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AH 83-159 (ah83159-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: AH 83-159 (ah83159-il)
Reynolds number: 500,000
Max Cl/Cd: 106.15 at α=7.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-ah83159-il-500000.txt
Download as CSV file: xf-ah83159-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: AH 83-159                                       
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.1695   0.08555   0.08229  -0.1020   0.7858   0.0209
 -10.500  -0.1712   0.08062   0.07739  -0.1048   0.7834   0.0209
 -10.250  -0.1771   0.07387   0.07066  -0.1095   0.7806   0.0210
 -10.000  -0.1903   0.06712   0.06386  -0.1145   0.7777   0.0210
  -9.750  -0.2097   0.06232   0.05897  -0.1167   0.7747   0.0210
  -9.500  -0.2301   0.05868   0.05520  -0.1167   0.7718   0.0210
  -9.250  -0.2459   0.05593   0.05236  -0.1153   0.7688   0.0210
  -9.000  -0.2645   0.05357   0.04992  -0.1123   0.7653   0.0210
  -8.750  -0.2794   0.05128   0.04748  -0.1092   0.7623   0.0211
  -8.500  -0.2866   0.04876   0.04477  -0.1067   0.7597   0.0211
  -8.250  -0.3071   0.04206   0.03795  -0.1045   0.7575   0.0221
  -8.000  -0.2999   0.04004   0.03582  -0.1032   0.7553   0.0224
  -7.750  -0.2902   0.03835   0.03408  -0.1020   0.7528   0.0230
  -7.500  -0.2801   0.03641   0.03200  -0.1006   0.7502   0.0237
  -7.250  -0.2687   0.03433   0.02972  -0.0991   0.7477   0.0246
  -7.000  -0.2772   0.02432   0.01837  -0.0923   0.7455   0.0161
  -6.750  -0.2551   0.02307   0.01688  -0.0915   0.7436   0.0158
  -6.500  -0.2333   0.02126   0.01480  -0.0908   0.7417   0.0159
  -6.250  -0.2102   0.01950   0.01288  -0.0903   0.7398   0.0162
  -6.000  -0.1853   0.01826   0.01149  -0.0899   0.7376   0.0161
  -5.750  -0.1601   0.01719   0.01032  -0.0895   0.7353   0.0160
  -5.500  -0.1358   0.01604   0.00909  -0.0890   0.7331   0.0164
  -5.250  -0.1120   0.01520   0.00820  -0.0885   0.7311   0.0169
  -5.000  -0.0877   0.01462   0.00757  -0.0881   0.7293   0.0177
  -4.750  -0.0632   0.01414   0.00703  -0.0877   0.7276   0.0187
  -4.500  -0.0390   0.01372   0.00658  -0.0873   0.7256   0.0202
  -4.250  -0.0162   0.01312   0.00595  -0.0866   0.7233   0.0225
  -4.000   0.0088   0.01277   0.00560  -0.0864   0.7210   0.0264
  -3.750   0.0337   0.01237   0.00520  -0.0861   0.7190   0.0342
  -3.500   0.0592   0.01200   0.00483  -0.0860   0.7171   0.0486
  -3.250   0.0834   0.01145   0.00452  -0.0858   0.7152   0.1059
  -3.000   0.1038   0.01047   0.00424  -0.0854   0.7134   0.2906
  -2.750   0.1210   0.00914   0.00395  -0.0847   0.7114   0.5664
  -2.500   0.1405   0.00890   0.00440  -0.0828   0.7093   0.7368
  -2.250   0.1675   0.00923   0.00472  -0.0823   0.7070   0.7708
  -2.000   0.1958   0.00952   0.00493  -0.0823   0.7049   0.7893
  -1.750   0.2227   0.00991   0.00528  -0.0817   0.7029   0.7983
  -1.500   0.2493   0.01034   0.00567  -0.0810   0.7011   0.8085
  -1.250   0.2760   0.01077   0.00603  -0.0803   0.6994   0.8195
  -1.000   0.2995   0.01126   0.00651  -0.0787   0.6976   0.8261
  -0.750   0.3252   0.01148   0.00672  -0.0782   0.6953   0.8342
  -0.500   0.3485   0.01169   0.00694  -0.0769   0.6930   0.8383
  -0.250   0.3751   0.01181   0.00703  -0.0766   0.6908   0.8441
   0.000   0.4023   0.01184   0.00701  -0.0767   0.6887   0.8486
   0.250   0.4280   0.01187   0.00702  -0.0761   0.6868   0.8512
   0.500   0.4555   0.01191   0.00700  -0.0761   0.6850   0.8543
   0.750   0.4839   0.01197   0.00702  -0.0766   0.6830   0.8578
   1.000   0.5121   0.01199   0.00704  -0.0772   0.6805   0.8613
   1.250   0.5370   0.01193   0.00700  -0.0768   0.6779   0.8630
   1.500   0.5634   0.01189   0.00696  -0.0767   0.6754   0.8647
   1.750   0.5911   0.01185   0.00690  -0.0769   0.6732   0.8666
   2.000   0.6201   0.01183   0.00684  -0.0774   0.6711   0.8686
   2.250   0.6491   0.01186   0.00684  -0.0780   0.6687   0.8708
   2.500   0.6766   0.01187   0.00689  -0.0785   0.6655   0.8732
   2.750   0.7052   0.01185   0.00688  -0.0791   0.6624   0.8750
   3.000   0.7318   0.01173   0.00677  -0.0791   0.6595   0.8764
   3.250   0.7602   0.01165   0.00666  -0.0794   0.6567   0.8776
   3.500   0.7868   0.01163   0.00666  -0.0795   0.6535   0.8791
   3.750   0.8122   0.01160   0.00669  -0.0793   0.6496   0.8808
   4.000   0.8401   0.01156   0.00667  -0.0797   0.6462   0.8822
   4.250   0.8695   0.01152   0.00662  -0.0804   0.6432   0.8836
   4.500   0.8989   0.01154   0.00664  -0.0811   0.6402   0.8851
   4.750   0.9251   0.01155   0.00673  -0.0813   0.6359   0.8868
   5.000   0.9539   0.01154   0.00676  -0.0820   0.6319   0.8879
   5.250   0.9827   0.01148   0.00670  -0.0825   0.6284   0.8889
   5.500   1.0083   0.01144   0.00672  -0.0824   0.6244   0.8900
   5.750   1.0323   0.01139   0.00675  -0.0820   0.6191   0.8914
   6.000   1.0591   0.01132   0.00670  -0.0821   0.6142   0.8927
   6.250   1.0838   0.01131   0.00676  -0.0818   0.6081   0.8939
   6.500   1.1088   0.01125   0.00675  -0.0816   0.6011   0.8950
   6.750   1.1330   0.01124   0.00679  -0.0813   0.5929   0.8963
   7.000   1.1578   0.01122   0.00678  -0.0811   0.5842   0.8975
   7.250   1.1794   0.01126   0.00691  -0.0803   0.5733   0.8992
   7.500   1.2007   0.01133   0.00701  -0.0795   0.5598   0.9005
   7.750   1.2186   0.01148   0.00712  -0.0780   0.5413   0.9016
   8.000   1.2329   0.01165   0.00730  -0.0760   0.5213   0.9029
   8.250   1.2413   0.01188   0.00751  -0.0727   0.5019   0.9045
   8.500   1.2422   0.01227   0.00786  -0.0682   0.4801   0.9068
   8.750   1.2417   0.01293   0.00844  -0.0638   0.4569   0.9089
   9.000   1.2360   0.01392   0.00933  -0.0591   0.4286   0.9110
   9.250   1.2318   0.01508   0.01038  -0.0550   0.4016   0.9130
   9.500   1.2244   0.01654   0.01170  -0.0509   0.3715   0.9151
   9.750   1.2141   0.01822   0.01323  -0.0465   0.3391   0.9169
  10.000   1.2102   0.01972   0.01462  -0.0433   0.3121   0.9186
  10.250   1.2027   0.02154   0.01629  -0.0398   0.2810   0.9202
  10.500   1.1969   0.02340   0.01798  -0.0368   0.2474   0.9218
  10.750   1.1908   0.02537   0.01978  -0.0339   0.2130   0.9237
  11.000   1.1861   0.02737   0.02160  -0.0314   0.1807   0.9253
  11.250   1.1841   0.02935   0.02342  -0.0293   0.1503   0.9265
  11.500   1.1834   0.03132   0.02526  -0.0275   0.1229   0.9276
  11.750   1.1810   0.03351   0.02726  -0.0257   0.0932   0.9286
  12.000   1.1834   0.03543   0.02907  -0.0244   0.0734   0.9296
  12.250   1.1870   0.03731   0.03089  -0.0233   0.0572   0.9307
  12.500   1.1902   0.03927   0.03278  -0.0223   0.0435   0.9320
  12.750   1.1948   0.04119   0.03468  -0.0214   0.0339   0.9336
  13.000   1.2000   0.04316   0.03664  -0.0207   0.0264   0.9350
  13.250   1.2036   0.04533   0.03882  -0.0200   0.0199   0.9363
  13.500   1.2071   0.04762   0.04115  -0.0194   0.0155   0.9375
  13.750   1.2058   0.05043   0.04400  -0.0186   0.0128   0.9387
  14.000   1.2132   0.05247   0.04615  -0.0184   0.0113   0.9400
  14.250   1.2184   0.05481   0.04855  -0.0183   0.0101   0.9413
  14.500   1.2194   0.05768   0.05150  -0.0181   0.0095   0.9426
  14.750   1.2156   0.06118   0.05513  -0.0180   0.0091   0.9439
  15.000   1.2213   0.06377   0.05782  -0.0183   0.0089   0.9457
  15.250   1.2267   0.06645   0.06061  -0.0188   0.0083   0.9478
  15.500   1.2327   0.06916   0.06343  -0.0194   0.0081   0.9502
  15.750   1.2339   0.07252   0.06690  -0.0200   0.0079   0.9525
  16.000   1.2409   0.07534   0.06980  -0.0210   0.0075   0.9554
  16.250   1.2444   0.07868   0.07323  -0.0222   0.0071   0.9616
  16.500   1.2432   0.08178   0.07643  -0.0224   0.0069   1.0000
  16.750   1.2423   0.08533   0.08009  -0.0230   0.0068   1.0000
  17.000   1.2401   0.08909   0.08394  -0.0237   0.0066   1.0000
  17.250   1.2386   0.09275   0.08770  -0.0244   0.0065   1.0000
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