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AH 83-159 (ah83159-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: AH 83-159 (ah83159-il)
Reynolds number: 100,000
Max Cl/Cd: 28.99 at α=11°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-ah83159-il-100000-n5.txt
Download as CSV file: xf-ah83159-il-100000-n5.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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -13.000  -0.1209   0.12314   0.11811  -0.0803   0.8514   0.0518
 -12.750  -0.1156   0.12014   0.11510  -0.0814   0.8486   0.0527
 -12.500  -0.2085   0.12299   0.11768  -0.0899   0.8720   0.0494
 -12.250  -0.1894   0.11938   0.11403  -0.0886   0.8680   0.0508
 -12.000  -0.1804   0.11612   0.11076  -0.0894   0.8640   0.0519
 -11.750  -0.1750   0.11269   0.10731  -0.0909   0.8605   0.0524
 -11.500  -0.1720   0.10892   0.10354  -0.0927   0.8571   0.0524
 -11.250  -0.1736   0.10469   0.09935  -0.0952   0.8529   0.0514
 -11.000  -0.1869   0.09402   0.08866  -0.1007   0.8494   0.0281
 -10.750  -0.1820   0.09091   0.08554  -0.1014   0.8459   0.0276
 -10.500  -0.1806   0.08715   0.08178  -0.1029   0.8426   0.0271
 -10.250  -0.1818   0.08304   0.07771  -0.1049   0.8385   0.0266
 -10.000  -0.1860   0.07820   0.07289  -0.1077   0.8346   0.0261
  -9.750  -0.1960   0.07210   0.06678  -0.1121   0.8311   0.0256
  -9.500  -0.2107   0.06690   0.06153  -0.1150   0.8273   0.0251
  -9.250  -0.2275   0.06273   0.05728  -0.1161   0.8223   0.0247
  -9.000  -0.2457   0.05914   0.05357  -0.1154   0.8178   0.0243
  -8.750  -0.2650   0.05631   0.05058  -0.1130   0.8140   0.0240
  -8.500  -0.2782   0.05351   0.04760  -0.1107   0.8091   0.0237
  -8.250  -0.2868   0.05050   0.04433  -0.1084   0.8052   0.0234
  -8.000  -0.2907   0.04751   0.04101  -0.1060   0.8021   0.0231
  -7.750  -0.2905   0.04457   0.03769  -0.1037   0.7992   0.0230
  -7.500  -0.2867   0.04210   0.03489  -0.1015   0.7947   0.0229
  -7.250  -0.2784   0.03974   0.03216  -0.0996   0.7911   0.0229
  -7.000  -0.2659   0.03755   0.02959  -0.0979   0.7883   0.0232
  -6.750  -0.2498   0.03551   0.02715  -0.0965   0.7862   0.0236
  -6.500  -0.2326   0.03401   0.02536  -0.0954   0.7833   0.0245
  -6.250  -0.2148   0.03276   0.02382  -0.0942   0.7794   0.0260
  -6.000  -0.1937   0.03149   0.02218  -0.0931   0.7764   0.0277
  -5.750  -0.1702   0.02998   0.02041  -0.0924   0.7740   0.0286
  -5.500  -0.1460   0.02854   0.01889  -0.0919   0.7721   0.0299
  -5.250  -0.1219   0.02750   0.01774  -0.0914   0.7704   0.0316
  -5.000  -0.1044   0.02698   0.01719  -0.0901   0.7660   0.0335
  -4.750  -0.0838   0.02648   0.01656  -0.0890   0.7627   0.0372
  -4.500  -0.0643   0.02567   0.01578  -0.0880   0.7600   0.0416
  -4.250  -0.0429   0.02504   0.01505  -0.0869   0.7580   0.0471
  -4.000  -0.0213   0.02441   0.01439  -0.0861   0.7563   0.0566
  -3.750  -0.0084   0.02430   0.01429  -0.0841   0.7516   0.0677
  -3.500   0.0085   0.02390   0.01401  -0.0827   0.7479   0.0937
  -3.250   0.0248   0.02301   0.01371  -0.0812   0.7453   0.2016
  -3.000   0.0309   0.02152   0.01354  -0.0780   0.7431   0.4826
  -2.750   0.0471   0.02245   0.01539  -0.0714   0.7418   0.7163
  -2.500   0.0488   0.02348   0.01636  -0.0670   0.7354   0.7630
  -2.250   0.0605   0.02435   0.01707  -0.0634   0.7320   0.8040
  -2.000   0.0776   0.02523   0.01785  -0.0592   0.7298   0.8361
  -1.750   0.1004   0.02571   0.01818  -0.0564   0.7283   0.8626
  -1.500   0.1326   0.02578   0.01805  -0.0563   0.7270   0.8773
  -1.250   0.1242   0.02657   0.01885  -0.0508   0.7190   0.8897
  -1.000   0.1537   0.02660   0.01872  -0.0512   0.7168   0.8965
  -0.750   0.1761   0.02650   0.01849  -0.0504   0.7147   0.9036
  -0.500   0.2107   0.02636   0.01818  -0.0518   0.7134   0.9074
  -0.250   0.1950   0.02720   0.01905  -0.0455   0.7049   0.9172
   0.000   0.2234   0.02722   0.01895  -0.0461   0.7024   0.9207
   0.250   0.2509   0.02713   0.01875  -0.0463   0.7005   0.9243
   0.500   0.2747   0.02698   0.01848  -0.0458   0.6989   0.9284
   1.000   0.2917   0.02804   0.01949  -0.0415   0.6872   0.9381
   1.250   0.3183   0.02792   0.01928  -0.0415   0.6855   0.9411
   1.500   0.3470   0.02776   0.01905  -0.0419   0.6841   0.9435
   2.000   0.3654   0.02905   0.02032  -0.0382   0.6716   0.9519
   2.250   0.3964   0.02888   0.02011  -0.0390   0.6702   0.9538
   2.750   0.4197   0.03026   0.02148  -0.0365   0.6577   0.9613
   3.000   0.4533   0.03010   0.02129  -0.0377   0.6561   0.9627
   3.250   0.4883   0.02987   0.02105  -0.0390   0.6550   0.9642
   3.750   0.5162   0.03129   0.02252  -0.0374   0.6420   0.9712
   4.000   0.5516   0.03108   0.02233  -0.0388   0.6406   0.9724
   4.500   0.5911   0.03242   0.02376  -0.0393   0.6278   0.9789
   4.750   0.6256   0.03211   0.02348  -0.0404   0.6264   0.9804
   5.000   0.6308   0.03364   0.02507  -0.0396   0.6151   0.9859
   5.250   0.6658   0.03326   0.02477  -0.0407   0.6133   0.9886
   5.750   0.6918   0.03429   0.02588  -0.0383   0.5999   1.0000
   6.000   0.7183   0.03394   0.02558  -0.0379   0.5974   1.0000
   6.250   0.7160   0.03523   0.02695  -0.0352   0.5865   1.0000
   6.500   0.7474   0.03475   0.02654  -0.0355   0.5846   1.0000
   7.000   0.7804   0.03566   0.02759  -0.0340   0.5709   1.0000
   7.500   0.8171   0.03647   0.02859  -0.0329   0.5572   1.0000
   7.750   0.8514   0.03570   0.02793  -0.0335   0.5553   1.0000
   8.250   0.8911   0.03628   0.02875  -0.0327   0.5409   1.0000
   8.500   0.8991   0.03749   0.03006  -0.0316   0.5291   1.0000
   9.000   0.9458   0.03746   0.03028  -0.0311   0.5141   1.0000
   9.250   0.9591   0.03825   0.03122  -0.0303   0.5024   1.0000
   9.750   1.0141   0.03735   0.03058  -0.0301   0.4845   1.0000
  10.000   1.0328   0.03762   0.03097  -0.0295   0.4707   1.0000
  10.250   1.0557   0.03752   0.03097  -0.0291   0.4557   1.0000
  10.500   1.0740   0.03782   0.03137  -0.0284   0.4375   1.0000
  10.750   1.0929   0.03804   0.03163  -0.0277   0.4159   1.0000
  11.000   1.1107   0.03831   0.03187  -0.0268   0.3896   1.0000
  11.250   1.1240   0.03901   0.03247  -0.0257   0.3594   1.0000
  11.500   1.1319   0.04025   0.03357  -0.0245   0.3271   1.0000
  12.000   1.1375   0.04399   0.03710  -0.0221   0.2640   1.0000
  12.250   1.1368   0.04636   0.03934  -0.0210   0.2315   1.0000
  12.500   1.1351   0.04894   0.04178  -0.0201   0.2005   1.0000
  12.750   1.1312   0.05185   0.04452  -0.0192   0.1695   1.0000
  13.000   1.1272   0.05491   0.04742  -0.0186   0.1409   1.0000
  13.250   1.1244   0.05796   0.05035  -0.0181   0.1157   1.0000
  13.500   1.1215   0.06114   0.05342  -0.0177   0.0938   1.0000
  13.750   1.1188   0.06441   0.05660  -0.0175   0.0771   1.0000
  14.000   1.1162   0.06775   0.05989  -0.0174   0.0641   1.0000
  14.250   1.1155   0.07097   0.06312  -0.0175   0.0544   1.0000
  14.500   1.1149   0.07426   0.06647  -0.0177   0.0467   1.0000
  14.750   1.1117   0.07796   0.07015  -0.0180   0.0411   1.0000
  15.000   1.1128   0.08119   0.07357  -0.0183   0.0362   1.0000
  15.250   1.1090   0.08511   0.07750  -0.0190   0.0326   1.0000
  15.500   1.1106   0.08837   0.08092  -0.0194   0.0296   1.0000
  15.750   1.1109   0.09189   0.08455  -0.0201   0.0268   1.0000
  16.000   1.1095   0.09564   0.08837  -0.0210   0.0249   1.0000
  16.250   1.1107   0.09905   0.09190  -0.0217   0.0228   1.0000
  16.500   1.1134   0.10228   0.09528  -0.0225   0.0211   1.0000
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