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MH 38 9.68% (mh38-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: MH 38 9.68% (mh38-il)
Reynolds number: 1,000,000
Max Cl/Cd: 149.65 at α=4.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-mh38-il-1000000.txt
Download as CSV file: xf-mh38-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: MH 38  9.68%                                    
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -13.500  -0.3104   0.14522   0.14369  -0.0194   1.0000   0.0062
 -13.250  -0.3049   0.14214   0.14061  -0.0209   1.0000   0.0064
  -7.250  -0.3437   0.02465   0.02153  -0.0933   0.8239   0.0046
  -7.000  -0.3259   0.02154   0.01808  -0.0936   0.8151   0.0041
  -6.750  -0.3082   0.01745   0.01337  -0.0937   0.8066   0.0038
  -6.500  -0.2853   0.01511   0.01063  -0.0935   0.7990   0.0037
  -6.250  -0.2607   0.01345   0.00860  -0.0932   0.7918   0.0036
  -6.000  -0.2349   0.01219   0.00710  -0.0930   0.7849   0.0036
  -5.750  -0.2085   0.01128   0.00597  -0.0928   0.7783   0.0037
  -5.500  -0.1814   0.01055   0.00507  -0.0927   0.7718   0.0038
  -5.250  -0.1540   0.00998   0.00435  -0.0926   0.7656   0.0040
  -5.000  -0.1263   0.00958   0.00384  -0.0926   0.7597   0.0043
  -4.750  -0.0987   0.00892   0.00304  -0.0925   0.7536   0.0073
  -4.500  -0.0711   0.00847   0.00260  -0.0925   0.7481   0.0191
  -4.250  -0.0430   0.00825   0.00236  -0.0925   0.7423   0.0272
  -4.000  -0.0152   0.00808   0.00217  -0.0926   0.7368   0.0361
  -3.750   0.0130   0.00787   0.00200  -0.0927   0.7313   0.0493
  -3.500   0.0409   0.00768   0.00186  -0.0928   0.7257   0.0677
  -3.250   0.0690   0.00754   0.00174  -0.0928   0.7206   0.0841
  -3.000   0.0973   0.00738   0.00161  -0.0929   0.7151   0.1012
  -2.750   0.1254   0.00727   0.00149  -0.0930   0.7099   0.1188
  -2.500   0.1537   0.00714   0.00140  -0.0931   0.7047   0.1362
  -2.250   0.1820   0.00703   0.00131  -0.0932   0.6994   0.1562
  -2.000   0.2101   0.00692   0.00124  -0.0933   0.6944   0.1827
  -1.750   0.2384   0.00676   0.00118  -0.0935   0.6892   0.2184
  -1.500   0.2664   0.00663   0.00112  -0.0936   0.6840   0.2567
  -1.250   0.2946   0.00651   0.00109  -0.0937   0.6790   0.2968
  -1.000   0.3228   0.00635   0.00106  -0.0939   0.6736   0.3501
  -0.750   0.3507   0.00623   0.00104  -0.0940   0.6686   0.4034
  -0.500   0.3789   0.00607   0.00104  -0.0941   0.6634   0.4628
  -0.250   0.4067   0.00591   0.00105  -0.0942   0.6580   0.5325
   0.000   0.4344   0.00576   0.00108  -0.0942   0.6529   0.6071
   0.250   0.4618   0.00556   0.00111  -0.0942   0.6473   0.6896
   0.500   0.4879   0.00536   0.00115  -0.0938   0.6419   0.7866
   0.750   0.5088   0.00505   0.00121  -0.0919   0.6366   0.9173
   1.000   0.5451   0.00499   0.00117  -0.0937   0.6304   1.0000
   1.250   0.5732   0.00505   0.00120  -0.0937   0.6246   1.0000
   1.500   0.6014   0.00511   0.00122  -0.0938   0.6180   1.0000
   1.750   0.6294   0.00518   0.00125  -0.0938   0.6117   1.0000
   2.000   0.6575   0.00523   0.00129  -0.0939   0.6046   1.0000
   2.250   0.6854   0.00531   0.00134  -0.0939   0.5978   1.0000
   2.500   0.7135   0.00538   0.00139  -0.0940   0.5902   1.0000
   2.750   0.7414   0.00545   0.00145  -0.0940   0.5828   1.0000
   3.000   0.7692   0.00554   0.00152  -0.0940   0.5745   1.0000
   3.250   0.7971   0.00562   0.00160  -0.0941   0.5660   1.0000
   3.500   0.8247   0.00572   0.00168  -0.0941   0.5568   1.0000
   3.750   0.8521   0.00583   0.00177  -0.0940   0.5462   1.0000
   4.000   0.8797   0.00594   0.00187  -0.0940   0.5346   1.0000
   4.250   0.9069   0.00607   0.00199  -0.0940   0.5213   1.0000
   4.500   0.9338   0.00624   0.00212  -0.0939   0.5053   1.0000
   4.750   0.9605   0.00642   0.00226  -0.0937   0.4849   1.0000
   5.000   0.9858   0.00673   0.00244  -0.0934   0.4522   1.0000
   5.250   1.0109   0.00706   0.00266  -0.0930   0.4200   1.0000
   5.500   1.0356   0.00743   0.00291  -0.0927   0.3868   1.0000
   5.750   1.0586   0.00799   0.00326  -0.0920   0.3386   1.0000
   6.000   1.0789   0.00880   0.00373  -0.0911   0.2702   1.0000
   6.250   1.0966   0.00985   0.00434  -0.0898   0.1893   1.0000
   6.500   1.1150   0.01081   0.00495  -0.0886   0.1270   1.0000
   6.750   1.1334   0.01172   0.00558  -0.0874   0.0763   1.0000
   7.500   1.1888   0.01430   0.00777  -0.0834   0.0050   1.0000
   7.750   1.2078   0.01505   0.00860  -0.0820   0.0037   1.0000
   8.000   1.2258   0.01583   0.00949  -0.0805   0.0033   1.0000
   8.250   1.2451   0.01644   0.01016  -0.0793   0.0031   1.0000
   8.500   1.2628   0.01713   0.01093  -0.0779   0.0030   1.0000
   8.750   1.2788   0.01790   0.01178  -0.0761   0.0028   1.0000
   9.000   1.2921   0.01876   0.01273  -0.0740   0.0027   1.0000
   9.250   1.3021   0.01957   0.01361  -0.0713   0.0026   1.0000
   9.500   1.3112   0.02041   0.01452  -0.0686   0.0025   1.0000
   9.750   1.3191   0.02137   0.01555  -0.0659   0.0024   1.0000
  10.000   1.3272   0.02238   0.01664  -0.0635   0.0023   1.0000
  10.250   1.3352   0.02348   0.01782  -0.0613   0.0022   1.0000
  10.500   1.3443   0.02456   0.01897  -0.0594   0.0020   1.0000
  10.750   1.3481   0.02613   0.02065  -0.0571   0.0020   1.0000
  11.000   1.3516   0.02783   0.02244  -0.0550   0.0019   1.0000
  11.250   1.3473   0.03040   0.02516  -0.0525   0.0018   1.0000
  11.500   1.3384   0.03380   0.02880  -0.0498   0.0016   1.0000
  11.750   1.3450   0.03557   0.03067  -0.0486   0.0015   1.0000
  12.000   1.3493   0.03765   0.03288  -0.0473   0.0015   1.0000
  12.250   1.3505   0.04018   0.03556  -0.0461   0.0015   1.0000
  12.500   1.3507   0.04293   0.03847  -0.0450   0.0014   1.0000
  12.750   1.3491   0.04595   0.04166  -0.0441   0.0014   1.0000
  13.000   1.3449   0.04943   0.04533  -0.0433   0.0014   1.0000
  13.250   1.3371   0.05350   0.04960  -0.0428   0.0014   1.0000
  13.500   1.3297   0.05757   0.05386  -0.0428   0.0014   1.0000
  13.750   1.3189   0.06229   0.05877  -0.0431   0.0014   1.0000
  14.000   1.3036   0.06802   0.06472  -0.0441   0.0014   1.0000
  14.250   1.2897   0.07375   0.07064  -0.0456   0.0014   1.0000
  14.500   1.2735   0.08025   0.07733  -0.0478   0.0014   1.0000
  14.750   1.2543   0.08772   0.08500  -0.0508   0.0014   1.0000
  15.000   1.2378   0.09514   0.09260  -0.0543   0.0014   1.0000
  15.250   1.2191   0.10351   0.10114  -0.0586   0.0015   1.0000
  15.500   1.1999   0.11253   0.11033  -0.0637   0.0015   1.0000
  15.750   1.1810   0.12204   0.12000  -0.0692   0.0015   1.0000
  16.000   1.1612   0.13248   0.13059  -0.0756   0.0015   1.0000
  16.250   1.1431   0.14297   0.14120  -0.0821   0.0015   1.0000
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