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AH 82-150 A (ah82150a-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: AH 82-150 A (ah82150a-il)
Reynolds number: 200,000
Max Cl/Cd: 73.36 at α=6.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-ah82150a-il-200000-n5.txt
Download as CSV file: xf-ah82150a-il-200000-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 =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.750  -0.2786   0.09293   0.08918  -0.0901   0.9169   0.0171
 -11.500  -0.2925   0.08181   0.07807  -0.0980   0.9072   0.0176
 -11.000  -0.3426   0.05715   0.05317  -0.1180   0.8853   0.0171
 -10.750  -0.3690   0.05087   0.04665  -0.1214   0.8735   0.0170
 -10.500  -0.3920   0.04641   0.04193  -0.1216   0.8632   0.0169
 -10.250  -0.4179   0.04219   0.03736  -0.1199   0.8543   0.0171
 -10.000  -0.4397   0.03906   0.03390  -0.1164   0.8459   0.0173
  -9.750  -0.4511   0.03608   0.03050  -0.1133   0.8400   0.0175
  -9.500  -0.4547   0.03329   0.02729  -0.1106   0.8337   0.0178
  -9.250  -0.4480   0.03123   0.02498  -0.1089   0.8290   0.0182
  -9.000  -0.4348   0.02994   0.02351  -0.1078   0.8251   0.0187
  -8.750  -0.4202   0.02871   0.02210  -0.1066   0.8207   0.0193
  -8.500  -0.4038   0.02743   0.02058  -0.1056   0.8168   0.0201
  -8.250  -0.3857   0.02607   0.01895  -0.1047   0.8135   0.0211
  -8.000  -0.3658   0.02493   0.01752  -0.1040   0.8100   0.0227
  -7.750  -0.3451   0.02390   0.01622  -0.1032   0.8061   0.0240
  -7.500  -0.3242   0.02271   0.01494  -0.1027   0.8027   0.0254
  -7.250  -0.3015   0.02195   0.01408  -0.1022   0.7999   0.0267
  -7.000  -0.2778   0.02124   0.01323  -0.1019   0.7974   0.0284
  -6.750  -0.2549   0.02065   0.01251  -0.1014   0.7938   0.0307
  -6.500  -0.2314   0.01998   0.01168  -0.1008   0.7903   0.0323
  -6.250  -0.2093   0.01904   0.01072  -0.1003   0.7873   0.0343
  -6.000  -0.1857   0.01853   0.01016  -0.0999   0.7848   0.0366
  -5.750  -0.1613   0.01810   0.00964  -0.0996   0.7825   0.0397
  -5.500  -0.1386   0.01768   0.00914  -0.0990   0.7790   0.0419
  -5.250  -0.1174   0.01704   0.00848  -0.0982   0.7756   0.0445
  -5.000  -0.0941   0.01663   0.00805  -0.0978   0.7728   0.0483
  -4.750  -0.0697   0.01628   0.00762  -0.0975   0.7703   0.0524
  -4.500  -0.0454   0.01587   0.00714  -0.0972   0.7681   0.0565
  -4.250  -0.0227   0.01553   0.00681  -0.0967   0.7647   0.0623
  -4.000   0.0012   0.01523   0.00650  -0.0963   0.7615   0.0714
  -3.750   0.0256   0.01489   0.00620  -0.0961   0.7588   0.0874
  -3.500   0.0500   0.01447   0.00590  -0.0960   0.7563   0.1220
  -3.250   0.0734   0.01383   0.00559  -0.0959   0.7541   0.2121
  -3.000   0.0935   0.01299   0.00534  -0.0956   0.7509   0.3581
  -2.750   0.1088   0.01227   0.00576  -0.0934   0.7477   0.6069
  -2.500   0.1344   0.01254   0.00607  -0.0926   0.7449   0.6768
  -2.250   0.1618   0.01277   0.00620  -0.0924   0.7424   0.7054
  -2.000   0.1879   0.01318   0.00655  -0.0915   0.7402   0.7320
  -1.750   0.2109   0.01371   0.00708  -0.0897   0.7377   0.7551
  -1.500   0.2328   0.01408   0.00745  -0.0880   0.7343   0.7673
  -1.250   0.2569   0.01428   0.00762  -0.0870   0.7312   0.7763
  -1.000   0.2833   0.01436   0.00764  -0.0867   0.7286   0.7824
  -0.750   0.3130   0.01431   0.00748  -0.0875   0.7263   0.7856
  -0.500   0.3413   0.01428   0.00737  -0.0878   0.7239   0.7874
  -0.250   0.3663   0.01431   0.00740  -0.0876   0.7201   0.7889
   0.000   0.3931   0.01431   0.00737  -0.0876   0.7168   0.7904
   0.250   0.4212   0.01428   0.00730  -0.0880   0.7139   0.7920
   0.500   0.4506   0.01424   0.00719  -0.0886   0.7114   0.7934
   0.750   0.4776   0.01425   0.00719  -0.0887   0.7079   0.7952
   1.000   0.5040   0.01427   0.00720  -0.0889   0.7036   0.7971
   1.250   0.5328   0.01423   0.00713  -0.0894   0.7000   0.7986
   1.500   0.5632   0.01417   0.00701  -0.0902   0.6970   0.8001
   1.750   0.5892   0.01420   0.00707  -0.0902   0.6925   0.8016
   2.000   0.6149   0.01421   0.00711  -0.0901   0.6879   0.8028
   2.250   0.6432   0.01418   0.00707  -0.0904   0.6842   0.8040
   2.500   0.6717   0.01416   0.00705  -0.0908   0.6808   0.8051
   2.750   0.6961   0.01423   0.00720  -0.0904   0.6755   0.8064
   3.000   0.7236   0.01423   0.00722  -0.0907   0.6713   0.8077
   3.250   0.7531   0.01420   0.00718  -0.0912   0.6678   0.8092
   3.500   0.7773   0.01429   0.00737  -0.0909   0.6622   0.8111
   3.750   0.8045   0.01431   0.00743  -0.0911   0.6572   0.8128
   4.000   0.8344   0.01428   0.00739  -0.0917   0.6533   0.8142
   4.250   0.8579   0.01439   0.00761  -0.0913   0.6466   0.8157
   4.500   0.8844   0.01439   0.00768  -0.0913   0.6413   0.8168
   4.750   0.9097   0.01444   0.00781  -0.0910   0.6355   0.8181
   5.000   0.9342   0.01449   0.00795  -0.0907   0.6288   0.8195
   5.250   0.9605   0.01452   0.00806  -0.0906   0.6227   0.8211
   5.500   0.9839   0.01461   0.00825  -0.0900   0.6148   0.8230
   5.750   1.0091   0.01466   0.00838  -0.0898   0.6072   0.8250
   6.000   1.0338   0.01472   0.00852  -0.0894   0.5983   0.8268
   6.250   1.0568   0.01483   0.00875  -0.0888   0.5883   0.8287
   6.500   1.0785   0.01489   0.00887  -0.0878   0.5740   0.8305
   6.750   1.0945   0.01492   0.00886  -0.0856   0.5460   0.8322
   7.000   1.1039   0.01517   0.00892  -0.0822   0.5022   0.8344
   7.250   1.1045   0.01571   0.00920  -0.0774   0.4554   0.8371
   7.500   1.1012   0.01654   0.00978  -0.0723   0.4119   0.8405
   8.000   1.0880   0.01897   0.01174  -0.0625   0.3222   0.8476
   8.250   1.0792   0.02057   0.01310  -0.0580   0.2704   0.8514
   8.500   1.0683   0.02257   0.01475  -0.0538   0.2104   0.8554
   8.750   1.0558   0.02494   0.01670  -0.0499   0.1424   0.8593
   9.000   1.0472   0.02722   0.01864  -0.0466   0.0858   0.8628
   9.250   1.0415   0.02947   0.02061  -0.0439   0.0398   0.8669
   9.500   1.0450   0.03119   0.02227  -0.0420   0.0261   0.8710
   9.750   1.0523   0.03264   0.02380  -0.0405   0.0219   0.8751
  10.000   1.0605   0.03403   0.02530  -0.0392   0.0198   0.8801
  10.250   1.0669   0.03562   0.02699  -0.0378   0.0180   0.8861
  10.500   1.0720   0.03728   0.02878  -0.0363   0.0169   0.8930
  11.000   1.0866   0.04032   0.03213  -0.0339   0.0148   0.9144
  11.500   1.0961   0.04394   0.03603  -0.0319   0.0137   1.0000
  11.750   1.1013   0.04613   0.03830  -0.0313   0.0132   1.0000
  12.000   1.1045   0.04855   0.04081  -0.0307   0.0128   1.0000
  12.250   1.1069   0.05112   0.04345  -0.0301   0.0125   1.0000
  12.500   1.1091   0.05374   0.04612  -0.0295   0.0122   1.0000
  12.750   1.1164   0.05590   0.04838  -0.0291   0.0119   1.0000
  13.000   1.1244   0.05801   0.05062  -0.0287   0.0116   1.0000
  13.250   1.1329   0.06011   0.05282  -0.0285   0.0111   1.0000
  13.500   1.1413   0.06223   0.05504  -0.0282   0.0107   1.0000
  13.750   1.1493   0.06442   0.05733  -0.0281   0.0102   1.0000
  14.000   1.1575   0.06664   0.05964  -0.0280   0.0099   1.0000
  14.250   1.1650   0.06897   0.06206  -0.0279   0.0095   1.0000
  14.500   1.1729   0.07130   0.06449  -0.0278   0.0093   1.0000
  14.750   1.1802   0.07372   0.06700  -0.0277   0.0091   1.0000
  15.000   1.1876   0.07621   0.06958  -0.0277   0.0089   1.0000
  15.250   1.1952   0.07879   0.07227  -0.0275   0.0087   1.0000
  15.500   1.2016   0.08172   0.07536  -0.0274   0.0086   1.0000
  15.750   1.2030   0.08514   0.07900  -0.0278   0.0085   1.0000
  16.000   1.2023   0.08892   0.08301  -0.0285   0.0084   1.0000
  16.250   1.1993   0.09310   0.08742  -0.0294   0.0084   1.0000
  16.500   1.1948   0.09758   0.09212  -0.0306   0.0083   1.0000
  16.750   1.1880   0.10251   0.09729  -0.0322   0.0083   1.0000
  17.000   1.1797   0.10779   0.10279  -0.0341   0.0082   1.0000
  17.250   1.1700   0.11343   0.10866  -0.0365   0.0082   1.0000
  17.500   1.1591   0.11949   0.11494  -0.0393   0.0082   1.0000
  17.750   1.1472   0.12592   0.12158  -0.0426   0.0082   1.0000
  18.000   1.1343   0.13280   0.12867  -0.0465   0.0082   1.0000
  18.250   1.1208   0.14005   0.13612  -0.0508   0.0082   1.0000
  18.500   1.1071   0.14766   0.14391  -0.0555   0.0083   1.0000
  18.750   1.0929   0.15573   0.15215  -0.0607   0.0083   1.0000
  19.000   1.0780   0.16445   0.16102  -0.0665   0.0083   1.0000
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