Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

GOE 629 AIRFOIL (goe629-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 629 AIRFOIL (goe629-il)
Reynolds number: 500,000
Max Cl/Cd: 94.65 at α=4.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe629-il-500000.txt
Download as CSV file: xf-goe629-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 629 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -17.000  -0.9368   0.08033   0.07672  -0.0667   1.0000   0.0311
 -16.750  -0.9689   0.07254   0.06883  -0.0710   1.0000   0.0312
 -16.500  -1.0072   0.06394   0.06010  -0.0758   1.0000   0.0312
 -16.250  -1.0448   0.05535   0.05138  -0.0808   1.0000   0.0311
 -16.000  -1.0802   0.04668   0.04254  -0.0865   1.0000   0.0309
 -15.750  -1.1050   0.03949   0.03515  -0.0917   1.0000   0.0312
 -15.500  -1.1220   0.03471   0.03020  -0.0944   1.0000   0.0316
 -15.250  -1.1413   0.03121   0.02660  -0.0943   1.0000   0.0323
 -15.000  -1.1542   0.02912   0.02442  -0.0920   1.0000   0.0330
 -14.750  -1.1647   0.02770   0.02293  -0.0884   1.0000   0.0339
 -14.500  -1.1760   0.02671   0.02187  -0.0835   1.0000   0.0350
 -14.250  -1.1893   0.02604   0.02111  -0.0775   1.0000   0.0359
 -14.000  -1.1992   0.02512   0.02015  -0.0722   1.0000   0.0372
 -13.750  -1.2003   0.02434   0.01934  -0.0680   1.0000   0.0388
 -13.500  -1.1958   0.02373   0.01864  -0.0646   1.0000   0.0411
 -13.250  -1.1927   0.02300   0.01789  -0.0611   1.0000   0.0431
 -13.000  -1.1836   0.02254   0.01739  -0.0583   1.0000   0.0456
 -12.750  -1.1636   0.02196   0.01673  -0.0576   0.9990   0.0483
 -12.500  -1.1317   0.02155   0.01631  -0.0591   0.9969   0.0514
 -12.250  -1.0993   0.02115   0.01578  -0.0605   0.9948   0.0542
 -12.000  -1.0678   0.02072   0.01536  -0.0620   0.9929   0.0568
 -11.750  -1.0379   0.02047   0.01504  -0.0627   0.9902   0.0593
 -11.500  -1.0066   0.02014   0.01459  -0.0638   0.9875   0.0615
 -11.250  -0.9759   0.01963   0.01410  -0.0650   0.9852   0.0638
 -11.000  -0.9420   0.01940   0.01383  -0.0666   0.9835   0.0662
 -10.750  -0.9069   0.01917   0.01349  -0.0684   0.9821   0.0684
 -10.500  -0.8825   0.01867   0.01290  -0.0681   0.9778   0.0702
 -10.250  -0.8535   0.01815   0.01240  -0.0688   0.9747   0.0725
 -10.000  -0.8206   0.01784   0.01206  -0.0701   0.9725   0.0746
  -9.750  -0.7862   0.01755   0.01169  -0.0717   0.9709   0.0768
  -9.500  -0.7503   0.01736   0.01138  -0.0734   0.9696   0.0786
  -9.250  -0.7263   0.01660   0.01067  -0.0731   0.9653   0.0817
  -9.000  -0.6954   0.01632   0.01038  -0.0739   0.9615   0.0843
  -8.750  -0.6598   0.01598   0.00998  -0.0756   0.9591   0.0868
  -8.500  -0.6219   0.01562   0.00953  -0.0776   0.9574   0.0885
  -8.250  -0.5854   0.01479   0.00869  -0.0797   0.9561   0.0914
  -8.000  -0.5465   0.01429   0.00820  -0.0821   0.9550   0.0937
  -7.750  -0.5214   0.01399   0.00787  -0.0815   0.9491   0.0959
  -7.500  -0.4898   0.01368   0.00750  -0.0823   0.9458   0.0982
  -7.250  -0.4562   0.01338   0.00714  -0.0834   0.9433   0.0999
  -7.000  -0.4233   0.01277   0.00656  -0.0846   0.9410   0.1033
  -6.750  -0.3883   0.01244   0.00623  -0.0861   0.9389   0.1064
  -6.500  -0.3673   0.01224   0.00601  -0.0845   0.9315   0.1089
  -6.250  -0.3362   0.01199   0.00571  -0.0851   0.9275   0.1115
  -6.000  -0.3050   0.01159   0.00532  -0.0857   0.9241   0.1157
  -5.750  -0.2796   0.01139   0.00514  -0.0851   0.9182   0.1195
  -5.500  -0.2520   0.01121   0.00492  -0.0849   0.9122   0.1235
  -5.250  -0.2222   0.01090   0.00461  -0.0852   0.9076   0.1286
  -5.000  -0.1966   0.01073   0.00446  -0.0845   0.9009   0.1342
  -4.750  -0.1687   0.01062   0.00430  -0.0843   0.8945   0.1395
  -4.500  -0.1394   0.01033   0.00405  -0.0845   0.8895   0.1471
  -4.250  -0.1150   0.01025   0.00394  -0.0836   0.8816   0.1529
  -4.000  -0.0876   0.01002   0.00371  -0.0833   0.8752   0.1595
  -3.750  -0.0609   0.00989   0.00359  -0.0829   0.8680   0.1657
  -3.500  -0.0340   0.00980   0.00345  -0.0825   0.8601   0.1708
  -3.250  -0.0074   0.00959   0.00326  -0.0821   0.8527   0.1779
  -3.000   0.0183   0.00948   0.00314  -0.0815   0.8441   0.1835
  -2.750   0.0459   0.00936   0.00299  -0.0812   0.8364   0.1890
  -2.500   0.0708   0.00921   0.00287  -0.0804   0.8263   0.1958
  -2.250   0.0970   0.00912   0.00275  -0.0798   0.8158   0.2025
  -2.000   0.1232   0.00899   0.00261  -0.0793   0.8050   0.2114
  -1.500   0.1733   0.00877   0.00244  -0.0777   0.7815   0.2342
  -1.250   0.1986   0.00867   0.00235  -0.0770   0.7694   0.2526
  -1.000   0.2227   0.00854   0.00229  -0.0761   0.7553   0.2786
  -0.750   0.2465   0.00840   0.00224  -0.0751   0.7413   0.3132
  -0.500   0.2702   0.00825   0.00221  -0.0741   0.7280   0.3547
  -0.250   0.2935   0.00810   0.00219  -0.0731   0.7148   0.4038
   0.000   0.3161   0.00796   0.00218  -0.0719   0.7009   0.4600
   0.250   0.3374   0.00777   0.00218  -0.0704   0.6865   0.5298
   0.500   0.3573   0.00755   0.00220  -0.0686   0.6721   0.6116
   0.750   0.3750   0.00727   0.00226  -0.0662   0.6585   0.7153
   1.000   0.3951   0.00710   0.00235  -0.0642   0.6459   0.8099
   1.250   0.4259   0.00710   0.00249  -0.0643   0.6333   0.8833
   1.500   0.4719   0.00726   0.00265  -0.0679   0.6197   0.9257
   1.750   0.5145   0.00743   0.00279  -0.0708   0.6071   0.9463
   2.000   0.5547   0.00762   0.00292  -0.0732   0.5955   0.9593
   2.250   0.5918   0.00783   0.00305  -0.0750   0.5846   0.9701
   2.500   0.6325   0.00800   0.00319  -0.0776   0.5724   0.9779
   2.750   0.6717   0.00818   0.00330  -0.0799   0.5588   0.9842
   3.000   0.7141   0.00837   0.00341  -0.0830   0.5437   0.9906
   3.250   0.7579   0.00854   0.00351  -0.0863   0.5270   0.9963
   3.500   0.7974   0.00869   0.00359  -0.0889   0.5119   1.0000
   3.750   0.8161   0.00880   0.00366  -0.0870   0.4994   1.0000
   4.000   0.8349   0.00891   0.00374  -0.0851   0.4857   1.0000
   4.250   0.8532   0.00904   0.00382  -0.0832   0.4704   1.0000
   4.500   0.8708   0.00920   0.00392  -0.0811   0.4529   1.0000
   4.750   0.8878   0.00938   0.00403  -0.0788   0.4331   1.0000
   5.000   0.9040   0.00960   0.00416  -0.0764   0.4122   1.0000
   5.250   0.9205   0.00982   0.00431  -0.0741   0.3911   1.0000
   5.500   0.9354   0.01012   0.00449  -0.0715   0.3686   1.0000
   5.750   0.9508   0.01042   0.00470  -0.0690   0.3505   1.0000
   6.000   0.9670   0.01070   0.00492  -0.0667   0.3352   1.0000
   6.250   0.9833   0.01098   0.00514  -0.0644   0.3210   1.0000
   6.500   0.9998   0.01126   0.00538  -0.0621   0.3080   1.0000
   6.750   1.0157   0.01156   0.00562  -0.0598   0.2938   1.0000
   7.000   1.0314   0.01188   0.00588  -0.0574   0.2776   1.0000
   7.250   1.0467   0.01220   0.00614  -0.0549   0.2616   1.0000
   7.500   1.0599   0.01252   0.00640  -0.0521   0.2441   1.0000
   7.750   1.0714   0.01290   0.00669  -0.0490   0.2226   1.0000
   8.000   1.0813   0.01338   0.00704  -0.0457   0.1981   1.0000
   8.250   1.0911   0.01393   0.00746  -0.0425   0.1753   1.0000
   8.750   1.1138   0.01504   0.00840  -0.0368   0.1436   1.0000
   9.000   1.1266   0.01558   0.00888  -0.0344   0.1303   1.0000
   9.250   1.1393   0.01615   0.00940  -0.0320   0.1173   1.0000
   9.500   1.1520   0.01674   0.00993  -0.0296   0.1051   1.0000
   9.750   1.1634   0.01742   0.01055  -0.0272   0.0922   1.0000
  10.000   1.1741   0.01817   0.01124  -0.0248   0.0794   1.0000
  10.250   1.1838   0.01900   0.01201  -0.0223   0.0655   1.0000
  10.500   1.1922   0.01994   0.01286  -0.0198   0.0546   1.0000
  10.750   1.2025   0.02080   0.01370  -0.0176   0.0493   1.0000
  11.000   1.2119   0.02174   0.01464  -0.0154   0.0461   1.0000
  11.250   1.2227   0.02263   0.01557  -0.0135   0.0440   1.0000
  11.500   1.2321   0.02365   0.01661  -0.0116   0.0425   1.0000
  11.750   1.2388   0.02487   0.01786  -0.0095   0.0411   1.0000
  12.000   1.2464   0.02609   0.01914  -0.0077   0.0401   1.0000
  12.250   1.2556   0.02724   0.02036  -0.0061   0.0391   1.0000
  12.500   1.2633   0.02855   0.02173  -0.0046   0.0383   1.0000
  12.750   1.2702   0.02997   0.02321  -0.0031   0.0374   1.0000
  13.000   1.2755   0.03156   0.02485  -0.0017   0.0367   1.0000
  13.250   1.2780   0.03344   0.02678  -0.0003   0.0360   1.0000
  13.500   1.2774   0.03567   0.02906   0.0010   0.0354   1.0000
  13.750   1.2794   0.03775   0.03121   0.0021   0.0348   1.0000
  14.000   1.2849   0.03960   0.03316   0.0029   0.0344   1.0000
  14.250   1.2900   0.04155   0.03519   0.0035   0.0338   1.0000
  14.500   1.2938   0.04367   0.03739   0.0041   0.0333   1.0000
  14.750   1.2966   0.04594   0.03973   0.0046   0.0328   1.0000
  15.000   1.2990   0.04832   0.04218   0.0050   0.0323   1.0000
  15.250   1.3011   0.05078   0.04470   0.0052   0.0318   1.0000
  15.500   1.3020   0.05339   0.04737   0.0054   0.0315   1.0000
  15.750   1.3014   0.05617   0.05019   0.0056   0.0309   1.0000
  16.000   1.3001   0.05897   0.05303   0.0059   0.0305   1.0000
  16.250   1.3009   0.06163   0.05575   0.0061   0.0300   1.0000
  16.500   1.3036   0.06421   0.05843   0.0060   0.0298   1.0000
  16.750   1.3053   0.06709   0.06141   0.0055   0.0292   1.0000
  17.000   1.3070   0.06985   0.06426   0.0052   0.0289   1.0000
  17.250   1.3076   0.07283   0.06733   0.0048   0.0285   1.0000
  17.500   1.3084   0.07575   0.07033   0.0044   0.0281   1.0000
  17.750   1.3086   0.07879   0.07345   0.0039   0.0278   1.0000
  18.000   1.3085   0.08196   0.07667   0.0031   0.0273   1.0000
  18.250   1.3092   0.08494   0.07970   0.0026   0.0269   1.0000
  18.500   1.3105   0.08777   0.08257   0.0022   0.0266   1.0000
  18.750   1.3143   0.08984   0.08463   0.0026   0.0261   1.0000
  19.000   1.3130   0.09302   0.08791   0.0021   0.0257   1.0000
  19.250   1.3075   0.09738   0.09241   0.0003   0.0254   1.0000
<< Back to GOE 629 AIRFOIL (goe629-il)

Polar data table (+)

Polar graphs


<< Back to GOE 629 AIRFOIL (goe629-il)