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NASA/AMES A-01 AIRFOIL (ames01-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: NASA/AMES A-01 AIRFOIL (ames01-il)
Reynolds number: 200,000
Max Cl/Cd: 53.31 at α=9.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-ames01-il-200000.txt
Download as CSV file: xf-ames01-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NASA/AMES A-01 AIRFOIL                          
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.6143   0.10553   0.10222  -0.0032   1.0000   0.0546
  -9.750  -0.6245   0.09775   0.09443  -0.0124   1.0000   0.0547
  -9.500  -0.6400   0.09207   0.08867  -0.0175   1.0000   0.0548
  -9.250  -0.6247   0.08660   0.08336  -0.0130   1.0000   0.0564
  -9.000  -0.6055   0.08717   0.08395  -0.0067   1.0000   0.0583
  -8.750  -0.6083   0.08174   0.07854  -0.0119   1.0000   0.0595
  -8.500  -0.6165   0.07629   0.07304  -0.0163   1.0000   0.0606
  -8.250  -0.6209   0.07100   0.06766  -0.0198   1.0000   0.0625
  -8.000  -0.6364   0.06551   0.06161  -0.0241   1.0000   0.0672
  -7.750  -0.5811   0.04616   0.04249  -0.0297   1.0000   0.0698
  -7.500  -0.5703   0.04304   0.03940  -0.0290   1.0000   0.0712
  -7.250  -0.5665   0.04020   0.03652  -0.0273   1.0000   0.0728
  -7.000  -0.5690   0.03769   0.03392  -0.0244   1.0000   0.0748
  -6.750  -0.5739   0.03538   0.03138  -0.0209   1.0000   0.0788
  -6.500  -0.5995   0.04377   0.03886  -0.0185   1.0000   0.0844
  -6.250  -0.5893   0.04171   0.03685  -0.0165   1.0000   0.0865
  -6.000  -0.5870   0.03259   0.02627  -0.0100   1.0000   0.0538
  -5.750  -0.5750   0.02971   0.02310  -0.0077   1.0000   0.0533
  -5.500  -0.5591   0.02860   0.02165  -0.0054   1.0000   0.0544
  -5.250  -0.5433   0.02635   0.01905  -0.0035   1.0000   0.0553
  -5.000  -0.5245   0.02392   0.01636  -0.0021   1.0000   0.0560
  -4.750  -0.5003   0.02215   0.01447  -0.0017   0.9993   0.0575
  -4.500  -0.4659   0.02109   0.01333  -0.0034   0.9966   0.0605
  -4.250  -0.4302   0.02015   0.01224  -0.0050   0.9941   0.0640
  -4.000  -0.3957   0.01924   0.01117  -0.0062   0.9909   0.0664
  -3.750  -0.3609   0.01798   0.00983  -0.0077   0.9881   0.0703
  -3.500  -0.3239   0.01716   0.00905  -0.0098   0.9855   0.0749
  -3.250  -0.2861   0.01650   0.00837  -0.0118   0.9810   0.0796
  -3.000  -0.2428   0.01559   0.00751  -0.0150   0.9758   0.0867
  -2.750  -0.1934   0.01493   0.00687  -0.0193   0.9706   0.0955
  -2.500  -0.1517   0.01423   0.00626  -0.0221   0.9638   0.1086
  -2.250  -0.1121   0.01357   0.00573  -0.0244   0.9575   0.1336
  -2.000  -0.0965   0.01122   0.00542  -0.0227   0.9489   0.5757
  -1.750  -0.0769   0.01054   0.00570  -0.0193   0.9403   0.8133
  -1.500  -0.0395   0.01067   0.00593  -0.0193   0.9325   0.8993
  -1.250  -0.0009   0.01093   0.00615  -0.0198   0.9217   0.9442
  -1.000   0.0524   0.01123   0.00635  -0.0235   0.9141   0.9721
  -0.750   0.1157   0.01137   0.00640  -0.0299   0.9072   0.9926
  -0.500   0.1535   0.01126   0.00622  -0.0317   0.8966   1.0000
  -0.250   0.1710   0.01108   0.00597  -0.0295   0.8848   1.0000
   0.000   0.1888   0.01088   0.00570  -0.0271   0.8733   1.0000
   0.250   0.2096   0.01069   0.00545  -0.0255   0.8601   1.0000
   0.500   0.2302   0.01048   0.00520  -0.0237   0.8461   1.0000
   0.750   0.2507   0.01026   0.00492  -0.0218   0.8306   1.0000
   1.000   0.2715   0.01005   0.00464  -0.0199   0.8132   1.0000
   1.250   0.2939   0.00987   0.00441  -0.0184   0.7909   1.0000
   1.500   0.3161   0.00969   0.00416  -0.0167   0.7617   1.0000
   1.750   0.3379   0.00956   0.00386  -0.0149   0.7133   1.0000
   2.000   0.3589   0.00971   0.00351  -0.0127   0.6077   1.0000
   2.250   0.3818   0.01063   0.00352  -0.0120   0.4461   1.0000
   2.500   0.4065   0.01129   0.00373  -0.0118   0.3807   1.0000
   2.750   0.4314   0.01175   0.00394  -0.0115   0.3524   1.0000
   3.000   0.4564   0.01212   0.00416  -0.0111   0.3346   1.0000
   3.250   0.4813   0.01250   0.00439  -0.0107   0.3219   1.0000
   3.500   0.5062   0.01284   0.00465  -0.0102   0.3113   1.0000
   3.750   0.5313   0.01315   0.00491  -0.0098   0.3018   1.0000
   4.000   0.5560   0.01358   0.00520  -0.0093   0.2936   1.0000
   4.250   0.5814   0.01384   0.00549  -0.0089   0.2858   1.0000
   4.500   0.6063   0.01426   0.00582  -0.0084   0.2794   1.0000
   4.750   0.6317   0.01459   0.00617  -0.0080   0.2727   1.0000
   5.000   0.6568   0.01494   0.00650  -0.0075   0.2661   1.0000
   5.250   0.6819   0.01540   0.00693  -0.0071   0.2604   1.0000
   5.500   0.7073   0.01572   0.00730  -0.0067   0.2542   1.0000
   5.750   0.7324   0.01622   0.00772  -0.0063   0.2484   1.0000
   6.000   0.7578   0.01657   0.00817  -0.0059   0.2424   1.0000
   6.250   0.7832   0.01693   0.00854  -0.0055   0.2363   1.0000
   6.500   0.8084   0.01748   0.00906  -0.0052   0.2307   1.0000
   6.750   0.8338   0.01777   0.00949  -0.0048   0.2241   1.0000
   7.000   0.8590   0.01823   0.00988  -0.0045   0.2180   1.0000
   7.250   0.8840   0.01856   0.01036  -0.0042   0.2111   1.0000
   7.500   0.9090   0.01887   0.01068  -0.0038   0.2045   1.0000
   7.750   0.9337   0.01929   0.01120  -0.0035   0.1978   1.0000
   8.000   0.9583   0.01947   0.01143  -0.0031   0.1902   1.0000
   8.250   0.9824   0.01975   0.01181  -0.0027   0.1824   1.0000
   8.500   1.0064   0.01985   0.01195  -0.0023   0.1742   1.0000
   8.750   1.0302   0.02004   0.01228  -0.0018   0.1650   1.0000
   9.000   1.0535   0.02023   0.01251  -0.0013   0.1561   1.0000
   9.250   1.0765   0.02039   0.01272  -0.0008   0.1456   1.0000
   9.500   1.0992   0.02062   0.01307  -0.0002   0.1330   1.0000
   9.750   1.1205   0.02107   0.01352   0.0004   0.1184   1.0000
  10.000   1.1414   0.02168   0.01420   0.0011   0.1011   1.0000
  10.250   1.1593   0.02264   0.01511   0.0021   0.0853   1.0000
  10.500   1.1749   0.02386   0.01630   0.0034   0.0732   1.0000
  10.750   1.1887   0.02521   0.01771   0.0049   0.0647   1.0000
  11.000   1.1978   0.02692   0.01934   0.0068   0.0587   1.0000
  11.250   1.2124   0.02806   0.02067   0.0082   0.0542   1.0000
  11.500   1.2222   0.02945   0.02209   0.0100   0.0505   1.0000
  11.750   1.2267   0.03132   0.02400   0.0124   0.0477   1.0000
  12.000   1.2340   0.03269   0.02555   0.0144   0.0455   1.0000
  12.250   1.2399   0.03428   0.02726   0.0164   0.0436   1.0000
  12.500   1.2450   0.03599   0.02907   0.0181   0.0419   1.0000
  12.750   1.2485   0.03801   0.03114   0.0197   0.0404   1.0000
  13.000   1.2499   0.04095   0.03414   0.0213   0.0388   1.0000
  13.250   1.2516   0.04299   0.03641   0.0225   0.0380   1.0000
  13.500   1.2516   0.04536   0.03899   0.0235   0.0371   1.0000
  13.750   1.2502   0.04803   0.04184   0.0242   0.0361   1.0000
  14.000   1.2468   0.05103   0.04503   0.0245   0.0354   1.0000
  14.250   1.2417   0.05441   0.04859   0.0244   0.0347   1.0000
  14.500   1.2349   0.05815   0.05252   0.0238   0.0342   1.0000
  14.750   1.2264   0.06233   0.05687   0.0227   0.0338   1.0000
  15.000   1.2159   0.06701   0.06173   0.0210   0.0334   1.0000
  15.250   1.2032   0.07233   0.06723   0.0185   0.0332   1.0000
  15.500   1.1871   0.07849   0.07359   0.0153   0.0331   1.0000
  15.750   1.1671   0.08577   0.08108   0.0111   0.0330   1.0000
  16.000   1.1396   0.09503   0.09059   0.0052   0.0332   1.0000
  16.250   1.0973   0.10809   0.10394  -0.0033   0.0339   1.0000
  16.500   0.9043   0.16200   0.15823  -0.0349   0.0395   1.0000
  16.750   0.8526   0.18894   0.18505  -0.0463   0.0476   1.0000
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