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MH 70 11.08% (mh70-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: MH 70 11.08% (mh70-il)
Reynolds number: 50,000
Max Cl/Cd: 27.4 at α=7.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-mh70-il-50000.txt
Download as CSV file: xf-mh70-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: MH 70  11.08%                                   
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.3925   0.12272   0.11603  -0.0148   1.0000   0.2016
  -9.500  -0.3605   0.11589   0.10918  -0.0128   1.0000   0.2115
  -9.250  -0.3823   0.11616   0.10961  -0.0161   1.0000   0.2173
  -9.000  -0.3504   0.10962   0.10304  -0.0142   1.0000   0.2269
  -8.750  -0.3667   0.10863   0.10221  -0.0166   1.0000   0.2339
  -8.500  -0.3416   0.10355   0.09712  -0.0153   1.0000   0.2434
  -8.250  -0.3465   0.10109   0.09478  -0.0164   1.0000   0.2514
  -8.000  -0.3399   0.09828   0.09201  -0.0164   1.0000   0.2624
  -7.750  -0.3303   0.09443   0.08825  -0.0161   1.0000   0.2708
  -7.500  -0.3512   0.09375   0.08776  -0.0172   1.0000   0.2813
  -7.250  -0.3290   0.08932   0.08334  -0.0159   1.0000   0.2934
  -7.000  -0.3224   0.08610   0.08022  -0.0151   1.0000   0.3044
  -6.750  -0.3354   0.08444   0.07875  -0.0141   1.0000   0.3152
  -6.500  -0.3515   0.08357   0.07807  -0.0115   1.0000   0.3275
  -6.250  -0.3456   0.08060   0.07519  -0.0088   1.0000   0.3415
  -5.250  -0.4382   0.06004   0.05423  -0.0303   1.0000   0.1569
  -5.000  -0.4270   0.05259   0.04615  -0.0336   1.0000   0.1239
  -4.750  -0.4147   0.04728   0.04024  -0.0346   1.0000   0.1124
  -4.500  -0.3992   0.04401   0.03659  -0.0343   1.0000   0.1089
  -4.250  -0.3822   0.04089   0.03304  -0.0340   1.0000   0.1082
  -4.000  -0.3627   0.03813   0.02978  -0.0338   1.0000   0.1084
  -3.750  -0.3408   0.03560   0.02669  -0.0334   1.0000   0.1095
  -3.500  -0.3179   0.03349   0.02405  -0.0328   1.0000   0.1106
  -3.250  -0.2975   0.03172   0.02228  -0.0322   1.0000   0.1179
  -3.000  -0.2744   0.03016   0.02031  -0.0314   1.0000   0.1269
  -2.750  -0.2529   0.02886   0.01892  -0.0306   1.0000   0.1421
  -2.500  -0.2313   0.02774   0.01789  -0.0298   1.0000   0.1654
  -2.250  -0.2095   0.02654   0.01688  -0.0289   1.0000   0.2146
  -2.000  -0.1861   0.02436   0.01604  -0.0279   1.0000   0.4144
  -1.750  -0.1776   0.02297   0.01615  -0.0228   1.0000   0.6678
  -1.500  -0.1183   0.02268   0.01590  -0.0281   0.9909   1.0000
  -1.250  -0.0695   0.02360   0.01614  -0.0335   0.9783   1.0000
  -1.000  -0.0242   0.02450   0.01652  -0.0381   0.9653   1.0000
  -0.750   0.0194   0.02539   0.01699  -0.0421   0.9520   1.0000
  -0.500   0.0620   0.02628   0.01753  -0.0459   0.9385   1.0000
  -0.250   0.1042   0.02715   0.01810  -0.0495   0.9247   1.0000
   0.000   0.1463   0.02800   0.01870  -0.0528   0.9107   1.0000
   0.250   0.1863   0.02880   0.01929  -0.0557   0.8964   1.0000
   0.500   0.2215   0.02955   0.01986  -0.0577   0.8815   1.0000
   0.750   0.2556   0.03030   0.02046  -0.0594   0.8664   1.0000
   1.000   0.2895   0.03104   0.02108  -0.0609   0.8512   1.0000
   1.250   0.3229   0.03177   0.02170  -0.0622   0.8358   1.0000
   1.500   0.3556   0.03247   0.02232  -0.0633   0.8203   1.0000
   1.750   0.3886   0.03315   0.02292  -0.0644   0.8047   1.0000
   2.000   0.4220   0.03377   0.02350  -0.0653   0.7889   1.0000
   2.250   0.4550   0.03436   0.02405  -0.0660   0.7731   1.0000
   2.500   0.4867   0.03490   0.02457  -0.0664   0.7572   1.0000
   2.750   0.5170   0.03540   0.02507  -0.0664   0.7413   1.0000
   3.000   0.5468   0.03585   0.02551  -0.0661   0.7253   1.0000
   3.250   0.5763   0.03623   0.02589  -0.0657   0.7094   1.0000
   3.500   0.6052   0.03656   0.02623  -0.0651   0.6935   1.0000
   3.750   0.6344   0.03679   0.02650  -0.0643   0.6776   1.0000
   4.000   0.6633   0.03694   0.02668  -0.0633   0.6618   1.0000
   4.250   0.6919   0.03704   0.02681  -0.0622   0.6460   1.0000
   4.500   0.7204   0.03705   0.02686  -0.0610   0.6302   1.0000
   4.750   0.7491   0.03701   0.02689  -0.0597   0.6144   1.0000
   5.000   0.7784   0.03684   0.02676  -0.0583   0.5986   1.0000
   5.250   0.8079   0.03661   0.02658  -0.0569   0.5827   1.0000
   5.500   0.8383   0.03627   0.02630  -0.0555   0.5668   1.0000
   5.750   0.8683   0.03596   0.02603  -0.0540   0.5508   1.0000
   6.000   0.8877   0.03660   0.02676  -0.0524   0.5325   1.0000
   6.250   0.9100   0.03704   0.02727  -0.0509   0.5149   1.0000
   6.500   0.9351   0.03725   0.02753  -0.0494   0.4976   1.0000
   6.750   0.9611   0.03742   0.02775  -0.0481   0.4805   1.0000
   7.000   0.9876   0.03760   0.02800  -0.0467   0.4636   1.0000
   7.250   1.0137   0.03788   0.02830  -0.0454   0.4469   1.0000
   7.500   1.0389   0.03833   0.02879  -0.0442   0.4304   1.0000
   7.750   1.0639   0.03883   0.02934  -0.0430   0.4140   1.0000
   8.000   1.0863   0.03968   0.03024  -0.0418   0.3982   1.0000
   8.250   1.1077   0.04063   0.03126  -0.0405   0.3826   1.0000
   8.500   1.1244   0.04207   0.03283  -0.0392   0.3680   1.0000
   8.750   1.1383   0.04374   0.03465  -0.0377   0.3539   1.0000
   9.000   1.1473   0.04587   0.03695  -0.0361   0.3409   1.0000
   9.250   1.1575   0.04798   0.03921  -0.0347   0.3287   1.0000
   9.500   1.1750   0.04947   0.04080  -0.0334   0.3162   1.0000
   9.750   1.1990   0.05054   0.04191  -0.0324   0.3034   1.0000
  10.000   1.1627   0.05638   0.04812  -0.0297   0.2979   1.0000
  10.250   1.1159   0.06326   0.05514  -0.0277   0.2949   1.0000
  10.500   1.0740   0.07076   0.06264  -0.0277   0.2916   1.0000
  11.000   1.1962   0.06563   0.05778  -0.0243   0.2596   1.0000
  11.250   0.7645   0.13654   0.12770  -0.0666   0.4264   1.0000
  11.500   0.7601   0.13890   0.13011  -0.0669   0.4146   1.0000
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