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

AH 94-156 (ah94156-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: AH 94-156 (ah94156-il)
Reynolds number: 50,000
Max Cl/Cd: 6.26 at α=12.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-ah94156-il-50000.txt
Download as CSV file: xf-ah94156-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: AH 94-156                                       
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.4603   0.11912   0.11388  -0.0118   1.0000   0.3019
  -7.750  -0.4835   0.11813   0.11298  -0.0095   1.0000   0.3144
  -7.500  -0.4783   0.11535   0.11022  -0.0071   1.0000   0.3294
  -7.250  -0.4858   0.11324   0.10817  -0.0044   1.0000   0.3454
  -7.000  -0.4977   0.11135   0.10635  -0.0014   1.0000   0.3617
  -6.750  -0.4736   0.10787   0.10284   0.0010   1.0000   0.3849
  -6.500  -0.4803   0.10601   0.10103   0.0042   1.0000   0.4060
  -6.250  -0.5110   0.10520   0.10033   0.0087   1.0000   0.4255
  -6.000  -0.4791   0.10150   0.09659   0.0104   1.0000   0.4521
  -4.750  -0.6343   0.06439   0.05751  -0.0158   1.0000   0.1574
  -4.500  -0.6174   0.05963   0.05218  -0.0156   1.0000   0.1416
  -4.250  -0.6016   0.05609   0.04842  -0.0149   1.0000   0.1370
  -4.000  -0.5804   0.05263   0.04394  -0.0143   1.0000   0.1270
  -3.750  -0.5616   0.04979   0.04084  -0.0136   1.0000   0.1245
  -3.500  -0.5411   0.04735   0.03798  -0.0128   1.0000   0.1225
  -3.250  -0.5201   0.04546   0.03564  -0.0119   1.0000   0.1238
  -3.000  -0.4983   0.04397   0.03362  -0.0111   1.0000   0.1267
  -2.750  -0.4766   0.04236   0.03173  -0.0102   1.0000   0.1294
  -2.500  -0.4553   0.04109   0.03037  -0.0094   1.0000   0.1332
  -2.250  -0.4336   0.04028   0.02932  -0.0085   1.0000   0.1412
  -2.000  -0.4121   0.03941   0.02848  -0.0075   1.0000   0.1522
  -1.750  -0.2341   0.04035   0.03311  -0.0223   1.0000   1.0000
  -1.500  -0.2268   0.04038   0.03273  -0.0201   1.0000   1.0000
  -1.250  -0.2195   0.04044   0.03245  -0.0180   1.0000   1.0000
  -1.000  -0.2120   0.04054   0.03226  -0.0159   1.0000   1.0000
  -0.750  -0.2045   0.04067   0.03213  -0.0138   1.0000   1.0000
  -0.500  -0.1967   0.04083   0.03206  -0.0118   1.0000   1.0000
  -0.250  -0.1888   0.04102   0.03204  -0.0098   1.0000   1.0000
   0.000  -0.1808   0.04124   0.03205  -0.0079   1.0000   1.0000
   0.250  -0.1726   0.04149   0.03211  -0.0061   1.0000   1.0000
   0.500  -0.1642   0.04177   0.03222  -0.0043   1.0000   1.0000
   0.750  -0.1556   0.04209   0.03238  -0.0026   1.0000   1.0000
   1.000  -0.1468   0.04245   0.03259  -0.0010   1.0000   1.0000
   1.250  -0.1376   0.04285   0.03284   0.0006   1.0000   1.0000
   1.500  -0.1277   0.04332   0.03317   0.0019   1.0000   1.0000
   1.750  -0.1172   0.04387   0.03358   0.0031   1.0000   1.0000
   2.000  -0.1058   0.04448   0.03408   0.0041   1.0000   1.0000
   2.250  -0.0938   0.04518   0.03466   0.0049   1.0000   1.0000
   2.500  -0.0679   0.04691   0.03624   0.0029   0.9949   1.0000
   2.750  -0.0319   0.04948   0.03865  -0.0010   0.9839   1.0000
   3.000   0.0012   0.05178   0.04082  -0.0044   0.9712   1.0000
   3.250   0.0313   0.05378   0.04272  -0.0071   0.9576   1.0000
   3.500   0.0586   0.05556   0.04442  -0.0092   0.9434   1.0000
   3.750   0.0824   0.05708   0.04588  -0.0107   0.9295   1.0000
   4.000   0.1051   0.05861   0.04736  -0.0119   0.9155   1.0000
   4.250   0.1254   0.06007   0.04877  -0.0127   0.9025   1.0000
   4.500   0.1462   0.06168   0.05035  -0.0136   0.8900   1.0000
   4.750   0.1699   0.06368   0.05231  -0.0149   0.8791   1.0000
   5.000   0.2023   0.06646   0.05506  -0.0177   0.8674   1.0000
   5.250   0.2162   0.06738   0.05597  -0.0174   0.8540   1.0000
   5.500   0.2300   0.06861   0.05720  -0.0173   0.8418   1.0000
   5.750   0.2473   0.07033   0.05893  -0.0177   0.8314   1.0000
   6.000   0.2791   0.07333   0.06193  -0.0203   0.8214   1.0000
   6.250   0.2929   0.07448   0.06311  -0.0202   0.8084   1.0000
   6.500   0.3031   0.07572   0.06438  -0.0197   0.7969   1.0000
   6.750   0.3225   0.07795   0.06665  -0.0207   0.7881   1.0000
   7.000   0.3535   0.08084   0.06958  -0.0230   0.7762   1.0000
   7.250   0.3573   0.08161   0.07039  -0.0218   0.7643   1.0000
   7.500   0.3697   0.08348   0.07232  -0.0219   0.7548   1.0000
   7.750   0.4001   0.08665   0.07555  -0.0243   0.7447   1.0000
   8.000   0.4092   0.08790   0.07687  -0.0239   0.7325   1.0000
   8.250   0.4168   0.08957   0.07860  -0.0236   0.7220   1.0000
   8.500   0.4391   0.09243   0.08153  -0.0251   0.7133   1.0000
   8.750   0.4656   0.09519   0.08441  -0.0267   0.7003   1.0000
   9.000   0.4624   0.09622   0.08550  -0.0255   0.6901   1.0000
   9.250   0.4761   0.09872   0.08808  -0.0261   0.6813   1.0000
   9.500   0.5023   0.10180   0.09127  -0.0278   0.6697   1.0000
   9.750   0.5110   0.10357   0.09316  -0.0279   0.6576   1.0000
  10.000   0.5144   0.10561   0.09528  -0.0277   0.6479   1.0000
  10.250   0.5324   0.10859   0.09837  -0.0289   0.6387   1.0000
  10.500   0.5555   0.11158   0.10148  -0.0302   0.6259   1.0000
  10.750   0.5583   0.11338   0.10337  -0.0301   0.6146   1.0000
  11.000   0.5635   0.11585   0.10595  -0.0303   0.6050   1.0000
  11.250   0.5817   0.11907   0.10931  -0.0316   0.5951   1.0000
  11.500   0.6013   0.12207   0.11245  -0.0326   0.5818   1.0000
  11.750   0.6196   0.12494   0.11546  -0.0335   0.5676   1.0000
  12.000   0.6124   0.12674   0.11734  -0.0332   0.5575   1.0000
  12.250   0.6209   0.12955   0.12026  -0.0339   0.5459   1.0000
  12.500   0.7139   0.12185   0.11288  -0.0290   0.4414   1.0000
  12.750   0.7587   0.12113   0.11243  -0.0282   0.4169   1.0000
  13.000   0.6803   0.13579   0.12697  -0.0346   0.4757   1.0000
  13.250   0.6870   0.14065   0.13196  -0.0364   0.4776   1.0000
<< Back to AH 94-156 (ah94156-il)

Polar data table (+)

Polar graphs


<< Back to AH 94-156 (ah94156-il)