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MH 82 13.31% (mh82-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: MH 82 13.31% (mh82-il)
Reynolds number: 100,000
Max Cl/Cd: 42.05 at α=7.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-mh82-il-100000-n5.txt
Download as CSV file: xf-mh82-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: MH 82  13.31%                                   
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.3574   0.09536   0.09108  -0.0035   0.8319   0.0299
  -8.500  -0.3531   0.09246   0.08810  -0.0038   0.8037   0.0292
  -8.000  -0.3642   0.08131   0.07687  -0.0107   0.7685   0.0256
  -7.750  -0.3639   0.07759   0.07312  -0.0127   0.7514   0.0253
  -7.500  -0.3679   0.07330   0.06881  -0.0159   0.7364   0.0249
  -7.250  -0.3686   0.06841   0.06384  -0.0197   0.7232   0.0244
  -7.000  -0.3692   0.06260   0.05787  -0.0236   0.7120   0.0238
  -6.500  -0.3773   0.04528   0.03947  -0.0304   0.6961   0.0217
  -6.250  -0.3644   0.04161   0.03540  -0.0305   0.6835   0.0215
  -6.000  -0.3496   0.03793   0.03119  -0.0303   0.6720   0.0215
  -5.750  -0.3320   0.03483   0.02753  -0.0297   0.6610   0.0215
  -5.500  -0.3116   0.03201   0.02415  -0.0290   0.6488   0.0218
  -5.250  -0.2888   0.03071   0.02272  -0.0287   0.6364   0.0226
  -5.000  -0.2654   0.02924   0.02092  -0.0280   0.6251   0.0237
  -4.750  -0.2407   0.02749   0.01871  -0.0274   0.6132   0.0250
  -4.500  -0.2151   0.02588   0.01667  -0.0267   0.6020   0.0259
  -4.250  -0.1898   0.02468   0.01529  -0.0260   0.5916   0.0268
  -4.000  -0.1634   0.02356   0.01401  -0.0255   0.5797   0.0278
  -3.750  -0.1371   0.02255   0.01279  -0.0249   0.5695   0.0290
  -3.500  -0.1109   0.02163   0.01168  -0.0242   0.5591   0.0307
  -3.250  -0.0848   0.02095   0.01096  -0.0238   0.5483   0.0337
  -3.000  -0.0589   0.02029   0.01016  -0.0231   0.5393   0.0377
  -2.750  -0.0323   0.01965   0.00942  -0.0226   0.5287   0.0423
  -2.500  -0.0063   0.01906   0.00878  -0.0221   0.5197   0.0513
  -2.250   0.0200   0.01841   0.00820  -0.0215   0.5100   0.0707
  -2.000   0.0458   0.01774   0.00777  -0.0211   0.5014   0.1275
  -1.750   0.0715   0.01718   0.00751  -0.0207   0.4923   0.2079
  -1.500   0.0962   0.01652   0.00730  -0.0202   0.4840   0.3274
  -1.250   0.1189   0.01568   0.00719  -0.0192   0.4757   0.5179
  -1.000   0.1399   0.01498   0.00725  -0.0164   0.4685   0.7463
  -0.750   0.1824   0.01492   0.00724  -0.0175   0.4587   0.8980
  -0.500   0.2291   0.01502   0.00709  -0.0204   0.4495   0.9550
  -0.250   0.2825   0.01509   0.00685  -0.0251   0.4402   0.9882
   0.000   0.3204   0.01519   0.00673  -0.0272   0.4322   1.0000
   0.250   0.3445   0.01533   0.00668  -0.0265   0.4252   1.0000
   0.500   0.3687   0.01550   0.00664  -0.0258   0.4191   1.0000
   0.750   0.3932   0.01567   0.00670  -0.0252   0.4120   1.0000
   1.000   0.4176   0.01586   0.00669  -0.0245   0.4064   1.0000
   1.250   0.4423   0.01608   0.00679  -0.0239   0.4005   1.0000
   1.500   0.4671   0.01630   0.00689  -0.0233   0.3943   1.0000
   1.750   0.4918   0.01652   0.00693  -0.0227   0.3893   1.0000
   2.000   0.5167   0.01677   0.00711  -0.0221   0.3833   1.0000
   2.250   0.5418   0.01703   0.00728  -0.0216   0.3778   1.0000
   2.500   0.5668   0.01729   0.00739  -0.0211   0.3734   1.0000
   2.750   0.5921   0.01759   0.00763  -0.0206   0.3684   1.0000
   3.000   0.6174   0.01789   0.00788  -0.0202   0.3630   1.0000
   3.250   0.6428   0.01816   0.00805  -0.0198   0.3585   1.0000
   3.500   0.6682   0.01848   0.00826  -0.0193   0.3544   1.0000
   3.750   0.6936   0.01884   0.00865  -0.0190   0.3494   1.0000
   4.000   0.7190   0.01918   0.00894  -0.0187   0.3452   1.0000
   4.250   0.7446   0.01950   0.00916  -0.0183   0.3414   1.0000
   4.500   0.7700   0.01988   0.00953  -0.0180   0.3374   1.0000
   4.750   0.7952   0.02030   0.00998  -0.0178   0.3327   1.0000
   5.000   0.8205   0.02067   0.01033  -0.0175   0.3287   1.0000
   5.250   0.8461   0.02104   0.01062  -0.0171   0.3256   1.0000
   5.500   0.8712   0.02148   0.01107  -0.0169   0.3221   1.0000
   5.750   0.8957   0.02199   0.01166  -0.0166   0.3178   1.0000
   6.000   0.9206   0.02243   0.01211  -0.0164   0.3139   1.0000
   6.250   0.9458   0.02282   0.01247  -0.0161   0.3107   1.0000
   6.500   0.9713   0.02326   0.01285  -0.0158   0.3080   1.0000
   6.750   0.9943   0.02392   0.01367  -0.0156   0.3040   1.0000
   7.000   1.0180   0.02448   0.01431  -0.0153   0.3001   1.0000
   7.250   1.0423   0.02495   0.01481  -0.0150   0.2968   1.0000
   7.500   1.0673   0.02538   0.01520  -0.0147   0.2941   1.0000
   7.750   1.0905   0.02603   0.01593  -0.0145   0.2911   1.0000
   8.000   1.1115   0.02682   0.01690  -0.0141   0.2873   1.0000
   8.250   1.1337   0.02747   0.01763  -0.0138   0.2838   1.0000
   8.500   1.1571   0.02798   0.01816  -0.0135   0.2808   1.0000
   8.750   1.1818   0.02845   0.01861  -0.0132   0.2783   1.0000
   9.000   1.2010   0.02938   0.01971  -0.0128   0.2752   1.0000
   9.250   1.2184   0.03039   0.02092  -0.0122   0.2715   1.0000
   9.500   1.2378   0.03118   0.02182  -0.0118   0.2682   1.0000
   9.750   1.2597   0.03175   0.02243  -0.0114   0.2654   1.0000
  10.250   1.2959   0.03358   0.02448  -0.0103   0.2599   1.0000
  10.500   1.3054   0.03500   0.02613  -0.0094   0.2563   1.0000
  10.750   1.3188   0.03606   0.02731  -0.0087   0.2532   1.0000
  11.000   1.3376   0.03674   0.02805  -0.0081   0.2505   1.0000
  11.250   1.3620   0.03713   0.02842  -0.0078   0.2483   1.0000
  11.500   1.3547   0.03943   0.03099  -0.0062   0.2451   1.0000
  11.750   1.3328   0.04253   0.03433  -0.0044   0.2418   1.0000
  12.000   1.3200   0.04557   0.03752  -0.0040   0.2387   1.0000
  12.250   1.3310   0.04682   0.03883  -0.0037   0.2361   1.0000
  12.500   1.3642   0.04623   0.03822  -0.0030   0.2340   1.0000
  13.000   1.1634   0.07620   0.06865  -0.0153   0.2196   1.0000
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