.8711   0.4880
  -4.000  -0.4044   0.02826   0.01792  -0.0086   0.8537   0.4981
  -3.750  -0.3815   0.02814   0.01773  -0.0076   0.8370   0.5099
  -3.500  -0.3568   0.02808   0.01765  -0.0066   0.8215   0.5201
  -3.250  -0.3329   0.02794   0.01743  -0.0057   0.8079   0.5319
  -3.000  -0.3082   0.02785   0.01730  -0.0047   0.7943   0.5422
  -2.750  -0.2849   0.02775   0.01715  -0.0036   0.7806   0.5540
  -2.500  -0.2595   0.02764   0.01698  -0.0025   0.7694   0.5649
  -2.250  -0.2365   0.02760   0.01693  -0.0014   0.7557   0.5768
  -2.000  -0.2110   0.02748   0.01675  -0.0004   0.7455   0.5880
  -1.750  -0.1874   0.02747   0.01674   0.0006   0.7322   0.5992
  -1.500  -0.1623   0.02728   0.01647   0.0015   0.7228   0.6099
  -1.250  -0.1377   0.02731   0.01653   0.0023   0.7100   0.6190
  -1.000  -0.1140   0.02708   0.01618   0.0032   0.7005   0.6306
  -0.750  -0.0878   0.02716   0.01634   0.0037   0.6885   0.6384
  -0.500  -0.0623   0.02705   0.01617   0.0044   0.6788   0.6489
  -0.250  -0.0364   0.02707   0.01620   0.0048   0.6685   0.6583
   0.000  -0.0099   0.02711   0.01626   0.0053   0.6581   0.6678
   0.250   0.0158   0.02703   0.01610   0.0058   0.6497   0.6787
   0.500   0.0418   0.02721   0.01639   0.0062   0.6383   0.6874
   0.750   0.0674   0.02717   0.01628   0.0069   0.6302   0.6990
   1.000   0.0926   0.02737   0.01658   0.0074   0.6198   0.7081
   1.250   0.1175   0.02744   0.01665   0.0081   0.6102   0.7193
   1.500   0.1441   0.02748   0.01669   0.0087   0.6022   0.7296
   1.750   0.1672   0.02769   0.01700   0.0095   0.5904   0.7410
   2.000   0.1945   0.02758   0.01684   0.0103   0.5815   0.7523
   2.250   0.2169   0.02778   0.01714   0.0112   0.5681   0.7642
   2.500   0.2447   0.02761   0.01693   0.0120   0.5586   0.7760
   2.750   0.2666   0.02782   0.01724   0.0129   0.5452   0.7895
   3.000   0.2954   0.02767   0.01707   0.0136   0.5361   0.8015
   3.250   0.3175   0.02793   0.01744   0.0144   0.5232   0.8158
   3.500   0.3458   0.02780   0.01728   0.0151   0.5142   0.8304
   3.750   0.3697   0.02808   0.01769   0.0156   0.5015   0.8457
   4.000   0.3985   0.02794   0.01751   0.0161   0.4922   0.8625
   4.250   0.4211   0.02820   0.01788   0.0166   0.4794   0.8825
   4.500   0.4525   0.02797   0.01759   0.0165   0.4697   0.9025
   4.750   0.4826   0.02821   0.01798   0.0154   0.4556   0.9242
   5.000   0.5288   0.02820   0.01799   0.0118   0.4425   0.9414
   5.250   0.5842   0.02834   0.01820   0.0064   0.4273   0.9530
   5.500   0.6384   0.02885   0.01884   0.0008   0.4103   0.9625
   6.000   0.7108   0.02969   0.01965  -0.0036   0.3849   1.0000
   6.250   0.7227   0.03033   0.02032  -0.0019   0.3739   1.0000
   6.500   0.7412   0.03067   0.02057  -0.0006   0.3646   1.0000
   6.750   0.7569   0.03145   0.02139   0.0007   0.3541   1.0000
   7.000   0.7770   0.03197   0.02186   0.0017   0.3451   1.0000
   7.250   0.7952   0.03279   0.02269   0.0026   0.3362   1.0000
   7.500   0.8138   0.03360   0.02354   0.0035   0.3273   1.0000
   7.750   0.8367   0.03414   0.02399   0.0042   0.3201   1.0000
   8.000   0.8510   0.03544   0.02544   0.0052   0.3112   1.0000
   8.250   0.8744   0.03599   0.02594   0.0058   0.3045   1.0000
   8.500   0.8901   0.03728   0.02733   0.0066   0.2972   1.0000
   8.750   0.9063   0.03847   0.02861   0.0074   0.2899   1.0000
   9.000   0.9330   0.03886   0.02890   0.0078   0.2841   1.0000
   9.250   0.9399   0.04085   0.03112   0.0089   0.2768   1.0000
   9.500   0.9563   0.04196   0.03228   0.0097   0.2699   1.0000
   9.750   0.9784   0.04255   0.03281   0.0103   0.2628   1.0000
  10.000   0.9797   0.04456   0.03500   0.0117   0.2541   1.0000
  10.250   1.0043   0.04452   0.03481   0.0124   0.2451   1.0000
  10.500   0.9966   0.04706   0.03755   0.0141   0.2367   1.0000
  10.750   1.0188   0.04707   0.03737   0.0150   0.2274   1.0000
  11.000   1.0006   0.05062   0.04117   0.0161   0.2207   1.0000
  11.250   1.0245   0.05057   0.04095   0.0169   0.2119   1.0000
  11.500   1.0027   0.05522   0.04586   0.0165   0.2058   1.0000
  11.750   0.9999   0.05819   0.04894   0.0161   0.1985   1.0000
  12.000   1.0025   0.06070   0.05147   0.0157   0.1914   1.0000
  12.250   0.9719   0.06777   0.05879   0.0130   0.1849   1.0000
  12.500   0.9947   0.06759   0.05849   0.0138   0.1770   1.0000
  12.750   0.9185   0.08244   0.07375   0.0066   0.1707   1.0000
  13.000   0.9755   0.07662   0.06770   0.0103   0.1629   1.0000
  13.250   0.8479   0.10203   0.09353  -0.0027   0.1536   1.0000
  13.500   0.9314   0.09050   0.08182   0.0040   0.1490   1.0000
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