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

MH 200 12.97% (mh200-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: MH 200 12.97% (mh200-il)
Reynolds number: 50,000
Max Cl/Cd: 33.72 at α=8°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-mh200-il-50000.txt
Download as CSV file: xf-mh200-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: MH 200  12.97%                                  
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.3727   0.10024   0.09386  -0.0289   1.0000   0.3129
  -8.250  -0.4837   0.08620   0.08031  -0.0413   1.0000   0.1675
  -8.000  -0.5238   0.08404   0.07832  -0.0388   1.0000   0.1662
  -7.750  -0.5591   0.08035   0.07468  -0.0376   1.0000   0.1531
  -7.500  -0.5907   0.07600   0.07032  -0.0366   1.0000   0.1401
  -7.250  -0.6157   0.07149   0.06565  -0.0356   1.0000   0.1286
  -7.000  -0.6376   0.06645   0.06025  -0.0347   1.0000   0.1173
  -6.750  -0.6513   0.06123   0.05444  -0.0336   1.0000   0.1071
  -6.500  -0.6430   0.05745   0.05053  -0.0322   1.0000   0.1020
  -6.250  -0.6393   0.05300   0.04559  -0.0310   1.0000   0.0964
  -6.000  -0.6297   0.04920   0.04097  -0.0297   1.0000   0.0910
  -5.750  -0.6149   0.04580   0.03724  -0.0286   1.0000   0.0892
  -5.500  -0.5976   0.04272   0.03368  -0.0275   1.0000   0.0883
  -5.250  -0.5781   0.04010   0.03055  -0.0265   1.0000   0.0896
  -5.000  -0.5569   0.03798   0.02782  -0.0253   1.0000   0.0921
  -4.750  -0.5357   0.03555   0.02535  -0.0244   1.0000   0.0961
  -4.500  -0.5129   0.03367   0.02327  -0.0230   1.0000   0.1010
  -4.250  -0.4908   0.03204   0.02155  -0.0214   1.0000   0.1099
  -4.000  -0.4698   0.03059   0.02017  -0.0197   1.0000   0.1269
  -3.750  -0.4498   0.02905   0.01878  -0.0178   1.0000   0.1585
  -3.500  -0.4412   0.02422   0.01703  -0.0144   1.0000   0.4882
  -3.250  -0.4549   0.02546   0.01913  -0.0010   1.0000   0.7281
  -3.000  -0.4620   0.02668   0.02029   0.0098   1.0000   0.8015
  -2.750  -0.4652   0.02787   0.02139   0.0213   1.0000   0.8712
  -2.500  -0.1700   0.03177   0.02321  -0.0202   1.0000   0.9897
  -2.250  -0.1350   0.03137   0.02250  -0.0246   1.0000   1.0000
  -2.000  -0.1365   0.03094   0.02192  -0.0220   1.0000   1.0000
  -1.750  -0.1373   0.03056   0.02142  -0.0194   1.0000   1.0000
  -1.500  -0.1377   0.03021   0.02096  -0.0167   1.0000   1.0000
  -1.250  -0.1376   0.02989   0.02052  -0.0140   1.0000   1.0000
  -1.000  -0.1373   0.02959   0.02012  -0.0113   1.0000   1.0000
  -0.750  -0.1367   0.02931   0.01973  -0.0086   1.0000   1.0000
  -0.500  -0.1359   0.02904   0.01936  -0.0058   1.0000   1.0000
  -0.250  -0.1347   0.02877   0.01899  -0.0031   1.0000   1.0000
   0.000  -0.1328   0.02854   0.01867  -0.0005   1.0000   1.0000
   0.250  -0.1297   0.02835   0.01839   0.0019   1.0000   1.0000
   0.500  -0.1229   0.02829   0.01823   0.0037   1.0000   1.0000
   0.750  -0.1118   0.02841   0.01824   0.0046   1.0000   1.0000
   1.000  -0.0974   0.02868   0.01841   0.0050   1.0000   1.0000
   1.250  -0.0808   0.02908   0.01869   0.0050   1.0000   1.0000
   1.500  -0.0630   0.02959   0.01911   0.0048   1.0000   1.0000
   1.750  -0.0445   0.03019   0.01962   0.0044   1.0000   1.0000
   2.000  -0.0257   0.03087   0.02023   0.0038   1.0000   1.0000
   2.250  -0.0068   0.03163   0.02092   0.0032   1.0000   1.0000
   2.500   0.0301   0.03324   0.02247  -0.0008   0.9914   1.0000
   2.750   0.0912   0.03566   0.02484  -0.0090   0.9656   1.0000
   3.000   0.1378   0.03736   0.02653  -0.0143   0.9455   1.0000
   3.250   0.1806   0.03886   0.02804  -0.0186   0.9252   1.0000
   3.500   0.2174   0.04009   0.02930  -0.0217   0.9055   1.0000
   3.750   0.2651   0.04160   0.03085  -0.0263   0.8855   1.0000
   4.000   0.2942   0.04253   0.03183  -0.0278   0.8648   1.0000
   4.250   0.3351   0.04366   0.03304  -0.0309   0.8442   1.0000
   4.500   0.3704   0.04464   0.03412  -0.0329   0.8232   1.0000
   4.750   0.4069   0.04548   0.03507  -0.0348   0.8020   1.0000
   5.000   0.4458   0.04622   0.03593  -0.0368   0.7810   1.0000
   5.250   0.4788   0.04683   0.03670  -0.0379   0.7591   1.0000
   5.500   0.5198   0.04718   0.03721  -0.0395   0.7380   1.0000
   5.750   0.5530   0.04747   0.03768  -0.0400   0.7155   1.0000
   6.000   0.5920   0.04740   0.03781  -0.0408   0.6938   1.0000
   6.250   0.6325   0.04695   0.03759  -0.0412   0.6716   1.0000
   6.500   0.6673   0.04646   0.03735  -0.0409   0.6481   1.0000
   6.750   0.7279   0.04398   0.03521  -0.0415   0.6276   1.0000
   7.000   0.7681   0.04220   0.03370  -0.0403   0.6029   1.0000
   7.250   0.8457   0.03718   0.02916  -0.0404   0.5788   1.0000
   7.500   0.9389   0.03151   0.02386  -0.0423   0.5378   1.0000
   7.750   0.9924   0.02959   0.02178  -0.0422   0.4832   1.0000
   8.000   1.0141   0.03007   0.02208  -0.0400   0.4342   1.0000
   8.250   1.0351   0.03099   0.02273  -0.0380   0.3873   1.0000
   8.500   1.0524   0.03228   0.02379  -0.0360   0.3449   1.0000
   8.750   1.0687   0.03380   0.02513  -0.0340   0.3056   1.0000
   9.000   1.0847   0.03548   0.02659  -0.0322   0.2696   1.0000
   9.250   1.1024   0.03747   0.02839  -0.0307   0.2372   1.0000
   9.500   1.1189   0.03959   0.03039  -0.0292   0.2093   1.0000
   9.750   1.1308   0.04195   0.03292  -0.0272   0.1880   1.0000
  10.000   1.1530   0.04451   0.03532  -0.0266   0.1676   1.0000
  10.250   1.1680   0.04734   0.03833  -0.0252   0.1534   1.0000
  10.500   1.1822   0.05008   0.04115  -0.0239   0.1404   1.0000
  10.750   1.1775   0.05340   0.04510  -0.0203   0.1353   1.0000
  11.000   1.1952   0.05690   0.04868  -0.0197   0.1263   1.0000
  11.250   1.1795   0.06017   0.05248  -0.0156   0.1236   1.0000
  11.500   1.1638   0.06340   0.05607  -0.0118   0.1209   1.0000
  11.750   1.1858   0.06754   0.06014  -0.0121   0.1135   1.0000
  12.000   1.1645   0.07121   0.06413  -0.0085   0.1132   1.0000
  12.250   1.1414   0.07525   0.06845  -0.0058   0.1132   1.0000
  12.500   1.1171   0.07971   0.07315  -0.0041   0.1133   1.0000
  12.750   1.0941   0.08475   0.07838  -0.0034   0.1136   1.0000
<< Back to MH 200 12.97% (mh200-il)

Polar data table (+)

Polar graphs


<< Back to MH 200 12.97% (mh200-il)