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AH 83-150 Q (ah83150q-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: AH 83-150 Q (ah83150q-il)
Reynolds number: 1,000,000
Max Cl/Cd: 134.69 at α=6.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-ah83150q-il-1000000.txt
Download as CSV file: xf-ah83150q-il-1000000.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 =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.2271   0.08413   0.08124  -0.0625   0.6833   0.0083
  -9.250  -0.2271   0.08005   0.07718  -0.0648   0.6818   0.0081
  -9.000  -0.2294   0.07564   0.07280  -0.0675   0.6802   0.0085
  -8.750  -0.2344   0.07077   0.06796  -0.0710   0.6784   0.0085
  -8.500  -0.2516   0.06429   0.06148  -0.0767   0.6767   0.0089
  -8.250  -0.2655   0.06040   0.05755  -0.0779   0.6748   0.0084
  -8.000  -0.2812   0.05662   0.05370  -0.0775   0.6729   0.0086
  -7.750  -0.2855   0.05280   0.04977  -0.0775   0.6710   0.0087
  -7.500  -0.2864   0.04874   0.04558  -0.0771   0.6692   0.0090
  -7.250  -0.3039   0.03800   0.03431  -0.0742   0.6682   0.0100
  -7.000  -0.2922   0.03579   0.03200  -0.0735   0.6667   0.0101
  -6.750  -0.2776   0.03405   0.03015  -0.0730   0.6650   0.0103
  -6.500  -0.2611   0.03233   0.02832  -0.0725   0.6632   0.0105
  -6.250  -0.2433   0.03052   0.02636  -0.0720   0.6615   0.0108
  -6.000  -0.2249   0.02827   0.02390  -0.0712   0.6599   0.0113
  -5.750  -0.2019   0.02635   0.02155  -0.0696   0.6583   0.0127
  -5.500  -0.1869   0.02253   0.01731  -0.0683   0.6565   0.0132
  -5.250  -0.1630   0.02123   0.01594  -0.0683   0.6543   0.0135
  -5.000  -0.1380   0.02029   0.01495  -0.0683   0.6530   0.0140
  -4.750  -0.1124   0.01923   0.01377  -0.0682   0.6516   0.0148
  -4.500  -0.0869   0.01784   0.01201  -0.0676   0.6500   0.0169
  -4.250  -0.0601   0.01685   0.01104  -0.0677   0.6482   0.0175
  -4.000  -0.0329   0.01612   0.01023  -0.0677   0.6464   0.0186
  -3.250   0.0502   0.01189   0.00545  -0.0658   0.6416   0.0101
  -3.000   0.0781   0.01167   0.00519  -0.0658   0.6395   0.0099
  -2.750   0.1044   0.01101   0.00452  -0.0656   0.6377   0.0097
  -2.500   0.1313   0.01051   0.00401  -0.0656   0.6363   0.0096
  -2.000   0.1862   0.00967   0.00313  -0.0656   0.6326   0.0103
  -1.750   0.2143   0.00940   0.00285  -0.0658   0.6306   0.0114
  -1.500   0.2429   0.00923   0.00265  -0.0660   0.6286   0.0127
  -1.250   0.2713   0.00904   0.00243  -0.0662   0.6266   0.0148
  -1.000   0.2992   0.00877   0.00228  -0.0664   0.6241   0.0598
  -0.750   0.3193   0.00663   0.00197  -0.0667   0.6222   0.6288
  -0.500   0.3452   0.00646   0.00226  -0.0662   0.6203   0.7859
  -0.250   0.3730   0.00675   0.00258  -0.0658   0.6180   0.8099
   0.000   0.4000   0.00706   0.00291  -0.0652   0.6157   0.8235
   0.250   0.4268   0.00732   0.00317  -0.0647   0.6134   0.8341
   0.500   0.4540   0.00750   0.00334  -0.0643   0.6112   0.8399
   0.750   0.4830   0.00767   0.00344  -0.0646   0.6084   0.8442
   1.000   0.5118   0.00765   0.00343  -0.0649   0.6063   0.8466
   1.250   0.5405   0.00762   0.00340  -0.0651   0.6036   0.8480
   1.500   0.5697   0.00759   0.00336  -0.0655   0.6007   0.8488
   1.750   0.5989   0.00758   0.00333  -0.0660   0.5978   0.8496
   2.000   0.6279   0.00760   0.00331  -0.0664   0.5949   0.8506
   2.250   0.6570   0.00763   0.00332  -0.0668   0.5920   0.8515
   2.500   0.6864   0.00761   0.00332  -0.0673   0.5889   0.8523
   2.750   0.7157   0.00760   0.00331  -0.0678   0.5856   0.8531
   3.000   0.7448   0.00761   0.00330  -0.0683   0.5822   0.8540
   3.250   0.7736   0.00767   0.00332  -0.0687   0.5784   0.8550
   3.500   0.8029   0.00766   0.00335  -0.0692   0.5750   0.8559
   3.750   0.8321   0.00766   0.00336  -0.0698   0.5709   0.8567
   4.000   0.8611   0.00769   0.00338  -0.0702   0.5666   0.8575
   4.250   0.8899   0.00773   0.00342  -0.0707   0.5618   0.8582
   4.500   0.9188   0.00775   0.00344  -0.0712   0.5546   0.8589
   4.750   0.9471   0.00781   0.00348  -0.0716   0.5468   0.8596
   5.000   0.9755   0.00786   0.00353  -0.0720   0.5380   0.8603
   5.250   1.0034   0.00789   0.00356  -0.0723   0.5309   0.8610
   5.500   1.0310   0.00795   0.00362  -0.0725   0.5223   0.8617
   5.750   1.0585   0.00802   0.00371  -0.0728   0.5131   0.8624
   6.000   1.0854   0.00814   0.00381  -0.0730   0.5036   0.8630
   6.250   1.1121   0.00828   0.00393  -0.0731   0.4921   0.8637
   6.500   1.1381   0.00845   0.00409  -0.0731   0.4783   0.8645
   6.750   1.1635   0.00866   0.00427  -0.0731   0.4637   0.8654
   7.000   1.1882   0.00890   0.00447  -0.0729   0.4480   0.8663
   7.250   1.2117   0.00921   0.00472  -0.0726   0.4301   0.8671
   7.500   1.2345   0.00954   0.00500  -0.0722   0.4099   0.8679
   7.750   1.2538   0.01005   0.00538  -0.0712   0.3826   0.8689
   8.000   1.2708   0.01064   0.00583  -0.0699   0.3515   0.8699
   8.500   1.3040   0.01170   0.00671  -0.0672   0.3057   0.8719
   8.750   1.3184   0.01224   0.00717  -0.0655   0.2863   0.8730
   9.000   1.3266   0.01282   0.00768  -0.0626   0.2682   0.8740
   9.500   1.3336   0.01434   0.00909  -0.0560   0.2330   0.8768
   9.750   1.3361   0.01539   0.01007  -0.0532   0.2146   0.8783
  10.000   1.3380   0.01663   0.01124  -0.0506   0.1963   0.8797
  10.250   1.3390   0.01806   0.01259  -0.0482   0.1777   0.8812
  10.500   1.3436   0.01938   0.01387  -0.0463   0.1633   0.8827
  10.750   1.3474   0.02081   0.01525  -0.0445   0.1486   0.8843
  11.000   1.3519   0.02224   0.01663  -0.0429   0.1359   0.8856
  11.250   1.3574   0.02366   0.01801  -0.0414   0.1250   0.8867
  11.500   1.3678   0.02479   0.01916  -0.0404   0.1190   0.8876
  11.750   1.3735   0.02626   0.02060  -0.0391   0.1099   0.8885
  12.000   1.3804   0.02765   0.02198  -0.0380   0.1010   0.8898
  12.250   1.3878   0.02903   0.02337  -0.0369   0.0935   0.8911
  12.500   1.3930   0.03059   0.02490  -0.0358   0.0849   0.8924
  12.750   1.3983   0.03219   0.02649  -0.0347   0.0762   0.8937
  13.000   1.4029   0.03390   0.02819  -0.0337   0.0669   0.8949
  13.250   1.4071   0.03572   0.02999  -0.0328   0.0587   0.8962
  13.500   1.4108   0.03764   0.03189  -0.0320   0.0515   0.8977
  13.750   1.4166   0.03944   0.03369  -0.0313   0.0468   0.8993
  14.000   1.4218   0.04136   0.03563  -0.0307   0.0421   0.9006
  14.250   1.4279   0.04323   0.03752  -0.0303   0.0387   0.9018
  14.500   1.4320   0.04535   0.03966  -0.0298   0.0351   0.9031
  14.750   1.4412   0.04700   0.04138  -0.0296   0.0338   0.9049
  15.000   1.4474   0.04897   0.04340  -0.0293   0.0317   0.9067
  15.250   1.4517   0.05116   0.04562  -0.0290   0.0292   0.9086
  15.500   1.4583   0.05319   0.04772  -0.0289   0.0276   0.9106
  15.750   1.4658   0.05515   0.04974  -0.0289   0.0263   0.9128
  16.000   1.4708   0.05743   0.05208  -0.0289   0.0246   0.9153
  16.250   1.4736   0.05995   0.05464  -0.0289   0.0224   0.9183
  16.500   1.4802   0.06208   0.05687  -0.0290   0.0212   0.9233
  16.750   1.4833   0.06463   0.05947  -0.0292   0.0187   0.9299
  17.000   1.4863   0.06772   0.06264  -0.0301   0.0148   0.9483
  17.250   1.4833   0.07154   0.06646  -0.0312   0.0096   1.0000
  17.500   1.4785   0.07539   0.07034  -0.0318   0.0067   1.0000
  17.750   1.4751   0.07917   0.07418  -0.0325   0.0055   1.0000
  18.000   1.4712   0.08310   0.07818  -0.0334   0.0048   1.0000
  18.250   1.4678   0.08703   0.08219  -0.0344   0.0042   1.0000
  18.500   1.4660   0.09078   0.08605  -0.0355   0.0039   1.0000
  18.750   1.4622   0.09490   0.09027  -0.0367   0.0037   1.0000
  19.000   1.4605   0.09878   0.09423  -0.0380   0.0037   1.0000
  19.250   1.4521   0.10376   0.09932  -0.0397   0.0033   1.0000
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