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NASA/AMES A-01 AIRFOIL (ames01-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: NASA/AMES A-01 AIRFOIL (ames01-il)
Reynolds number: 500,000
Max Cl/Cd: 74.59 at α=8°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-ames01-il-500000-n5.txt
Download as CSV file: xf-ames01-il-500000-n5.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 =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -14.250  -1.1853   0.05054   0.04758  -0.0243   1.0000   0.0077
 -14.000  -1.2128   0.04468   0.04143  -0.0254   1.0000   0.0076
 -13.750  -1.2293   0.04086   0.03737  -0.0238   1.0000   0.0077
 -13.500  -1.2381   0.03809   0.03438  -0.0211   1.0000   0.0078
 -13.250  -1.2358   0.03577   0.03188  -0.0194   1.0000   0.0080
 -13.000  -1.2275   0.03381   0.02975  -0.0180   1.0000   0.0082
 -12.750  -1.2155   0.03211   0.02789  -0.0169   1.0000   0.0085
 -12.500  -1.2012   0.03053   0.02614  -0.0159   1.0000   0.0087
 -12.250  -1.1850   0.02909   0.02453  -0.0151   1.0000   0.0091
 -12.000  -1.1672   0.02773   0.02300  -0.0144   1.0000   0.0094
 -11.750  -1.1482   0.02645   0.02154  -0.0138   1.0000   0.0098
 -11.500  -1.1278   0.02526   0.02018  -0.0132   1.0000   0.0101
 -11.250  -1.1056   0.02422   0.01900  -0.0130   0.9822   0.0104
 -11.000  -1.0835   0.02340   0.01809  -0.0125   0.9709   0.0108
 -10.750  -1.0624   0.02268   0.01725  -0.0116   0.9629   0.0111
 -10.500  -1.0411   0.02199   0.01646  -0.0107   0.9571   0.0115
 -10.250  -1.0193   0.02132   0.01567  -0.0099   0.9520   0.0119
 -10.000  -0.9981   0.02065   0.01488  -0.0089   0.9472   0.0123
  -9.750  -0.9754   0.01999   0.01410  -0.0082   0.9430   0.0128
  -9.500  -0.9521   0.01935   0.01334  -0.0075   0.9389   0.0131
  -9.250  -0.9290   0.01877   0.01266  -0.0068   0.9352   0.0135
  -9.000  -0.9057   0.01829   0.01211  -0.0060   0.9318   0.0140
  -8.750  -0.8803   0.01783   0.01160  -0.0057   0.9282   0.0146
  -8.500  -0.8552   0.01738   0.01109  -0.0053   0.9247   0.0153
  -8.250  -0.8303   0.01696   0.01058  -0.0048   0.9215   0.0160
  -8.000  -0.8058   0.01654   0.01007  -0.0042   0.9184   0.0167
  -7.750  -0.7801   0.01607   0.00954  -0.0039   0.9153   0.0174
  -7.500  -0.7539   0.01567   0.00912  -0.0037   0.9121   0.0181
  -7.250  -0.7279   0.01530   0.00870  -0.0033   0.9088   0.0188
  -7.000  -0.7022   0.01495   0.00830  -0.0029   0.9058   0.0196
  -6.500  -0.6496   0.01422   0.00743  -0.0023   0.8999   0.0211
  -6.250  -0.6229   0.01383   0.00701  -0.0021   0.8966   0.0219
  -6.000  -0.5961   0.01354   0.00672  -0.0019   0.8934   0.0231
  -5.750  -0.5694   0.01329   0.00645  -0.0017   0.8905   0.0243
  -5.500  -0.5428   0.01306   0.00617  -0.0014   0.8879   0.0258
  -5.250  -0.5147   0.01282   0.00590  -0.0014   0.8845   0.0270
  -5.000  -0.4875   0.01250   0.00560  -0.0013   0.8811   0.0290
  -4.750  -0.4601   0.01230   0.00540  -0.0012   0.8776   0.0308
  -4.500  -0.4333   0.01213   0.00519  -0.0008   0.8738   0.0328
  -4.250  -0.4054   0.01191   0.00494  -0.0008   0.8683   0.0341
  -4.000  -0.3789   0.01154   0.00456  -0.0004   0.8620   0.0364
  -3.750  -0.3520   0.01130   0.00431  -0.0001   0.8560   0.0385
  -3.500  -0.3241   0.01109   0.00409   0.0000   0.8485   0.0409
  -3.250  -0.2971   0.01091   0.00385   0.0004   0.8424   0.0427
  -3.000  -0.2690   0.01065   0.00358   0.0004   0.8344   0.0449
  -2.750  -0.2419   0.01042   0.00333   0.0007   0.8268   0.0481
  -2.500  -0.2137   0.01023   0.00314   0.0007   0.8170   0.0515
  -2.250  -0.1857   0.01009   0.00295   0.0009   0.8073   0.0544
  -2.000  -0.1580   0.00989   0.00274   0.0010   0.7965   0.0594
  -1.750  -0.1299   0.00973   0.00257   0.0011   0.7829   0.0656
  -1.500  -0.1019   0.00957   0.00240   0.0012   0.7672   0.0750
  -1.250  -0.0738   0.00940   0.00224   0.0013   0.7502   0.0922
  -1.000  -0.0464   0.00906   0.00207   0.0013   0.7293   0.1541
  -0.750  -0.0206   0.00843   0.00189   0.0014   0.7049   0.3043
  -0.500   0.0049   0.00785   0.00174   0.0016   0.6723   0.4625
  -0.250   0.0299   0.00741   0.00166   0.0020   0.6263   0.6083
   0.000   0.0539   0.00717   0.00166   0.0028   0.5606   0.7377
   0.250   0.0773   0.00718   0.00174   0.0039   0.4840   0.8389
   0.500   0.1034   0.00742   0.00188   0.0045   0.4110   0.9047
   0.750   0.1369   0.00780   0.00204   0.0035   0.3498   0.9462
   1.000   0.1730   0.00812   0.00218   0.0017   0.3119   0.9680
   1.250   0.2102   0.00836   0.00228  -0.0003   0.2893   0.9779
   1.500   0.2441   0.00855   0.00236  -0.0017   0.2740   0.9841
   1.750   0.2810   0.00872   0.00243  -0.0037   0.2609   0.9867
   2.000   0.3161   0.00888   0.00251  -0.0054   0.2500   0.9896
   2.250   0.3503   0.00902   0.00259  -0.0068   0.2425   0.9928
   2.500   0.3845   0.00917   0.00268  -0.0083   0.2355   0.9953
   2.750   0.4193   0.00930   0.00277  -0.0099   0.2299   0.9974
   3.000   0.4539   0.00944   0.00287  -0.0114   0.2241   0.9995
   3.250   0.4818   0.00958   0.00296  -0.0116   0.2186   1.0000
   3.500   0.5075   0.00969   0.00305  -0.0112   0.2147   1.0000
   3.750   0.5333   0.00979   0.00314  -0.0108   0.2110   1.0000
   4.000   0.5590   0.00992   0.00325  -0.0105   0.2070   1.0000
   4.250   0.5846   0.01009   0.00338  -0.0101   0.2026   1.0000
   4.500   0.6104   0.01021   0.00351  -0.0097   0.1991   1.0000
   4.750   0.6362   0.01034   0.00365  -0.0094   0.1956   1.0000
   5.000   0.6620   0.01050   0.00380  -0.0090   0.1914   1.0000
   5.250   0.6876   0.01070   0.00396  -0.0087   0.1868   1.0000
   5.500   0.7136   0.01082   0.00412  -0.0083   0.1831   1.0000
   5.750   0.7395   0.01098   0.00429  -0.0080   0.1784   1.0000
   6.000   0.7652   0.01119   0.00446  -0.0077   0.1734   1.0000
   6.250   0.7911   0.01134   0.00464  -0.0074   0.1683   1.0000
   6.500   0.8170   0.01153   0.00483  -0.0071   0.1625   1.0000
   6.750   0.8427   0.01174   0.00504  -0.0068   0.1575   1.0000
   7.000   0.8687   0.01193   0.00525  -0.0065   0.1511   1.0000
   7.250   0.8944   0.01218   0.00546  -0.0063   0.1428   1.0000
   7.500   0.9201   0.01243   0.00570  -0.0061   0.1337   1.0000
   7.750   0.9457   0.01270   0.00597  -0.0058   0.1260   1.0000
   8.000   0.9711   0.01302   0.00626  -0.0056   0.1166   1.0000
   8.250   0.9961   0.01339   0.00660  -0.0053   0.1050   1.0000
   8.500   1.0207   0.01381   0.00697  -0.0050   0.0922   1.0000
   8.750   1.0448   0.01431   0.00740  -0.0047   0.0787   1.0000
   9.000   1.0686   0.01484   0.00789  -0.0043   0.0671   1.0000
   9.250   1.0921   0.01540   0.00842  -0.0040   0.0575   1.0000
   9.500   1.1154   0.01597   0.00897  -0.0035   0.0493   1.0000
   9.750   1.1387   0.01651   0.00952  -0.0031   0.0428   1.0000
  10.000   1.1614   0.01711   0.01012  -0.0026   0.0372   1.0000
  10.250   1.1837   0.01773   0.01074  -0.0021   0.0323   1.0000
  10.500   1.2059   0.01832   0.01138  -0.0016   0.0290   1.0000
  10.750   1.2276   0.01895   0.01203  -0.0010   0.0261   1.0000
  11.000   1.2483   0.01966   0.01278  -0.0003   0.0236   1.0000
  11.250   1.2694   0.02027   0.01346   0.0003   0.0220   1.0000
  11.500   1.2893   0.02096   0.01420   0.0011   0.0205   1.0000
  11.750   1.3077   0.02177   0.01507   0.0020   0.0191   1.0000
  12.000   1.3252   0.02262   0.01599   0.0030   0.0181   1.0000
  12.250   1.3428   0.02336   0.01683   0.0040   0.0174   1.0000
  12.500   1.3589   0.02418   0.01774   0.0052   0.0167   1.0000
  12.750   1.3729   0.02507   0.01872   0.0065   0.0161   1.0000
  13.000   1.3828   0.02604   0.01977   0.0085   0.0155   1.0000
  13.250   1.3906   0.02717   0.02100   0.0104   0.0150   1.0000
  13.500   1.3969   0.02851   0.02242   0.0122   0.0145   1.0000
  13.750   1.4000   0.03018   0.02420   0.0139   0.0140   1.0000
  14.000   1.4047   0.03181   0.02593   0.0153   0.0137   1.0000
  14.250   1.4101   0.03346   0.02771   0.0163   0.0134   1.0000
  14.500   1.4138   0.03536   0.02972   0.0172   0.0132   1.0000
  14.750   1.4158   0.03754   0.03203   0.0178   0.0128   1.0000
  15.000   1.4159   0.04005   0.03466   0.0181   0.0125   1.0000
  15.250   1.4137   0.04303   0.03778   0.0179   0.0123   1.0000
  15.500   1.4083   0.04664   0.04153   0.0171   0.0121   1.0000
  15.750   1.4007   0.05094   0.04597   0.0155   0.0119   1.0000
  16.000   1.3876   0.05649   0.05169   0.0128   0.0118   1.0000
  16.250   1.3688   0.06363   0.05902   0.0089   0.0117   1.0000
  16.500   1.3436   0.07235   0.06794   0.0040   0.0117   1.0000
  16.750   1.3136   0.08183   0.07760  -0.0010   0.0118   1.0000
  17.000   1.2823   0.09115   0.08706  -0.0055   0.0119   1.0000
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