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MH 46 9.1% (mh46-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: MH 46 9.1% (mh46-il)
Reynolds number: 100,000
Max Cl/Cd: 46.04 at α=6°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-mh46-il-100000.txt
Download as CSV file: xf-mh46-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: MH 46  9.1%                                     
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.4431   0.09136   0.08711  -0.0033   1.0000   0.1126
  -8.500  -0.4434   0.08735   0.08314  -0.0047   1.0000   0.1171
  -8.250  -0.4684   0.08296   0.07889  -0.0106   1.0000   0.1206
  -8.000  -0.5790   0.08465   0.08025  -0.0210   1.0000   0.1078
  -7.750  -0.5366   0.08216   0.07789  -0.0104   1.0000   0.1181
  -7.500  -0.5621   0.07653   0.07220  -0.0213   1.0000   0.1209
  -7.250  -0.5374   0.07360   0.06941  -0.0154   1.0000   0.1269
  -7.000  -0.5526   0.06802   0.06367  -0.0233   1.0000   0.1359
  -6.750  -0.5550   0.04953   0.04420  -0.0300   1.0000   0.0536
  -6.500  -0.5447   0.04488   0.03935  -0.0297   1.0000   0.0512
  -6.250  -0.5354   0.03935   0.03272  -0.0280   1.0000   0.0431
  -6.000  -0.5205   0.03573   0.02868  -0.0268   1.0000   0.0432
  -5.750  -0.5042   0.03235   0.02489  -0.0253   1.0000   0.0434
  -5.500  -0.4860   0.02952   0.02164  -0.0237   1.0000   0.0433
  -5.250  -0.4672   0.02677   0.01853  -0.0219   1.0000   0.0434
  -5.000  -0.4486   0.02411   0.01561  -0.0201   1.0000   0.0446
  -4.750  -0.4303   0.02223   0.01365  -0.0183   1.0000   0.0473
  -4.500  -0.4124   0.02104   0.01225  -0.0162   1.0000   0.0543
  -4.250  -0.3970   0.01947   0.01076  -0.0140   1.0000   0.0641
  -4.000  -0.3828   0.01797   0.00935  -0.0115   1.0000   0.0845
  -3.750  -0.3699   0.01655   0.00826  -0.0090   1.0000   0.1384
  -3.500  -0.3577   0.01521   0.00756  -0.0066   1.0000   0.2436
  -3.250  -0.3440   0.01450   0.00728  -0.0045   1.0000   0.3396
  -3.000  -0.3299   0.01402   0.00718  -0.0024   1.0000   0.4323
  -2.750  -0.3152   0.01361   0.00709  -0.0002   1.0000   0.5252
  -2.500  -0.2994   0.01319   0.00706   0.0021   1.0000   0.6267
  -2.250  -0.2621   0.01268   0.00715   0.0014   0.9956   0.8007
  -2.000  -0.1307   0.01270   0.00689  -0.0175   1.0000   1.0000
  -1.750  -0.0952   0.01285   0.00676  -0.0205   0.9926   1.0000
  -1.500  -0.0394   0.01301   0.00665  -0.0268   0.9819   1.0000
  -1.250   0.0145   0.01310   0.00651  -0.0325   0.9705   1.0000
  -1.000   0.0692   0.01314   0.00638  -0.0382   0.9593   1.0000
  -0.750   0.1222   0.01312   0.00624  -0.0435   0.9477   1.0000
  -0.500   0.1699   0.01309   0.00609  -0.0475   0.9344   1.0000
  -0.250   0.2107   0.01307   0.00599  -0.0499   0.9194   1.0000
   0.000   0.2440   0.01309   0.00594  -0.0507   0.9032   1.0000
   0.250   0.2711   0.01316   0.00594  -0.0500   0.8868   1.0000
   0.500   0.2921   0.01330   0.00602  -0.0483   0.8683   1.0000
   0.750   0.3127   0.01343   0.00609  -0.0464   0.8507   1.0000
   1.000   0.3329   0.01354   0.00614  -0.0443   0.8340   1.0000
   1.250   0.3531   0.01364   0.00618  -0.0421   0.8179   1.0000
   1.500   0.3735   0.01379   0.00630  -0.0401   0.7999   1.0000
   1.750   0.3942   0.01390   0.00638  -0.0382   0.7823   1.0000
   2.000   0.4154   0.01400   0.00643  -0.0362   0.7653   1.0000
   2.250   0.4370   0.01408   0.00645  -0.0343   0.7487   1.0000
   2.500   0.4591   0.01421   0.00660  -0.0327   0.7296   1.0000
   2.750   0.4815   0.01430   0.00667  -0.0311   0.7111   1.0000
   3.000   0.5042   0.01437   0.00669  -0.0294   0.6934   1.0000
   3.250   0.5272   0.01450   0.00683  -0.0280   0.6727   1.0000
   3.500   0.5505   0.01458   0.00692  -0.0265   0.6533   1.0000
   3.750   0.5739   0.01471   0.00705  -0.0252   0.6318   1.0000
   4.000   0.5976   0.01482   0.00712  -0.0238   0.6109   1.0000
   4.250   0.6212   0.01498   0.00729  -0.0226   0.5871   1.0000
   4.500   0.6448   0.01515   0.00745  -0.0213   0.5631   1.0000
   4.750   0.6685   0.01534   0.00765  -0.0200   0.5382   1.0000
   5.000   0.6919   0.01558   0.00786  -0.0188   0.5115   1.0000
   5.250   0.7151   0.01586   0.00813  -0.0176   0.4828   1.0000
   5.500   0.7380   0.01619   0.00845  -0.0165   0.4521   1.0000
   5.750   0.7606   0.01656   0.00879  -0.0153   0.4200   1.0000
   6.000   0.7826   0.01700   0.00922  -0.0141   0.3858   1.0000
   6.250   0.8040   0.01750   0.00966  -0.0129   0.3492   1.0000
   6.500   0.8246   0.01809   0.01020  -0.0117   0.3097   1.0000
   6.750   0.8442   0.01880   0.01082  -0.0104   0.2683   1.0000
   7.000   0.8624   0.01973   0.01158  -0.0091   0.2254   1.0000
   7.250   0.8792   0.02095   0.01259  -0.0077   0.1823   1.0000
   7.500   0.8945   0.02242   0.01385  -0.0063   0.1417   1.0000
   7.750   0.9103   0.02416   0.01548  -0.0046   0.1119   1.0000
   8.000   0.9259   0.02592   0.01711  -0.0032   0.0909   1.0000
   8.250   0.9446   0.02811   0.01924  -0.0018   0.0780   1.0000
   8.500   0.9633   0.02980   0.02111  -0.0004   0.0678   1.0000
   8.750   0.9826   0.03228   0.02379   0.0009   0.0604   1.0000
   9.000   1.0018   0.03478   0.02644   0.0020   0.0554   1.0000
   9.250   1.0165   0.03808   0.03005   0.0034   0.0510   1.0000
   9.500   1.0281   0.04071   0.03312   0.0052   0.0470   1.0000
   9.750   1.0382   0.04404   0.03678   0.0069   0.0449   1.0000
  10.000   1.0450   0.04764   0.04058   0.0083   0.0427   1.0000
  10.250   1.0421   0.05323   0.04648   0.0096   0.0415   1.0000
  10.500   1.0309   0.05572   0.04944   0.0122   0.0405   1.0000
  10.750   1.0177   0.05919   0.05324   0.0143   0.0402   1.0000
  11.000   0.9992   0.06240   0.05669   0.0162   0.0399   1.0000
  11.250   0.9820   0.06664   0.06111   0.0164   0.0403   1.0000
  11.500   0.9633   0.07117   0.06581   0.0154   0.0405   1.0000
  11.750   0.9438   0.07652   0.07130   0.0133   0.0408   1.0000
  12.000   0.9278   0.08266   0.07752   0.0109   0.0413   1.0000
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