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GOE 142 (MVA H.19) AIRFOIL (goe142-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 142 (MVA H.19) AIRFOIL (goe142-il)
Reynolds number: 1,000,000
Max Cl/Cd: 118.2 at α=5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe142-il-1000000.txt
Download as CSV file: xf-goe142-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 142 (MVA H.19) AIRFOIL                      
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.4305   0.11116   0.10953  -0.0019   1.0000   0.0076
  -9.000  -0.4244   0.10770   0.10608  -0.0035   1.0000   0.0076
  -8.750  -0.4227   0.10316   0.10156  -0.0043   1.0000   0.0078
  -8.500  -0.4158   0.10021   0.09861  -0.0054   1.0000   0.0079
  -8.250  -0.4089   0.09724   0.09566  -0.0068   1.0000   0.0081
  -8.000  -0.4021   0.09427   0.09270  -0.0083   1.0000   0.0082
  -7.750  -0.3954   0.09131   0.08976  -0.0098   1.0000   0.0084
  -7.500  -0.3893   0.08834   0.08681  -0.0115   1.0000   0.0086
  -7.250  -0.3830   0.08529   0.08378  -0.0135   1.0000   0.0089
  -7.000  -0.3727   0.08184   0.08034  -0.0168   1.0000   0.0093
  -6.750  -0.3617   0.07809   0.07660  -0.0206   1.0000   0.0103
  -6.500  -0.3511   0.07430   0.07283  -0.0254   1.0000   0.0109
  -6.250  -0.3306   0.06976   0.06827  -0.0312   0.9983   0.0109
  -6.000  -0.2968   0.06409   0.06255  -0.0400   0.9955   0.0110
  -5.750  -0.2658   0.05612   0.05452  -0.0501   0.9915   0.0114
  -5.500  -0.2356   0.05292   0.05126  -0.0548   0.9882   0.0118
  -5.250  -0.2032   0.04982   0.04811  -0.0597   0.9846   0.0124
  -5.000  -0.1706   0.04600   0.04422  -0.0646   0.9777   0.0135
  -4.750  -0.1292   0.04141   0.03947  -0.0701   0.9710   0.0153
  -4.500  -0.0907   0.01322   0.00941  -0.0805   0.9603   0.0118
  -4.250  -0.0641   0.01214   0.00811  -0.0803   0.9513   0.0123
  -4.000  -0.0380   0.01128   0.00705  -0.0798   0.9413   0.0128
  -3.750  -0.0119   0.01086   0.00653  -0.0792   0.9299   0.0136
  -3.500   0.0146   0.01025   0.00577  -0.0787   0.9184   0.0146
  -3.250   0.0414   0.00971   0.00508  -0.0783   0.9066   0.0153
  -3.000   0.0680   0.00873   0.00386  -0.0778   0.8942   0.0161
  -2.750   0.0949   0.00807   0.00307  -0.0774   0.8809   0.0175
  -2.500   0.1220   0.00786   0.00279  -0.0771   0.8665   0.0189
  -2.250   0.1493   0.00772   0.00258  -0.0768   0.8509   0.0208
  -2.000   0.1767   0.00761   0.00238  -0.0764   0.8335   0.0222
  -1.750   0.2040   0.00720   0.00185  -0.0762   0.8154   0.0263
  -1.500   0.2315   0.00713   0.00171  -0.0759   0.7960   0.0293
  -1.250   0.2591   0.00702   0.00149  -0.0757   0.7750   0.0324
  -1.000   0.2867   0.00694   0.00135  -0.0755   0.7536   0.0385
  -0.750   0.3142   0.00697   0.00128  -0.0753   0.7310   0.0417
  -0.500   0.3419   0.00688   0.00113  -0.0752   0.7080   0.0505
  -0.250   0.3695   0.00690   0.00105  -0.0750   0.6844   0.0563
   0.000   0.3972   0.00691   0.00099  -0.0749   0.6606   0.0672
   0.250   0.4248   0.00693   0.00096  -0.0748   0.6357   0.0810
   0.500   0.4524   0.00696   0.00094  -0.0747   0.6117   0.0971
   0.750   0.4800   0.00698   0.00095  -0.0746   0.5869   0.1304
   1.000   0.5076   0.00687   0.00099  -0.0747   0.5623   0.2294
   1.250   0.5301   0.00522   0.00111  -0.0740   0.5394   1.0000
   1.500   0.5576   0.00539   0.00114  -0.0739   0.5156   1.0000
   1.750   0.5852   0.00555   0.00118  -0.0738   0.4920   1.0000
   2.000   0.6127   0.00571   0.00123  -0.0737   0.4708   1.0000
   2.250   0.6402   0.00588   0.00129  -0.0736   0.4493   1.0000
   2.500   0.6676   0.00606   0.00136  -0.0735   0.4287   1.0000
   2.750   0.6951   0.00622   0.00145  -0.0734   0.4099   1.0000
   3.000   0.7224   0.00640   0.00154  -0.0733   0.3915   1.0000
   3.250   0.7497   0.00659   0.00163  -0.0733   0.3730   1.0000
   3.500   0.7771   0.00676   0.00174  -0.0732   0.3561   1.0000
   3.750   0.8044   0.00695   0.00186  -0.0731   0.3402   1.0000
   4.000   0.8315   0.00714   0.00199  -0.0730   0.3237   1.0000
   4.250   0.8587   0.00734   0.00213  -0.0729   0.3087   1.0000
   4.500   0.8857   0.00753   0.00227  -0.0728   0.2945   1.0000
   4.750   0.9127   0.00774   0.00244  -0.0727   0.2797   1.0000
   5.000   0.9397   0.00795   0.00260  -0.0726   0.2664   1.0000
   5.250   0.9662   0.00821   0.00279  -0.0724   0.2488   1.0000
   5.500   0.9927   0.00848   0.00298  -0.0723   0.2295   1.0000
   5.750   1.0191   0.00873   0.00320  -0.0721   0.2147   1.0000
   6.000   1.0453   0.00903   0.00342  -0.0719   0.1973   1.0000
   6.250   1.0714   0.00932   0.00366  -0.0718   0.1817   1.0000
   6.500   1.0975   0.00962   0.00390  -0.0716   0.1676   1.0000
   6.750   1.1232   0.00996   0.00419  -0.0713   0.1509   1.0000
   7.000   1.1484   0.01036   0.00451  -0.0710   0.1306   1.0000
   7.250   1.1729   0.01087   0.00490  -0.0707   0.1054   1.0000
   7.500   1.1956   0.01163   0.00544  -0.0701   0.0700   1.0000
   7.750   1.2175   0.01252   0.00613  -0.0694   0.0381   1.0000
   8.000   1.2403   0.01325   0.00678  -0.0688   0.0235   1.0000
   8.250   1.2642   0.01378   0.00733  -0.0683   0.0188   1.0000
   8.500   1.2870   0.01449   0.00808  -0.0675   0.0148   1.0000
   8.750   1.3111   0.01494   0.00858  -0.0671   0.0134   1.0000
   9.000   1.3341   0.01554   0.00920  -0.0665   0.0116   1.0000
   9.250   1.3540   0.01657   0.01038  -0.0653   0.0100   1.0000
   9.500   1.3770   0.01709   0.01096  -0.0647   0.0095   1.0000
   9.750   1.3990   0.01770   0.01164  -0.0640   0.0088   1.0000
  10.000   1.4207   0.01832   0.01231  -0.0633   0.0081   1.0000
  10.250   1.4412   0.01905   0.01309  -0.0624   0.0075   1.0000
  10.500   1.4561   0.02040   0.01458  -0.0607   0.0068   1.0000
  10.750   1.4687   0.02189   0.01623  -0.0588   0.0065   1.0000
  11.000   1.4875   0.02261   0.01705  -0.0577   0.0063   1.0000
  11.250   1.5045   0.02347   0.01799  -0.0564   0.0060   1.0000
  11.500   1.5194   0.02446   0.01908  -0.0549   0.0058   1.0000
  11.750   1.5327   0.02551   0.02024  -0.0532   0.0055   1.0000
  12.000   1.5440   0.02659   0.02142  -0.0513   0.0052   1.0000
  12.250   1.5504   0.02774   0.02265  -0.0486   0.0050   1.0000
  12.500   1.5556   0.02900   0.02401  -0.0460   0.0049   1.0000
  12.750   1.5586   0.03052   0.02563  -0.0436   0.0047   1.0000
  13.000   1.5577   0.03250   0.02772  -0.0414   0.0046   1.0000
  13.250   1.5525   0.03509   0.03046  -0.0394   0.0044   1.0000
  13.500   1.5417   0.03858   0.03411  -0.0380   0.0043   1.0000
  13.750   1.5249   0.04321   0.03894  -0.0374   0.0042   1.0000
  14.000   1.5055   0.04869   0.04463  -0.0378   0.0041   1.0000
  14.250   1.4868   0.05454   0.05068  -0.0391   0.0041   1.0000
  14.500   1.4792   0.05919   0.05549  -0.0406   0.0041   1.0000
  14.750   1.4734   0.06379   0.06022  -0.0425   0.0040   1.0000
  15.000   1.4626   0.06927   0.06584  -0.0447   0.0040   1.0000
  15.250   1.4485   0.07541   0.07212  -0.0472   0.0040   1.0000
  15.500   1.4361   0.08143   0.07827  -0.0499   0.0040   1.0000
  15.750   1.4197   0.08828   0.08526  -0.0529   0.0040   1.0000
  16.000   1.4033   0.09530   0.09241  -0.0561   0.0039   1.0000
  16.250   1.3854   0.10271   0.09994  -0.0595   0.0039   1.0000
  16.500   1.3671   0.11041   0.10777  -0.0631   0.0040   1.0000
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