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AH 83-150 Q (ah83150q-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: AH 83-150 Q (ah83150q-il)
Reynolds number: 100,000
Max Cl/Cd: 35.36 at α=9.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-ah83150q-il-100000-n5.txt
Download as CSV file: xf-ah83150q-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: AH 83-150 Q                                     
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.2074   0.09890   0.09355  -0.0639   0.7835   0.0555
  -9.500  -0.2061   0.09547   0.09012  -0.0659   0.7807   0.0569
  -9.250  -0.2182   0.09135   0.08607  -0.0722   0.7771   0.0597
  -9.000  -0.2375   0.08630   0.08105  -0.0799   0.7732   0.0602
  -8.750  -0.2533   0.08294   0.07763  -0.0824   0.7697   0.0604
  -8.250  -0.1911   0.05675   0.05161  -0.0830   0.7574   0.0321
  -7.750  -0.2503   0.06269   0.05710  -0.0847   0.7582   0.0326
  -7.250  -0.2520   0.05428   0.04813  -0.0837   0.7523   0.0252
  -7.000  -0.2436   0.05174   0.04546  -0.0831   0.7501   0.0248
  -6.750  -0.2352   0.04899   0.04251  -0.0824   0.7475   0.0242
  -6.500  -0.2248   0.04621   0.03949  -0.0818   0.7442   0.0235
  -6.250  -0.2131   0.04334   0.03631  -0.0809   0.7409   0.0228
  -6.000  -0.1995   0.04041   0.03298  -0.0797   0.7381   0.0221
  -5.750  -0.1833   0.03754   0.02960  -0.0784   0.7358   0.0214
  -5.500  -0.1640   0.03499   0.02639  -0.0769   0.7338   0.0207
  -5.250  -0.1423   0.03318   0.02423  -0.0762   0.7312   0.0205
  -5.000  -0.1195   0.03163   0.02239  -0.0757   0.7278   0.0205
  -4.750  -0.0959   0.03011   0.02064  -0.0752   0.7248   0.0207
  -4.500  -0.0717   0.02890   0.01929  -0.0748   0.7222   0.0214
  -4.250  -0.0467   0.02795   0.01821  -0.0745   0.7200   0.0228
  -4.000  -0.0206   0.02698   0.01702  -0.0739   0.7181   0.0244
  -3.750   0.0050   0.02616   0.01601  -0.0734   0.7154   0.0254
  -3.500   0.0283   0.02529   0.01517  -0.0729   0.7118   0.0261
  -3.250   0.0514   0.02461   0.01450  -0.0723   0.7088   0.0271
  -3.000   0.0746   0.02405   0.01389  -0.0716   0.7062   0.0284
  -2.750   0.0982   0.02352   0.01324  -0.0709   0.7040   0.0303
  -2.500   0.1225   0.02302   0.01265  -0.0702   0.7020   0.0336
  -2.250   0.1450   0.02284   0.01244  -0.0696   0.6986   0.0403
  -2.000   0.1669   0.02264   0.01228  -0.0689   0.6949   0.0512
  -1.750   0.1781   0.02097   0.01209  -0.0669   0.6917   0.3607
  -1.500   0.1721   0.02120   0.01390  -0.0570   0.6891   0.8028
  -1.250   0.2030   0.02247   0.01512  -0.0506   0.6876   0.9100
  -1.000   0.2445   0.02242   0.01479  -0.0527   0.6860   0.9214
  -0.750   0.2693   0.02271   0.01495  -0.0529   0.6818   0.9294
  -0.500   0.2965   0.02287   0.01498  -0.0534   0.6778   0.9338
  -0.250   0.3277   0.02289   0.01485  -0.0545   0.6748   0.9372
   0.000   0.3555   0.02286   0.01467  -0.0548   0.6724   0.9406
   0.250   0.3793   0.02279   0.01446  -0.0541   0.6703   0.9443
   0.500   0.3992   0.02324   0.01489  -0.0539   0.6649   0.9476
   0.750   0.4251   0.02344   0.01502  -0.0543   0.6608   0.9501
   1.000   0.4521   0.02345   0.01495  -0.0545   0.6578   0.9524
   1.250   0.4798   0.02338   0.01477  -0.0547   0.6556   0.9546
   1.500   0.4949   0.02375   0.01513  -0.0532   0.6509   0.9581
   1.750   0.5153   0.02416   0.01554  -0.0529   0.6455   0.9609
   2.000   0.5446   0.02418   0.01550  -0.0536   0.6424   0.9626
   2.250   0.5742   0.02407   0.01533  -0.0541   0.6401   0.9639
   2.750   0.6123   0.02496   0.01626  -0.0530   0.6291   0.9701
   3.000   0.6380   0.02488   0.01616  -0.0528   0.6262   0.9722
   3.250   0.6695   0.02469   0.01593  -0.0534   0.6241   0.9732
   3.500   0.6840   0.02566   0.01700  -0.0531   0.6154   0.9768
   3.750   0.7132   0.02562   0.01698  -0.0536   0.6119   0.9789
   4.000   0.7451   0.02535   0.01669  -0.0542   0.6095   0.9804
   4.500   0.7834   0.02624   0.01769  -0.0534   0.5969   0.9869
   4.750   0.8172   0.02588   0.01737  -0.0543   0.5945   0.9886
   5.250   0.8553   0.02671   0.01834  -0.0534   0.5814   0.9991
   5.500   0.8852   0.02623   0.01787  -0.0533   0.5791   1.0000
   5.750   0.8500   0.02764   0.01934  -0.0448   0.5674   1.0000
   6.000   0.8808   0.02710   0.01886  -0.0448   0.5649   1.0000
   6.500   0.8964   0.02796   0.01982  -0.0400   0.5505   1.0000
   7.000   0.9263   0.02878   0.02078  -0.0379   0.5358   1.0000
   7.500   0.9642   0.02937   0.02150  -0.0368   0.5208   1.0000
   7.750   0.9690   0.03074   0.02294  -0.0356   0.5086   1.0000
   8.250   1.0204   0.03020   0.02255  -0.0351   0.4914   1.0000
   8.500   1.0330   0.03101   0.02342  -0.0343   0.4784   1.0000
   8.750   1.0491   0.03159   0.02408  -0.0337   0.4663   1.0000
   9.000   1.0717   0.03168   0.02424  -0.0333   0.4554   1.0000
   9.250   1.1019   0.03116   0.02376  -0.0332   0.4458   1.0000
   9.500   1.1169   0.03191   0.02459  -0.0326   0.4324   1.0000
   9.750   1.1340   0.03249   0.02522  -0.0320   0.4189   1.0000
  10.000   1.1514   0.03305   0.02582  -0.0314   0.4047   1.0000
  10.250   1.1680   0.03368   0.02647  -0.0308   0.3897   1.0000
  10.500   1.1829   0.03445   0.02727  -0.0300   0.3741   1.0000
  10.750   1.1962   0.03535   0.02817  -0.0293   0.3577   1.0000
  11.250   1.2150   0.03787   0.03068  -0.0275   0.3233   1.0000
  11.500   1.2201   0.03953   0.03233  -0.0266   0.3047   1.0000
  11.750   1.2244   0.04129   0.03405  -0.0257   0.2855   1.0000
  12.000   1.2271   0.04319   0.03590  -0.0248   0.2663   1.0000
  12.250   1.2285   0.04534   0.03802  -0.0240   0.2477   1.0000
  12.500   1.2301   0.04757   0.04023  -0.0234   0.2302   1.0000
  12.750   1.2317   0.04989   0.04252  -0.0229   0.2138   1.0000
  13.000   1.2333   0.05227   0.04489  -0.0224   0.1990   1.0000
  13.250   1.2353   0.05471   0.04733  -0.0221   0.1856   1.0000
  13.500   1.2372   0.05723   0.04985  -0.0219   0.1733   1.0000
  13.750   1.2388   0.05983   0.05248  -0.0218   0.1624   1.0000
  14.000   1.2401   0.06255   0.05521  -0.0218   0.1519   1.0000
  14.250   1.2425   0.06524   0.05798  -0.0218   0.1420   1.0000
  14.500   1.2439   0.06806   0.06084  -0.0220   0.1334   1.0000
  14.750   1.2444   0.07107   0.06389  -0.0222   0.1250   1.0000
  15.000   1.2464   0.07400   0.06692  -0.0225   0.1170   1.0000
  15.250   1.2451   0.07734   0.07024  -0.0230   0.1100   1.0000
  15.500   1.2473   0.08038   0.07345  -0.0235   0.1025   1.0000
  15.750   1.2465   0.08374   0.07682  -0.0241   0.0970   1.0000
  16.000   1.2486   0.08689   0.08015  -0.0247   0.0907   1.0000
  16.250   1.2474   0.09043   0.08372  -0.0255   0.0858   1.0000
  16.500   1.2494   0.09364   0.08707  -0.0263   0.0809   1.0000
  16.750   1.2493   0.09717   0.09070  -0.0272   0.0765   1.0000
  17.000   1.2498   0.10054   0.09406  -0.0282   0.0731   1.0000
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