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

CH10 (smoothed) (ch10sm-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: CH10 (smoothed) (ch10sm-il)
Reynolds number: 500,000
Max Cl/Cd: 132.36 at α=3.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-ch10sm-il-500000-n5.txt
Download as CSV file: xf-ch10sm-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: CH10 (smoothed)                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750   0.2748   0.09398   0.09018  -0.1585   0.7621   0.0140
  -9.500   0.2843   0.09155   0.08774  -0.1598   0.7582   0.0145
  -9.000   0.2978   0.08511   0.08126  -0.1628   0.7513   0.0121
  -8.750   0.3086   0.08303   0.07918  -0.1637   0.7476   0.0119
  -8.500   0.3183   0.08070   0.07685  -0.1649   0.7436   0.0118
  -8.250   0.3272   0.07817   0.07430  -0.1662   0.7399   0.0118
  -8.000   0.3356   0.07550   0.07160  -0.1676   0.7365   0.0120
  -7.750   0.3432   0.07255   0.06867  -0.1693   0.7331   0.0121
  -7.500   0.3508   0.06975   0.06588  -0.1708   0.7294   0.0124
  -7.250   0.3644   0.06855   0.06467  -0.1715   0.7258   0.0127
  -7.000   0.3764   0.06701   0.06310  -0.1723   0.7223   0.0131
  -6.750   0.3865   0.06511   0.06121  -0.1733   0.7188   0.0138
  -6.500   0.3949   0.06296   0.05908  -0.1746   0.7152   0.0141
  -5.500   0.5736   0.01728   0.01211  -0.2613   0.7021   0.0173
  -5.250   0.6107   0.01528   0.00964  -0.2652   0.6988   0.0180
  -5.000   0.6429   0.01431   0.00835  -0.2670   0.6957   0.0187
  -4.750   0.6733   0.01369   0.00754  -0.2682   0.6927   0.0194
  -4.500   0.7023   0.01339   0.00716  -0.2689   0.6898   0.0201
  -4.250   0.7315   0.01301   0.00669  -0.2696   0.6866   0.0207
  -4.000   0.7607   0.01264   0.00619  -0.2702   0.6834   0.0215
  -3.750   0.7898   0.01231   0.00574  -0.2708   0.6803   0.0223
  -3.500   0.8187   0.01204   0.00534  -0.2713   0.6772   0.0231
  -3.250   0.8474   0.01183   0.00508  -0.2718   0.6744   0.0242
  -3.000   0.8756   0.01170   0.00492  -0.2721   0.6712   0.0257
  -2.750   0.9038   0.01157   0.00472  -0.2724   0.6681   0.0274
  -2.500   0.9322   0.01142   0.00453  -0.2728   0.6649   0.0292
  -2.250   0.9601   0.01136   0.00441  -0.2730   0.6619   0.0313
  -2.000   0.9883   0.01128   0.00428  -0.2733   0.6590   0.0338
  -1.750   1.0161   0.01123   0.00423  -0.2736   0.6560   0.0372
  -1.500   1.0438   0.01119   0.00417  -0.2738   0.6529   0.0410
  -1.250   1.0712   0.01117   0.00413  -0.2739   0.6496   0.0451
  -1.000   1.0983   0.01118   0.00409  -0.2740   0.6466   0.0496
  -0.750   1.1255   0.01119   0.00410  -0.2741   0.6437   0.0554
  -0.500   1.1527   0.01118   0.00409  -0.2742   0.6407   0.0612
  -0.250   1.1796   0.01119   0.00411  -0.2742   0.6374   0.0682
   0.000   1.2062   0.01122   0.00413  -0.2742   0.6341   0.0766
   0.250   1.2326   0.01127   0.00416  -0.2742   0.6310   0.0869
   0.500   1.2593   0.01130   0.00422  -0.2742   0.6281   0.1036
   1.000   1.3124   0.01129   0.00442  -0.2744   0.6214   0.1969
   1.250   1.3385   0.01132   0.00454  -0.2744   0.6180   0.2572
   1.500   1.3643   0.01138   0.00468  -0.2743   0.6149   0.3175
   1.750   1.3900   0.01143   0.00484  -0.2742   0.6117   0.3741
   2.000   1.4154   0.01148   0.00501  -0.2740   0.6082   0.4300
   2.250   1.4402   0.01156   0.00518  -0.2738   0.6046   0.4865
   2.500   1.4647   0.01164   0.00537  -0.2734   0.6012   0.5606
   2.750   1.4891   0.01165   0.00560  -0.2731   0.5980   0.6755
   3.000   1.5099   0.01141   0.00575  -0.2718   0.5946   1.0000
   3.250   1.5327   0.01158   0.00591  -0.2711   0.5907   1.0000
   3.500   1.5550   0.01178   0.00608  -0.2703   0.5869   1.0000
   4.000   1.5992   0.01220   0.00647  -0.2686   0.5798   1.0000
   4.250   1.6207   0.01242   0.00668  -0.2677   0.5757   1.0000
   4.500   1.6412   0.01267   0.00692  -0.2666   0.5715   1.0000
   4.750   1.6613   0.01295   0.00718  -0.2654   0.5677   1.0000
   5.000   1.6820   0.01319   0.00745  -0.2644   0.5635   1.0000
   5.250   1.7015   0.01348   0.00775  -0.2632   0.5589   1.0000
   5.500   1.7199   0.01382   0.00807  -0.2618   0.5544   1.0000
   5.750   1.7389   0.01415   0.00842  -0.2605   0.5501   1.0000
   6.000   1.7576   0.01449   0.00879  -0.2592   0.5452   1.0000
   6.250   1.7747   0.01490   0.00920  -0.2576   0.5403   1.0000
   6.500   1.7921   0.01532   0.00963  -0.2562   0.5358   1.0000
   6.750   1.8097   0.01574   0.01009  -0.2548   0.5306   1.0000
   7.000   1.8252   0.01625   0.01061  -0.2530   0.5251   1.0000
   7.250   1.8411   0.01677   0.01115  -0.2514   0.5200   1.0000
   7.500   1.8570   0.01730   0.01173  -0.2498   0.5142   1.0000
   7.750   1.8707   0.01794   0.01238  -0.2479   0.5085   1.0000
   8.000   1.8858   0.01855   0.01302  -0.2462   0.5031   1.0000
   8.250   1.9000   0.01921   0.01372  -0.2444   0.4971   1.0000
   8.500   1.9116   0.02002   0.01453  -0.2423   0.4913   1.0000
   8.750   1.9261   0.02070   0.01529  -0.2407   0.4853   1.0000
   9.000   1.9370   0.02159   0.01620  -0.2385   0.4790   1.0000
   9.250   1.9488   0.02246   0.01711  -0.2366   0.4729   1.0000
   9.500   1.9594   0.02341   0.01810  -0.2345   0.4659   1.0000
   9.750   1.9681   0.02449   0.01922  -0.2322   0.4594   1.0000
  10.000   1.9749   0.02573   0.02048  -0.2297   0.4496   1.0000
  10.250   1.9764   0.02738   0.02213  -0.2266   0.4363   1.0000
  10.500   1.9733   0.02943   0.02414  -0.2230   0.4200   1.0000
  10.750   1.9680   0.03173   0.02639  -0.2193   0.4029   1.0000
  11.000   1.9627   0.03415   0.02877  -0.2158   0.3864   1.0000
  11.500   1.9507   0.03940   0.03394  -0.2091   0.3527   1.0000
  11.750   1.9423   0.04235   0.03684  -0.2058   0.3341   1.0000
  12.000   1.9329   0.04550   0.03993  -0.2025   0.3156   1.0000
  12.250   1.9232   0.04875   0.04313  -0.1993   0.2979   1.0000
  12.500   1.9126   0.05216   0.04648  -0.1962   0.2804   1.0000
  12.750   1.9026   0.05559   0.04986  -0.1933   0.2625   1.0000
  13.000   1.8918   0.05919   0.05340  -0.1905   0.2434   1.0000
  13.250   1.8788   0.06308   0.05720  -0.1877   0.2235   1.0000
  13.500   1.8652   0.06711   0.06117  -0.1850   0.2034   1.0000
  13.750   1.8504   0.07136   0.06533  -0.1824   0.1815   1.0000
  14.000   1.8350   0.07578   0.06964  -0.1799   0.1587   1.0000
  14.250   1.8181   0.08041   0.07416  -0.1776   0.1352   1.0000
  14.500   1.8023   0.08500   0.07864  -0.1754   0.1124   1.0000
  14.750   1.7845   0.08994   0.08346  -0.1734   0.0883   1.0000
<< Back to CH10 (smoothed) (ch10sm-il)

Polar data table (+)

Polar graphs


<< Back to CH10 (smoothed) (ch10sm-il)