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AH 82-150 A (ah82150a-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: AH 82-150 A (ah82150a-il)
Reynolds number: 50,000
Max Cl/Cd: 20.22 at α=10.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-ah82150a-il-50000-n5.txt
Download as CSV file: xf-ah82150a-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: AH 82-150 A                                     
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -11.500  -0.3575   0.12577   0.11929  -0.0560   1.0000   0.0669
 -11.250  -0.3607   0.12414   0.11773  -0.0527   1.0000   0.0650
 -11.000  -0.3714   0.12245   0.11612  -0.0502   1.0000   0.0635
 -10.750  -0.3726   0.11863   0.11234  -0.0516   0.9970   0.0615
 -10.250  -0.3859   0.10302   0.09678  -0.0669   0.9834   0.0543
 -10.000  -0.3812   0.09808   0.09183  -0.0701   0.9772   0.0539
  -9.750  -0.3775   0.09241   0.08614  -0.0750   0.9719   0.0534
  -9.500  -0.3825   0.08693   0.08065  -0.0793   0.9646   0.0530
  -9.250  -0.3901   0.08135   0.07499  -0.0842   0.9581   0.0527
  -9.000  -0.4066   0.07721   0.07078  -0.0861   0.9490   0.0526
  -8.750  -0.4184   0.07307   0.06649  -0.0882   0.9417   0.0524
  -8.500  -0.4316   0.06966   0.06291  -0.0877   0.9326   0.0524
  -8.250  -0.4419   0.06587   0.05881  -0.0878   0.9256   0.0529
  -8.000  -0.4500   0.06278   0.05540  -0.0864   0.9181   0.0534
  -7.750  -0.4484   0.05905   0.05115  -0.0864   0.9130   0.0542
  -7.500  -0.4529   0.05654   0.04839  -0.0836   0.9057   0.0549
  -7.250  -0.4405   0.05342   0.04498  -0.0836   0.9015   0.0558
  -7.000  -0.4285   0.05082   0.04208  -0.0829   0.8972   0.0568
  -6.750  -0.4215   0.04883   0.03982  -0.0808   0.8913   0.0578
  -6.500  -0.4024   0.04672   0.03738  -0.0807   0.8875   0.0607
  -6.250  -0.3773   0.04437   0.03449  -0.0814   0.8847   0.0648
  -6.000  -0.3713   0.04300   0.03269  -0.0782   0.8785   0.0666
  -5.750  -0.3487   0.04107   0.03035  -0.0777   0.8748   0.0685
  -5.500  -0.3211   0.03958   0.02877  -0.0783   0.8719   0.0730
  -5.250  -0.2968   0.03850   0.02739  -0.0779   0.8685   0.0790
  -5.000  -0.2810   0.03765   0.02632  -0.0757   0.8635   0.0822
  -4.750  -0.2548   0.03670   0.02537  -0.0752   0.8603   0.0868
  -4.500  -0.2246   0.03602   0.02445  -0.0753   0.8575   0.0963
  -4.250  -0.2004   0.03537   0.02379  -0.0748   0.8544   0.1049
  -4.000  -0.1924   0.03510   0.02342  -0.0715   0.8487   0.1108
  -3.750  -0.1722   0.03453   0.02285  -0.0706   0.8449   0.1251
  -3.500  -0.1482   0.03374   0.02220  -0.0706   0.8419   0.1489
  -3.250  -0.1423   0.03325   0.02188  -0.0677   0.8364   0.1772
  -3.000  -0.1328   0.03190   0.02138  -0.0661   0.8317   0.2976
  -2.500  -0.1272   0.03278   0.02380  -0.0530   0.8229   0.7357
  -2.250  -0.1229   0.03364   0.02454  -0.0472   0.8176   0.7802
  -2.000  -0.1141   0.03452   0.02532  -0.0405   0.8139   0.8318
  -1.750  -0.0396   0.03598   0.02645  -0.0428   0.8140   0.9145
  -1.500   0.0236   0.03616   0.02623  -0.0495   0.8125   0.9296
  -1.250   0.0462   0.03637   0.02625  -0.0500   0.8069   0.9353
  -1.000   0.0679   0.03649   0.02618  -0.0499   0.8021   0.9411
  -0.750   0.0998   0.03652   0.02601  -0.0516   0.7988   0.9450
  -0.500   0.1202   0.03678   0.02612  -0.0516   0.7934   0.9494
  -0.250   0.1385   0.03699   0.02621  -0.0512   0.7878   0.9541
   0.000   0.1668   0.03707   0.02615  -0.0521   0.7841   0.9577
   0.250   0.1855   0.03742   0.02641  -0.0519   0.7779   0.9615
   0.500   0.2084   0.03767   0.02655  -0.0523   0.7725   0.9650
   0.750   0.2407   0.03778   0.02656  -0.0538   0.7691   0.9678
   1.000   0.2498   0.03827   0.02701  -0.0522   0.7613   0.9726
   1.250   0.2792   0.03848   0.02715  -0.0534   0.7565   0.9754
   1.500   0.3061   0.03875   0.02736  -0.0543   0.7517   0.9788
   1.750   0.3200   0.03923   0.02783  -0.0534   0.7441   0.9838
   2.000   0.3544   0.03936   0.02791  -0.0552   0.7402   0.9863
   2.250   0.3649   0.03999   0.02855  -0.0540   0.7316   0.9922
   2.500   0.3955   0.04018   0.02873  -0.0553   0.7268   0.9965
   2.750   0.3979   0.04071   0.02925  -0.0524   0.7183   1.0000
   3.000   0.4129   0.04083   0.02937  -0.0508   0.7125   1.0000
   3.250   0.4058   0.04126   0.02980  -0.0462   0.7034   1.0000
   3.500   0.4238   0.04135   0.02990  -0.0450   0.6978   1.0000
   3.750   0.4226   0.04186   0.03042  -0.0416   0.6884   1.0000
   4.000   0.4482   0.04201   0.03057  -0.0416   0.6833   1.0000
   4.250   0.4547   0.04272   0.03131  -0.0398   0.6737   1.0000
   4.500   0.4845   0.04291   0.03155  -0.0405   0.6688   1.0000
   4.750   0.4946   0.04374   0.03241  -0.0394   0.6589   1.0000
   5.000   0.5271   0.04389   0.03262  -0.0404   0.6542   1.0000
   5.250   0.5381   0.04483   0.03362  -0.0396   0.6437   1.0000
   5.500   0.5728   0.04490   0.03379  -0.0408   0.6394   1.0000
   5.750   0.5838   0.04596   0.03492  -0.0401   0.6284   1.0000
   6.250   0.6304   0.04708   0.03623  -0.0406   0.6129   1.0000
   6.500   0.6455   0.04809   0.03734  -0.0403   0.6027   1.0000
   6.750   0.6785   0.04814   0.03755  -0.0411   0.5974   1.0000
   7.000   0.6905   0.04936   0.03887  -0.0406   0.5861   1.0000
   7.500   0.7377   0.05045   0.04025  -0.0409   0.5699   1.0000
   7.750   0.7511   0.05165   0.04163  -0.0405   0.5588   1.0000
   8.000   0.7866   0.05131   0.04149  -0.0412   0.5540   1.0000
   8.250   0.7976   0.05270   0.04302  -0.0406   0.5419   1.0000
   8.500   0.8117   0.05387   0.04436  -0.0401   0.5306   1.0000
   8.750   0.8475   0.05326   0.04403  -0.0404   0.5254   1.0000
   9.000   0.8587   0.05463   0.04557  -0.0398   0.5130   1.0000
   9.250   0.8724   0.05581   0.04694  -0.0392   0.5012   1.0000
   9.500   0.9094   0.05470   0.04613  -0.0391   0.4956   1.0000
  10.500   0.9998   0.05260   0.04514  -0.0342   0.4356   1.0000
  10.750   1.0130   0.05010   0.04249  -0.0301   0.3739   1.0000
  11.000   1.0155   0.05081   0.04282  -0.0276   0.3041   1.0000
  11.250   1.0139   0.05285   0.04443  -0.0258   0.2312   1.0000
  11.500   1.0012   0.05649   0.04747  -0.0243   0.1574   1.0000
  11.750   0.9868   0.06089   0.05138  -0.0236   0.1094   1.0000
  12.000   0.9756   0.06529   0.05548  -0.0233   0.0830   1.0000
  12.250   0.9694   0.06930   0.05938  -0.0232   0.0692   1.0000
  12.500   0.9656   0.07310   0.06314  -0.0232   0.0612   1.0000
  12.750   0.9652   0.07657   0.06669  -0.0233   0.0554   1.0000
  13.000   0.9640   0.08015   0.07024  -0.0234   0.0519   1.0000
  13.250   0.9693   0.08292   0.07321  -0.0233   0.0484   1.0000
  13.500   0.9743   0.08574   0.07614  -0.0233   0.0448   1.0000
  13.750   0.9791   0.08854   0.07897  -0.0234   0.0421   1.0000
  14.000   0.9893   0.09068   0.08125  -0.0231   0.0396   1.0000
  14.250   1.0039   0.09232   0.08312  -0.0223   0.0375   1.0000
  14.500   1.0212   0.09374   0.08475  -0.0214   0.0359   1.0000
  14.750   1.0394   0.09528   0.08656  -0.0205   0.0346   1.0000
  15.000   1.0556   0.09727   0.08876  -0.0200   0.0336   1.0000
  15.250   1.0676   0.09988   0.09152  -0.0199   0.0325   1.0000
  15.500   1.0751   0.10331   0.09511  -0.0202   0.0315   1.0000
  15.750   1.0701   0.10817   0.10030  -0.0218   0.0311   1.0000
  16.000   1.0618   0.11360   0.10605  -0.0239   0.0308   1.0000
  16.250   1.0514   0.11956   0.11229  -0.0266   0.0306   1.0000
  16.500   1.0396   0.12599   0.11897  -0.0299   0.0306   1.0000
  16.750   1.0264   0.13301   0.12622  -0.0338   0.0306   1.0000
  17.000   1.0120   0.14068   0.13408  -0.0384   0.0307   1.0000
  17.250   0.9983   0.14869   0.14225  -0.0434   0.0309   1.0000
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