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AH 94-145 (ah94145-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: AH 94-145 (ah94145-il)
Reynolds number: 50,000
Max Cl/Cd: 14.81 at α=13.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-ah94145-il-50000-n5.txt
Download as CSV file: xf-ah94145-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: AH 94-145                                       
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.1290   0.12099   0.11391  -0.0834   0.8774   0.1129
 -10.500  -0.1354   0.11958   0.11254  -0.0870   0.8712   0.1157
 -10.250  -0.1386   0.11750   0.11048  -0.0901   0.8655   0.1163
  -9.500  -0.1174   0.10715   0.10013  -0.0941   0.8519   0.1174
  -9.250  -0.1049   0.09916   0.09197  -0.0968   0.8483   0.0723
  -9.000  -0.0979   0.09595   0.08875  -0.0978   0.8445   0.0706
  -8.750  -0.0943   0.09283   0.08563  -0.0996   0.8398   0.0697
  -8.500  -0.0922   0.08969   0.08251  -0.1016   0.8349   0.0691
  -7.500  -0.1168   0.07224   0.06495  -0.1187   0.8154   0.0629
  -7.250  -0.1123   0.06861   0.06120  -0.1207   0.8118   0.0627
  -7.000  -0.1099   0.06547   0.05793  -0.1219   0.8075   0.0624
  -6.750  -0.1092   0.06259   0.05490  -0.1226   0.8024   0.0622
  -6.500  -0.1032   0.05915   0.05116  -0.1239   0.7984   0.0623
  -6.250  -0.0924   0.05504   0.04654  -0.1260   0.7952   0.0631
  -6.000  -0.0769   0.05399   0.04553  -0.1254   0.7918   0.0652
  -5.750  -0.0703   0.05264   0.04402  -0.1245   0.7865   0.0668
  -5.500  -0.0546   0.05034   0.04135  -0.1250   0.7828   0.0686
  -5.250  -0.0327   0.04765   0.03816  -0.1260   0.7800   0.0702
  -5.000  -0.0051   0.04497   0.03470  -0.1274   0.7777   0.0738
  -4.750   0.0079   0.04425   0.03393  -0.1264   0.7732   0.0766
  -4.500   0.0234   0.04352   0.03303  -0.1256   0.7688   0.0795
  -4.250   0.0473   0.04234   0.03145  -0.1257   0.7657   0.0843
  -4.000   0.0744   0.04120   0.03003  -0.1262   0.7632   0.0899
  -3.750   0.1037   0.04026   0.02887  -0.1266   0.7611   0.0970
  -3.500   0.1188   0.04008   0.02850  -0.1254   0.7567   0.1031
  -3.250   0.1334   0.04009   0.02850  -0.1242   0.7522   0.1099
  -3.000   0.1562   0.03976   0.02801  -0.1237   0.7492   0.1193
  -2.750   0.1814   0.03944   0.02754  -0.1234   0.7466   0.1316
  -2.500   0.2099   0.03900   0.02706  -0.1236   0.7445   0.1464
  -2.250   0.2222   0.03942   0.02749  -0.1222   0.7398   0.1585
  -2.000   0.2365   0.03981   0.02790  -0.1212   0.7353   0.1748
  -1.750   0.2605   0.03978   0.02792  -0.1212   0.7322   0.2015
  -1.500   0.2898   0.03936   0.02780  -0.1222   0.7298   0.2564
  -1.250   0.3175   0.03818   0.02792  -0.1226   0.7279   0.5081
  -1.000   0.3099   0.03884   0.02925  -0.1165   0.7226   0.6987
  -0.750   0.3042   0.03946   0.03009  -0.1101   0.7178   0.8459
  -0.500   0.3250   0.03973   0.03020  -0.1088   0.7143   0.9998
  -0.250   0.3556   0.04024   0.03035  -0.1097   0.7119   0.9998
   0.000   0.3735   0.04125   0.03112  -0.1094   0.7080   0.9998
   0.250   0.3821   0.04260   0.03232  -0.1083   0.7025   0.9998
   0.500   0.4055   0.04341   0.03291  -0.1085   0.6988   0.9998
   0.750   0.4337   0.04406   0.03334  -0.1091   0.6961   0.9998
   1.000   0.4646   0.04463   0.03372  -0.1100   0.6940   0.9998
   1.250   0.4634   0.04646   0.03548  -0.1080   0.6869   0.9998
   1.500   0.4844   0.04742   0.03630  -0.1079   0.6828   0.9998
   1.750   0.5114   0.04817   0.03691  -0.1084   0.6799   0.9998
   2.000   0.5417   0.04880   0.03741  -0.1091   0.6777   0.9998
   2.500   0.5613   0.05171   0.04020  -0.1071   0.6661   0.9998
   2.750   0.5886   0.05247   0.04087  -0.1076   0.6632   0.9998
   3.000   0.6056   0.05369   0.04203  -0.1072   0.6587   0.9998
   3.250   0.6138   0.05523   0.04356  -0.1061   0.6522   0.9998
   3.500   0.6381   0.05613   0.04440  -0.1062   0.6484   0.9998
   3.750   0.6679   0.05679   0.04501  -0.1068   0.6458   0.9998
   4.000   0.6670   0.05878   0.04702  -0.1050   0.6376   0.9998
   4.250   0.6892   0.05976   0.04798  -0.1050   0.6332   0.9998
   4.500   0.7187   0.06041   0.04860  -0.1054   0.6302   0.9998
   4.750   0.7188   0.06241   0.05065  -0.1038   0.6219   0.9998
   5.000   0.7418   0.06333   0.05157  -0.1038   0.6172   0.9998
   5.250   0.7723   0.06389   0.05213  -0.1042   0.6143   0.9998
   5.500   0.7700   0.06603   0.05432  -0.1025   0.6048   0.9998
   5.750   0.7966   0.06673   0.05506  -0.1027   0.6006   0.9998
   6.000   0.8036   0.06845   0.05682  -0.1016   0.5928   0.9998
   6.250   0.8240   0.06942   0.05784  -0.1013   0.5870   0.9998
   6.500   0.8551   0.06982   0.05828  -0.1016   0.5837   0.9998
   6.750   0.8537   0.07197   0.06052  -0.1001   0.5732   0.9998
   7.000   0.8836   0.07233   0.06094  -0.1002   0.5693   0.9998
   7.250   0.8847   0.07437   0.06307  -0.0989   0.5589   0.9998
   7.500   0.9142   0.07465   0.06342  -0.0989   0.5547   0.9998
   7.750   0.9163   0.07664   0.06551  -0.0976   0.5439   0.9998
   8.000   0.9468   0.07670   0.06567  -0.0976   0.5396   0.9998
   8.250   0.9490   0.07867   0.06774  -0.0963   0.5282   0.9998
   8.500   0.9815   0.07842   0.06759  -0.0962   0.5241   0.9998
   8.750   0.9829   0.08045   0.06975  -0.0950   0.5121   0.9998
   9.000   0.9917   0.08193   0.07134  -0.0940   0.5017   0.9998
   9.250   1.0194   0.08174   0.07128  -0.0935   0.4956   0.9998
   9.500   1.0245   0.08348   0.07313  -0.0924   0.4836   0.9998
  10.000   1.0631   0.08416   0.07410  -0.0907   0.4659   0.9998
  10.250   1.0697   0.08568   0.07576  -0.0896   0.4533   0.9998
  10.500   1.0807   0.08674   0.07695  -0.0886   0.4416   0.9998
  10.750   1.1122   0.08536   0.07576  -0.0876   0.4348   0.9998
  11.000   1.1198   0.08664   0.07719  -0.0864   0.4213   0.9998
  11.250   1.1298   0.08765   0.07834  -0.0853   0.4079   0.9998
  11.500   1.1425   0.08830   0.07917  -0.0842   0.3950   0.9998
  12.000   1.1908   0.08611   0.07732  -0.0815   0.3741   0.9998
  12.500   1.2215   0.08643   0.07796  -0.0790   0.3446   0.9998
  12.750   1.2414   0.08594   0.07758  -0.0777   0.3287   0.9998
  13.000   1.2567   0.08621   0.07792  -0.0765   0.3104   0.9998
  13.250   1.2697   0.08685   0.07862  -0.0753   0.2906   0.9998
  13.500   1.2865   0.08688   0.07860  -0.0740   0.2699   0.9998
  13.750   1.2975   0.08783   0.07945  -0.0728   0.2496   0.9998
  14.000   1.3016   0.08995   0.08153  -0.0719   0.2302   0.9998
  14.250   1.3057   0.09212   0.08362  -0.0712   0.2127   0.9998
  14.500   1.3084   0.09455   0.08601  -0.0705   0.1969   0.9998
  14.750   1.3106   0.09715   0.08857  -0.0700   0.1828   0.9998
  15.000   1.3125   0.09985   0.09125  -0.0697   0.1701   0.9998
  15.250   1.3153   0.10246   0.09384  -0.0694   0.1589   0.9998
  15.500   1.3196   0.10477   0.09607  -0.0690   0.1488   0.9998
  15.750   1.3206   0.10791   0.09935  -0.0691   0.1393   0.9998
  16.000   1.3240   0.11059   0.10209  -0.0690   0.1311   0.9998
  16.250   1.3285   0.11302   0.10452  -0.0690   0.1234   0.9998
  16.500   1.3297   0.11627   0.10794  -0.0693   0.1166   0.9998
  16.750   1.3358   0.11848   0.11015  -0.0693   0.1104   0.9998
  17.000   1.3363   0.12197   0.11383  -0.0699   0.1049   0.9998
  17.250   1.3382   0.12513   0.11712  -0.0706   0.0997   0.9998
  17.500   1.3454   0.12724   0.11925  -0.0706   0.0951   0.9998
  17.750   1.3385   0.13238   0.12472  -0.0725   0.0913   0.9998
  18.000   1.3379   0.13618   0.12867  -0.0738   0.0876   0.9998
  18.250   1.3488   0.13753   0.12996  -0.0737   0.0838   0.9998
  18.500   1.3317   0.14509   0.13791  -0.0774   0.0818   0.9998
  18.750   1.3125   0.15351   0.14663  -0.0820   0.0799   0.9998
  19.000   1.2879   0.16377   0.15715  -0.0881   0.0784   0.9998
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