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

J5012 12% (j5012-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: J5012 12% (j5012-il)
Reynolds number: 100,000
Max Cl/Cd: 41.4 at α=4.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-j5012-il-100000.txt
Download as CSV file: xf-j5012-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: J5012   12%                                     
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.500  -0.8513   0.06820   0.06220  -0.0471   1.0000   0.0715
 -11.250  -0.8787   0.06620   0.06000  -0.0429   1.0000   0.0711
 -11.000  -0.8927   0.06231   0.05595  -0.0400   1.0000   0.0708
 -10.750  -0.9066   0.05891   0.05234  -0.0367   1.0000   0.0707
 -10.500  -0.9185   0.05554   0.04871  -0.0332   1.0000   0.0707
 -10.250  -0.9255   0.05210   0.04499  -0.0298   1.0000   0.0705
 -10.000  -0.9307   0.04887   0.04143  -0.0262   1.0000   0.0706
  -9.750  -0.9332   0.04596   0.03815  -0.0225   1.0000   0.0708
  -9.500  -0.9320   0.04309   0.03492  -0.0190   1.0000   0.0712
  -9.250  -0.9232   0.03962   0.03125  -0.0169   1.0000   0.0724
  -9.000  -0.9094   0.03769   0.02930  -0.0152   1.0000   0.0751
  -8.750  -0.8967   0.03597   0.02740  -0.0129   1.0000   0.0780
  -8.500  -0.8851   0.03405   0.02514  -0.0103   1.0000   0.0807
  -8.250  -0.8728   0.03235   0.02301  -0.0074   1.0000   0.0832
  -8.000  -0.8519   0.03001   0.02075  -0.0066   1.0000   0.0875
  -7.750  -0.8355   0.02877   0.01938  -0.0046   1.0000   0.0933
  -7.500  -0.8167   0.02715   0.01767  -0.0030   1.0000   0.0997
  -7.250  -0.7993   0.02600   0.01647  -0.0012   1.0000   0.1077
  -7.000  -0.7816   0.02471   0.01526   0.0005   1.0000   0.1172
  -6.750  -0.7649   0.02356   0.01412   0.0025   1.0000   0.1287
  -6.500  -0.7495   0.02251   0.01315   0.0047   1.0000   0.1427
  -6.250  -0.7352   0.02153   0.01226   0.0070   1.0000   0.1598
  -6.000  -0.7215   0.02060   0.01140   0.0096   1.0000   0.1825
  -5.750  -0.7098   0.01961   0.01064   0.0123   1.0000   0.2115
  -5.500  -0.6996   0.01861   0.00999   0.0154   1.0000   0.2491
  -5.250  -0.6899   0.01772   0.00943   0.0185   1.0000   0.3001
  -5.000  -0.6802   0.01695   0.00901   0.0217   1.0000   0.3582
  -4.750  -0.6695   0.01636   0.00873   0.0249   1.0000   0.4185
  -4.500  -0.6576   0.01590   0.00854   0.0280   1.0000   0.4764
  -4.250  -0.6446   0.01557   0.00843   0.0310   1.0000   0.5309
  -4.000  -0.6307   0.01534   0.00836   0.0340   1.0000   0.5821
  -3.750  -0.6157   0.01519   0.00837   0.0368   1.0000   0.6291
  -3.500  -0.5996   0.01512   0.00846   0.0396   1.0000   0.6725
  -3.250  -0.5825   0.01514   0.00859   0.0422   1.0000   0.7133
  -3.000  -0.5652   0.01522   0.00874   0.0448   1.0000   0.7518
  -2.750  -0.5457   0.01540   0.00895   0.0472   1.0000   0.7872
  -2.500  -0.5233   0.01569   0.00927   0.0490   1.0000   0.8205
  -2.250  -0.4965   0.01611   0.00968   0.0500   1.0000   0.8517
  -2.000  -0.4638   0.01665   0.01016   0.0497   1.0000   0.8800
  -1.750  -0.4147   0.01741   0.01083   0.0463   1.0000   0.9014
  -1.500  -0.3596   0.01817   0.01147   0.0415   1.0000   0.9193
  -1.250  -0.2956   0.01887   0.01206   0.0346   1.0000   0.9329
  -1.000  -0.2364   0.01940   0.01249   0.0283   1.0000   0.9469
  -0.750  -0.1790   0.01979   0.01281   0.0220   1.0000   0.9610
  -0.500  -0.1213   0.02007   0.01304   0.0153   1.0000   0.9746
  -0.250  -0.0623   0.02024   0.01319   0.0081   1.0000   0.9876
   0.000   0.0000   0.02036   0.01329   0.0000   1.0000   1.0000
   0.250   0.0622   0.02024   0.01318  -0.0081   0.9876   1.0000
   0.500   0.1212   0.02007   0.01304  -0.0153   0.9746   1.0000
   0.750   0.1790   0.01979   0.01281  -0.0220   0.9610   1.0000
   1.000   0.2359   0.01940   0.01249  -0.0282   0.9470   1.0000
   1.250   0.2953   0.01888   0.01206  -0.0346   0.9330   1.0000
   1.500   0.3595   0.01817   0.01147  -0.0415   0.9194   1.0000
   1.750   0.4146   0.01741   0.01083  -0.0463   0.9014   1.0000
   2.000   0.4639   0.01664   0.01015  -0.0498   0.8799   1.0000
   2.250   0.4965   0.01610   0.00968  -0.0500   0.8516   1.0000
   2.500   0.5233   0.01569   0.00927  -0.0490   0.8206   1.0000
   2.750   0.5457   0.01540   0.00896  -0.0472   0.7876   1.0000
   3.000   0.5652   0.01522   0.00872  -0.0449   0.7520   1.0000
   3.250   0.5824   0.01514   0.00859  -0.0422   0.7132   1.0000
   3.500   0.5996   0.01512   0.00845  -0.0396   0.6727   1.0000
   3.750   0.6157   0.01519   0.00837  -0.0368   0.6293   1.0000
   4.000   0.6306   0.01533   0.00837  -0.0340   0.5819   1.0000
   4.250   0.6446   0.01557   0.00843  -0.0310   0.5308   1.0000
   4.500   0.6576   0.01590   0.00853  -0.0280   0.4767   1.0000
   4.750   0.6695   0.01635   0.00872  -0.0249   0.4185   1.0000
   5.000   0.6802   0.01695   0.00901  -0.0217   0.3581   1.0000
   5.250   0.6899   0.01773   0.00943  -0.0185   0.3001   1.0000
   5.500   0.6996   0.01862   0.00999  -0.0154   0.2490   1.0000
   5.750   0.7098   0.01961   0.01064  -0.0123   0.2118   1.0000
   6.000   0.7216   0.02059   0.01140  -0.0096   0.1827   1.0000
   6.250   0.7352   0.02152   0.01225  -0.0070   0.1598   1.0000
   6.500   0.7494   0.02251   0.01314  -0.0047   0.1425   1.0000
   6.750   0.7649   0.02354   0.01411  -0.0025   0.1287   1.0000
   7.000   0.7815   0.02470   0.01525  -0.0005   0.1171   1.0000
   7.250   0.7992   0.02600   0.01647   0.0012   0.1076   1.0000
   7.500   0.8167   0.02715   0.01768   0.0030   0.0996   1.0000
   7.750   0.8354   0.02877   0.01939   0.0046   0.0932   1.0000
   8.000   0.8517   0.02998   0.02071   0.0066   0.0872   1.0000
   8.250   0.8726   0.03234   0.02301   0.0075   0.0831   1.0000
   8.500   0.8853   0.03406   0.02515   0.0102   0.0808   1.0000
   8.750   0.8967   0.03594   0.02736   0.0130   0.0779   1.0000
   9.000   0.9099   0.03760   0.02918   0.0151   0.0748   1.0000
   9.250   0.9234   0.03962   0.03124   0.0169   0.0723   1.0000
   9.500   0.9315   0.04333   0.03514   0.0190   0.0710   1.0000
   9.750   0.9318   0.04589   0.03811   0.0227   0.0706   1.0000
  10.000   0.9301   0.04884   0.04142   0.0263   0.0705   1.0000
  10.250   0.9253   0.05210   0.04499   0.0298   0.0705   1.0000
  10.500   0.9179   0.05548   0.04866   0.0333   0.0706   1.0000
  10.750   0.9082   0.05915   0.05256   0.0365   0.0708   1.0000
  11.000   0.8963   0.06290   0.05650   0.0395   0.0710   1.0000
  11.250   0.8001   0.06691   0.06120   0.0474   0.0756   1.0000
  11.500   0.7484   0.07439   0.06887   0.0453   0.0779   1.0000
  11.750   0.7069   0.08359   0.07813   0.0398   0.0803   1.0000
  12.000   0.6937   0.09037   0.08491   0.0371   0.0822   1.0000
<< Back to J5012 12% (j5012-il)

Polar data table (+)

Polar graphs


<< Back to J5012 12% (j5012-il)