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AH 95-160 (ah95160-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: AH 95-160 (ah95160-il)
Reynolds number: 100,000
Max Cl/Cd: 24.79 at α=1.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-ah95160-il-100000-n5.txt
Download as CSV file: xf-ah95160-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: AH 95-160                                       
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -12.000  -0.1779   0.12972   0.12386  -0.0641   0.7822   0.0587
 -11.750  -0.1715   0.12649   0.12062  -0.0657   0.7793   0.0591
 -11.250  -0.1778   0.11519   0.10926  -0.0723   0.7747   0.0420
 -11.000  -0.1676   0.11241   0.10644  -0.0726   0.7721   0.0413
 -10.750  -0.1618   0.10908   0.10308  -0.0738   0.7699   0.0406
 -10.500  -0.1575   0.10534   0.09937  -0.0759   0.7672   0.0404
 -10.250  -0.1544   0.10143   0.09547  -0.0783   0.7645   0.0407
 -10.000  -0.1521   0.09739   0.09144  -0.0808   0.7620   0.0409
  -9.750  -0.1501   0.09330   0.08736  -0.0833   0.7597   0.0409
  -9.250  -0.1475   0.08488   0.07893  -0.0885   0.7553   0.0404
  -9.000  -0.1485   0.08015   0.07419  -0.0917   0.7532   0.0401
  -8.750  -0.1515   0.07465   0.06872  -0.0962   0.7508   0.0398
  -8.500  -0.1618   0.06734   0.06146  -0.1037   0.7477   0.0393
  -8.250  -0.1848   0.05668   0.05059  -0.1148   0.7446   0.0387
  -8.000  -0.1945   0.04957   0.04309  -0.1192   0.7418   0.0387
  -7.750  -0.1910   0.04486   0.03794  -0.1212   0.7395   0.0396
  -7.500  -0.1839   0.04009   0.03251  -0.1225   0.7374   0.0412
  -7.250  -0.1688   0.03681   0.02865  -0.1230   0.7356   0.0426
  -7.000  -0.1472   0.03554   0.02724  -0.1232   0.7332   0.0437
  -6.750  -0.1260   0.03397   0.02541  -0.1234   0.7301   0.0450
  -6.500  -0.1040   0.03218   0.02323  -0.1236   0.7271   0.0471
  -6.250  -0.0805   0.03087   0.02162  -0.1236   0.7246   0.0495
  -6.000  -0.0555   0.03015   0.02078  -0.1237   0.7224   0.0518
  -5.750  -0.0301   0.02895   0.01928  -0.1237   0.7206   0.0546
  -5.500  -0.0042   0.02813   0.01830  -0.1238   0.7188   0.0576
  -5.250   0.0221   0.02755   0.01759  -0.1238   0.7170   0.0614
  -5.000   0.0461   0.02695   0.01685  -0.1237   0.7136   0.0652
  -4.750   0.0707   0.02664   0.01657  -0.1237   0.7106   0.0694
  -4.500   0.0963   0.02618   0.01595  -0.1236   0.7081   0.0747
  -4.250   0.1218   0.02580   0.01562  -0.1236   0.7060   0.0801
  -4.000   0.1484   0.02539   0.01509  -0.1236   0.7040   0.0867
  -3.750   0.1750   0.02499   0.01470  -0.1236   0.7022   0.0938
  -3.500   0.2022   0.02458   0.01424  -0.1236   0.7006   0.1018
  -3.250   0.2255   0.02457   0.01425  -0.1235   0.6974   0.1103
  -3.000   0.2482   0.02458   0.01433  -0.1232   0.6942   0.1195
  -2.750   0.2726   0.02455   0.01431  -0.1231   0.6915   0.1309
  -2.500   0.2981   0.02444   0.01422  -0.1231   0.6891   0.1455
  -2.250   0.3247   0.02421   0.01407  -0.1232   0.6870   0.1666
  -2.000   0.3520   0.02388   0.01389  -0.1234   0.6852   0.2056
  -1.750   0.3792   0.02334   0.01375  -0.1238   0.6837   0.3083
  -1.500   0.3985   0.02314   0.01429  -0.1231   0.6808   0.4905
  -1.250   0.4136   0.02354   0.01516  -0.1213   0.6766   0.6248
  -1.000   0.4318   0.02381   0.01562  -0.1194   0.6735   0.7065
  -0.750   0.4512   0.02397   0.01587  -0.1174   0.6710   0.7666
  -0.500   0.4713   0.02407   0.01599  -0.1153   0.6691   0.8169
  -0.250   0.4915   0.02414   0.01604  -0.1132   0.6675   0.8637
   0.000   0.5134   0.02411   0.01601  -0.1111   0.6663   0.9290
   0.250   0.5351   0.02546   0.01744  -0.1122   0.6594   0.9998
   0.500   0.5569   0.02600   0.01787  -0.1122   0.6560   0.9998
   0.750   0.5829   0.02635   0.01810  -0.1125   0.6537   0.9998
   1.000   0.6108   0.02662   0.01824  -0.1129   0.6520   0.9998
   1.250   0.6405   0.02678   0.01829  -0.1135   0.6506   0.9998
   1.500   0.6692   0.02700   0.01841  -0.1140   0.6490   0.9998
   2.000   0.6868   0.02998   0.02139  -0.1114   0.6368   0.9998
   2.250   0.7157   0.03016   0.02149  -0.1118   0.6352   0.9998
   2.500   0.7463   0.03022   0.02148  -0.1123   0.6339   0.9998
   3.500   0.8145   0.03398   0.02519  -0.1095   0.6177   0.9998
   4.000   0.8189   0.03815   0.02940  -0.1063   0.6030   0.9998
   4.250   0.8400   0.03887   0.03011  -0.1060   0.6000   0.9998
   4.750   0.8598   0.04193   0.03320  -0.1040   0.5878   0.9998
   5.000   0.8897   0.04188   0.03315  -0.1041   0.5864   0.9998
   6.000   0.9232   0.04833   0.03972  -0.0996   0.5595   0.9998
   6.250   0.9512   0.04831   0.03973  -0.0996   0.5574   0.9998
   6.500   0.9818   0.04803   0.03948  -0.0996   0.5559   0.9998
   7.000   1.0020   0.05078   0.04234  -0.0975   0.5420   0.9998
   7.250   1.0334   0.05031   0.04192  -0.0975   0.5405   0.9998
   7.750   1.0559   0.05273   0.04445  -0.0955   0.5263   0.9998
   8.250   1.0816   0.05478   0.04664  -0.0936   0.5122   0.9998
   8.500   1.1147   0.05380   0.04573  -0.0934   0.5103   0.9998
   9.000   1.1437   0.05523   0.04732  -0.0915   0.4957   0.9998
   9.500   1.1751   0.05626   0.04851  -0.0896   0.4807   0.9998
  10.000   1.2101   0.05678   0.04920  -0.0878   0.4650   0.9998
  10.500   1.2205   0.06010   0.05269  -0.0853   0.4407   0.9998
  11.000   1.2571   0.06057   0.05333  -0.0837   0.4211   0.9998
  11.250   1.2688   0.06164   0.05448  -0.0828   0.4080   0.9998
  11.500   1.2860   0.06207   0.05497  -0.0820   0.3951   0.9998
  11.750   1.3058   0.06215   0.05509  -0.0812   0.3812   0.9998
  12.000   1.3249   0.06230   0.05524  -0.0803   0.3650   0.9998
  12.250   1.3440   0.06240   0.05530  -0.0794   0.3464   0.9998
  12.500   1.3625   0.06249   0.05527  -0.0783   0.3256   0.9998
  12.750   1.3701   0.06400   0.05671  -0.0772   0.3035   0.9998
  13.000   1.3766   0.06561   0.05820  -0.0761   0.2814   0.9998
  13.250   1.3800   0.06769   0.06017  -0.0750   0.2608   0.9998
  13.500   1.3811   0.07013   0.06254  -0.0740   0.2411   0.9998
  13.750   1.3815   0.07269   0.06503  -0.0731   0.2230   0.9998
  14.000   1.3818   0.07534   0.06761  -0.0722   0.2066   0.9998
  14.250   1.3818   0.07809   0.07031  -0.0715   0.1916   0.9998
  14.500   1.3824   0.08083   0.07302  -0.0709   0.1781   0.9998
  14.750   1.3829   0.08360   0.07578  -0.0704   0.1661   0.9998
  15.000   1.3835   0.08640   0.07856  -0.0699   0.1554   0.9998
  15.250   1.3840   0.08923   0.08138  -0.0695   0.1455   0.9998
  15.500   1.3860   0.09196   0.08416  -0.0692   0.1364   0.9998
  15.750   1.3872   0.09476   0.08695  -0.0690   0.1286   0.9998
  16.000   1.3888   0.09757   0.08981  -0.0688   0.1211   0.9998
  16.250   1.3907   0.10033   0.09260  -0.0687   0.1145   0.9998
  16.500   1.3923   0.10318   0.09551  -0.0687   0.1082   0.9998
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