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AH 82-150 A (ah82150a-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: AH 82-150 A (ah82150a-il)
Reynolds number: 200,000
Max Cl/Cd: 72.78 at α=8°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-ah82150a-il-200000.txt
Download as CSV file: xf-ah82150a-il-200000.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 =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.750  -0.1656   0.11753   0.11432  -0.0770   0.9679   0.0474
 -12.500  -0.1578   0.11367   0.11044  -0.0800   0.9644   0.0492
 -12.250  -0.3268   0.12423   0.12100  -0.0616   0.9907   0.0437
 -12.000  -0.3063   0.12071   0.11745  -0.0633   0.9857   0.0450
 -11.750  -0.2914   0.11669   0.11341  -0.0666   0.9802   0.0463
 -11.500  -0.2784   0.11227   0.10896  -0.0707   0.9754   0.0487
 -11.250  -0.2675   0.10716   0.10385  -0.0762   0.9718   0.0511
 -11.000  -0.2688   0.09993   0.09664  -0.0878   0.9657   0.0540
 -10.500  -0.2537   0.08666   0.08335  -0.0995   0.9577   0.0561
 -10.250  -0.2256   0.08572   0.08236  -0.0987   0.9532   0.0593
 -10.000  -0.2140   0.08051   0.07712  -0.1048   0.9473   0.0620
  -9.750  -0.2123   0.07260   0.06919  -0.1156   0.9398   0.0647
  -9.500  -0.2380   0.06436   0.06076  -0.1269   0.9267   0.0663
  -9.250  -0.2680   0.06161   0.05778  -0.1271   0.9133   0.0669
  -9.000  -0.2259   0.04418   0.04058  -0.1226   0.8934   0.0704
  -8.750  -0.2303   0.04168   0.03803  -0.1212   0.8875   0.0715
  -8.500  -0.2948   0.05157   0.04737  -0.1232   0.8900   0.0702
  -8.250  -0.2838   0.04919   0.04495  -0.1226   0.8857   0.0721
  -8.000  -0.2811   0.04711   0.04275  -0.1210   0.8799   0.0743
  -7.750  -0.2810   0.04519   0.04050  -0.1188   0.8739   0.0790
  -7.500  -0.2974   0.03386   0.02760  -0.1123   0.8682   0.0421
  -7.250  -0.2891   0.03072   0.02406  -0.1103   0.8631   0.0433
  -7.000  -0.2709   0.02855   0.02175  -0.1098   0.8595   0.0456
  -6.750  -0.2483   0.02682   0.01976  -0.1092   0.8565   0.0469
  -6.500  -0.2279   0.02548   0.01821  -0.1081   0.8524   0.0485
  -6.250  -0.2063   0.02454   0.01707  -0.1072   0.8482   0.0514
  -6.000  -0.1820   0.02392   0.01617  -0.1066   0.8450   0.0541
  -5.750  -0.1556   0.02195   0.01407  -0.1064   0.8426   0.0568
  -5.500  -0.1321   0.02123   0.01335  -0.1059   0.8394   0.0607
  -5.250  -0.1109   0.02082   0.01287  -0.1050   0.8349   0.0650
  -5.000  -0.0866   0.02032   0.01227  -0.1044   0.8317   0.0679
  -4.750  -0.0641   0.01932   0.01135  -0.1037   0.8289   0.0734
  -4.500  -0.0384   0.01889   0.01085  -0.1034   0.8266   0.0803
  -4.250  -0.0236   0.01849   0.01052  -0.1016   0.8216   0.0862
  -4.000  -0.0021   0.01820   0.01021  -0.1009   0.8180   0.0957
  -3.750   0.0195   0.01756   0.00971  -0.1003   0.8150   0.1184
  -3.500   0.0353   0.01586   0.00906  -0.0996   0.8125   0.3312
  -3.250   0.0387   0.01558   0.01024  -0.0948   0.8073   0.6723
  -3.000   0.0605   0.01636   0.01093  -0.0929   0.8036   0.7202
  -2.750   0.0840   0.01702   0.01152  -0.0910   0.8009   0.7455
  -2.500   0.1083   0.01753   0.01195  -0.0892   0.7986   0.7616
  -2.250   0.1260   0.01816   0.01255  -0.0865   0.7950   0.7758
  -2.000   0.1395   0.01879   0.01316  -0.0833   0.7899   0.7893
  -1.750   0.1555   0.01936   0.01372  -0.0792   0.7868   0.8065
  -1.500   0.1723   0.01985   0.01417  -0.0751   0.7845   0.8276
  -1.250   0.1938   0.02010   0.01436  -0.0724   0.7827   0.8438
  -1.000   0.1917   0.02070   0.01501  -0.0666   0.7750   0.8548
  -0.750   0.2138   0.02070   0.01497  -0.0647   0.7721   0.8651
  -0.500   0.2423   0.02056   0.01473  -0.0650   0.7700   0.8717
  -0.250   0.2740   0.02033   0.01440  -0.0659   0.7683   0.8742
   0.000   0.2733   0.02079   0.01491  -0.0616   0.7598   0.8780
   0.250   0.3038   0.02059   0.01464  -0.0624   0.7572   0.8801
   0.500   0.3377   0.02033   0.01430  -0.0637   0.7553   0.8821
   0.750   0.3712   0.02012   0.01402  -0.0651   0.7533   0.8838
   1.000   0.3761   0.02063   0.01456  -0.0625   0.7444   0.8871
   1.250   0.4100   0.02032   0.01420  -0.0637   0.7422   0.8881
   1.500   0.4450   0.02000   0.01383  -0.0650   0.7403   0.8893
   1.750   0.4531   0.02042   0.01430  -0.0624   0.7323   0.8916
   2.000   0.4853   0.02021   0.01406  -0.0635   0.7292   0.8927
   2.250   0.5214   0.01988   0.01372  -0.0651   0.7270   0.8940
   2.500   0.5586   0.01957   0.01337  -0.0669   0.7252   0.8951
   2.750   0.5674   0.02009   0.01396  -0.0647   0.7165   0.8974
   3.000   0.6033   0.01980   0.01366  -0.0664   0.7138   0.8984
   3.250   0.6416   0.01945   0.01331  -0.0684   0.7117   0.8994
   3.500   0.6579   0.01980   0.01372  -0.0672   0.7043   0.9017
   3.750   0.6891   0.01956   0.01350  -0.0680   0.7005   0.9028
   4.000   0.7262   0.01916   0.01313  -0.0697   0.6979   0.9037
   4.250   0.7482   0.01924   0.01328  -0.0691   0.6920   0.9053
   4.500   0.7757   0.01912   0.01321  -0.0693   0.6866   0.9069
   4.750   0.8131   0.01872   0.01285  -0.0710   0.6837   0.9082
   5.000   0.8360   0.01876   0.01297  -0.0706   0.6773   0.9106
   5.250   0.8659   0.01858   0.01286  -0.0712   0.6717   0.9125
   5.500   0.9061   0.01812   0.01244  -0.0734   0.6685   0.9136
   5.750   0.9250   0.01826   0.01271  -0.0724   0.6599   0.9158
   6.000   0.9608   0.01780   0.01230  -0.0737   0.6552   0.9171
   6.250   0.9817   0.01774   0.01236  -0.0727   0.6471   0.9195
   6.500   1.0158   0.01732   0.01201  -0.0737   0.6410   0.9214
   6.750   1.0376   0.01712   0.01195  -0.0727   0.6310   0.9246
   7.000   1.0648   0.01631   0.01117  -0.0720   0.6157   0.9276
   7.250   1.0852   0.01553   0.01038  -0.0700   0.5929   0.9308
   7.500   1.0999   0.01517   0.01002  -0.0674   0.5683   0.9347
   8.000   1.1135   0.01530   0.01005  -0.0599   0.5036   0.9465
   8.250   1.1140   0.01585   0.01038  -0.0556   0.4575   0.9559
   8.500   1.1130   0.01695   0.01121  -0.0520   0.4028   0.9723
   8.750   1.1053   0.01873   0.01264  -0.0486   0.3390   1.0000
   9.000   1.0905   0.02128   0.01472  -0.0449   0.2605   1.0000
   9.250   1.0678   0.02473   0.01748  -0.0411   0.1603   1.0000
   9.500   1.0476   0.02836   0.02044  -0.0379   0.0695   1.0000
   9.750   1.0425   0.03110   0.02293  -0.0359   0.0416   1.0000
  10.000   1.0501   0.03292   0.02483  -0.0350   0.0360   1.0000
  10.250   1.0516   0.03524   0.02719  -0.0338   0.0319   1.0000
  10.500   1.0592   0.03709   0.02915  -0.0330   0.0302   1.0000
  10.750   1.0649   0.03913   0.03131  -0.0322   0.0284   1.0000
  11.000   1.0699   0.04127   0.03353  -0.0313   0.0274   1.0000
  11.250   1.0752   0.04342   0.03574  -0.0305   0.0265   1.0000
  11.500   1.0800   0.04564   0.03801  -0.0296   0.0256   1.0000
  11.750   1.0865   0.04776   0.04016  -0.0287   0.0249   1.0000
  12.000   1.0986   0.04954   0.04194  -0.0275   0.0241   1.0000
  12.250   1.1207   0.05076   0.04320  -0.0266   0.0233   1.0000
  12.500   1.1366   0.05223   0.04479  -0.0262   0.0224   1.0000
  12.750   1.1573   0.05365   0.04633  -0.0256   0.0217   1.0000
  13.000   1.1835   0.05515   0.04801  -0.0251   0.0215   1.0000
  13.250   1.2083   0.05715   0.05022  -0.0247   0.0214   1.0000
  13.500   1.2297   0.05985   0.05317  -0.0242   0.0217   1.0000
  13.750   1.2441   0.06324   0.05685  -0.0236   0.0221   1.0000
  14.000   1.2538   0.06745   0.06134  -0.0230   0.0227   1.0000
  14.250   1.2799   0.07128   0.06534  -0.0230   0.0241   1.0000
  14.500   1.2549   0.08290   0.07781  -0.0211   0.0315   1.0000
  14.750   1.2323   0.08574   0.08088  -0.0204   0.0311   1.0000
  16.000   0.9522   0.10598   0.10276  -0.0226   0.0276   1.0000
  16.250   0.9227   0.11318   0.11018  -0.0269   0.0280   1.0000
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