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MH 80 12.72% (mh80-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: MH 80 12.72% (mh80-il)
Reynolds number: 100,000
Max Cl/Cd: 39.74 at α=8°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-mh80-il-100000-n5.txt
Download as CSV file: xf-mh80-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: MH 80  12.72%                                   
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.4957   0.10351   0.09917   0.0159   1.0000   0.0237
  -9.500  -0.4919   0.09957   0.09528   0.0141   1.0000   0.0234
  -9.250  -0.4901   0.09519   0.09097   0.0118   1.0000   0.0230
  -9.000  -0.4911   0.09019   0.08603   0.0088   1.0000   0.0227
  -8.750  -0.4940   0.08475   0.08066   0.0051   1.0000   0.0222
  -8.250  -0.5439   0.06351   0.05929  -0.0112   1.0000   0.0199
  -8.000  -0.5498   0.05884   0.05450  -0.0128   1.0000   0.0197
  -7.750  -0.5522   0.05420   0.04968  -0.0139   1.0000   0.0196
  -7.500  -0.5477   0.04936   0.04449  -0.0152   0.9082   0.0194
  -7.250  -0.5442   0.04542   0.04006  -0.0143   0.8572   0.0193
  -7.000  -0.5395   0.04174   0.03585  -0.0124   0.8247   0.0193
  -6.750  -0.5306   0.03844   0.03197  -0.0105   0.7990   0.0194
  -6.500  -0.5182   0.03521   0.02803  -0.0086   0.7765   0.0201
  -6.250  -0.4998   0.03358   0.02616  -0.0074   0.7546   0.0206
  -6.000  -0.4800   0.03216   0.02447  -0.0063   0.7345   0.0216
  -5.750  -0.4592   0.03028   0.02214  -0.0050   0.7164   0.0225
  -5.500  -0.4366   0.02839   0.01979  -0.0038   0.6992   0.0232
  -5.250  -0.4125   0.02666   0.01763  -0.0026   0.6827   0.0238
  -5.000  -0.3881   0.02527   0.01605  -0.0018   0.6665   0.0244
  -4.750  -0.3634   0.02414   0.01477  -0.0010   0.6507   0.0253
  -4.500  -0.3385   0.02308   0.01354  -0.0001   0.6356   0.0265
  -4.250  -0.3133   0.02213   0.01236   0.0008   0.6212   0.0284
  -4.000  -0.2890   0.02136   0.01155   0.0016   0.6074   0.0312
  -3.750  -0.2645   0.02059   0.01064   0.0025   0.5943   0.0349
  -3.500  -0.2395   0.01987   0.00978   0.0033   0.5809   0.0391
  -3.250  -0.2145   0.01917   0.00904   0.0040   0.5682   0.0472
  -3.000  -0.1897   0.01843   0.00829   0.0048   0.5563   0.0635
  -2.750  -0.1658   0.01753   0.00771   0.0056   0.5449   0.1182
  -2.500  -0.1416   0.01677   0.00735   0.0062   0.5329   0.2119
  -2.250  -0.1182   0.01605   0.00705   0.0070   0.5222   0.3210
  -2.000  -0.0977   0.01508   0.00683   0.0084   0.5118   0.4999
  -1.750  -0.0721   0.01430   0.00700   0.0106   0.5009   0.7366
  -1.500  -0.0305   0.01449   0.00716   0.0099   0.4893   0.8518
  -1.250   0.0039   0.01470   0.00715   0.0096   0.4784   0.8962
  -1.000   0.0390   0.01489   0.00712   0.0090   0.4675   0.9262
  -0.750   0.0842   0.01507   0.00701   0.0062   0.4570   0.9468
  -0.500   0.1340   0.01519   0.00687   0.0024   0.4454   0.9652
  -0.250   0.1881   0.01527   0.00671  -0.0025   0.4341   0.9843
   0.000   0.2440   0.01523   0.00640  -0.0081   0.4240   1.0000
   0.250   0.2680   0.01530   0.00634  -0.0075   0.4156   1.0000
   0.500   0.2917   0.01539   0.00624  -0.0068   0.4090   1.0000
   0.750   0.3159   0.01550   0.00627  -0.0063   0.4010   1.0000
   1.000   0.3397   0.01562   0.00625  -0.0056   0.3946   1.0000
   1.250   0.3639   0.01578   0.00631  -0.0050   0.3879   1.0000
   1.500   0.3879   0.01593   0.00636  -0.0044   0.3812   1.0000
   1.750   0.4117   0.01611   0.00639  -0.0037   0.3757   1.0000
   2.000   0.4360   0.01630   0.00655  -0.0031   0.3688   1.0000
   2.250   0.4599   0.01650   0.00665  -0.0024   0.3633   1.0000
   2.500   0.4838   0.01672   0.00678  -0.0017   0.3584   1.0000
   2.750   0.5078   0.01697   0.00702  -0.0011   0.3522   1.0000
   3.000   0.5316   0.01720   0.00716  -0.0004   0.3471   1.0000
   3.250   0.5554   0.01746   0.00734   0.0003   0.3424   1.0000
   3.500   0.5793   0.01775   0.00766   0.0008   0.3370   1.0000
   3.750   0.6031   0.01803   0.00790   0.0015   0.3323   1.0000
   4.000   0.6267   0.01832   0.00807   0.0023   0.3283   1.0000
   4.250   0.6504   0.01867   0.00847   0.0028   0.3232   1.0000
   4.500   0.6740   0.01899   0.00881   0.0035   0.3183   1.0000
   4.750   0.6976   0.01931   0.00907   0.0042   0.3144   1.0000
   5.000   0.7211   0.01968   0.00940   0.0048   0.3107   1.0000
   5.250   0.7445   0.02010   0.00990   0.0054   0.3059   1.0000
   5.500   0.7678   0.02047   0.01030   0.0060   0.3016   1.0000
   5.750   0.7914   0.02082   0.01059   0.0067   0.2981   1.0000
   6.000   0.8146   0.02127   0.01106   0.0073   0.2945   1.0000
   6.250   0.8374   0.02177   0.01169   0.0079   0.2901   1.0000
   6.500   0.8606   0.02221   0.01216   0.0085   0.2861   1.0000
   6.750   0.8841   0.02259   0.01251   0.0091   0.2827   1.0000
   7.000   0.9073   0.02309   0.01304   0.0096   0.2793   1.0000
   7.250   0.9294   0.02372   0.01383   0.0101   0.2751   1.0000
   7.500   0.9520   0.02425   0.01444   0.0106   0.2714   1.0000
   7.750   0.9754   0.02469   0.01489   0.0111   0.2681   1.0000
   8.000   0.9991   0.02514   0.01531   0.0116   0.2651   1.0000
   8.250   1.0193   0.02597   0.01637   0.0121   0.2609   1.0000
   8.500   1.0406   0.02666   0.01720   0.0126   0.2572   1.0000
   8.750   1.0630   0.02719   0.01778   0.0131   0.2539   1.0000
   9.000   1.0867   0.02763   0.01819   0.0135   0.2510   1.0000
   9.250   1.1053   0.02856   0.01935   0.0140   0.2472   1.0000
   9.500   1.1235   0.02950   0.02047   0.0146   0.2434   1.0000
   9.750   1.1437   0.03020   0.02128   0.0151   0.2400   1.0000
  10.000   1.1661   0.03069   0.02179   0.0156   0.2371   1.0000
  10.250   1.1851   0.03151   0.02271   0.0161   0.2340   1.0000
  10.500   1.1965   0.03290   0.02437   0.0169   0.2299   1.0000
  10.750   1.2114   0.03392   0.02555   0.0176   0.2265   1.0000
  11.000   1.2308   0.03453   0.02622   0.0181   0.2234   1.0000
  11.250   1.2547   0.03487   0.02651   0.0186   0.2208   1.0000
  11.500   1.2508   0.03712   0.02914   0.0198   0.2169   1.0000
  11.750   1.2509   0.03893   0.03115   0.0209   0.2134   1.0000
  12.000   1.2568   0.04013   0.03244   0.0220   0.2104   1.0000
  12.250   1.2779   0.04042   0.03274   0.0227   0.2076   1.0000
  12.500   1.2633   0.04333   0.03583   0.0233   0.2048   1.0000
  12.750   1.0638   0.07024   0.06312   0.0094   0.1957   1.0000
  13.000   1.1042   0.06729   0.06024   0.0119   0.1948   1.0000
  13.250   1.1661   0.06157   0.05454   0.0160   0.1940   1.0000
  15.250   0.9115   0.13463   0.12797  -0.0205   0.1419   1.0000
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