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GOE 624 AIRFOIL (goe624-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 624 AIRFOIL (goe624-il)
Reynolds number: 200,000
Max Cl/Cd: 69.05 at α=7°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe624-il-200000.txt
Download as CSV file: xf-goe624-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 624 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  -0.0622   0.09168   0.08827  -0.0784   0.9421   0.0834
  -9.750  -0.0656   0.08807   0.08465  -0.0801   0.9322   0.0864
  -9.500  -0.1109   0.08069   0.07728  -0.0885   0.9226   0.0886
  -9.250  -0.0908   0.07846   0.07503  -0.0847   0.9116   0.0893
  -9.000  -0.0801   0.07633   0.07287  -0.0824   0.9010   0.0901
  -8.750  -0.0731   0.07398   0.07048  -0.0811   0.8895   0.0912
  -8.500  -0.0693   0.07125   0.06773  -0.0807   0.8790   0.0926
  -8.250  -0.3022   0.04119   0.03611  -0.1104   0.8908   0.0618
  -8.000  -0.2915   0.03794   0.03264  -0.1095   0.8828   0.0615
  -7.750  -0.2824   0.03458   0.02884  -0.1084   0.8729   0.0615
  -7.500  -0.2700   0.03170   0.02544  -0.1070   0.8643   0.0618
  -7.250  -0.2533   0.02927   0.02269  -0.1058   0.8546   0.0623
  -7.000  -0.2328   0.02751   0.02072  -0.1049   0.8467   0.0628
  -6.750  -0.2105   0.02618   0.01923  -0.1041   0.8377   0.0636
  -6.500  -0.1865   0.02503   0.01789  -0.1034   0.8317   0.0645
  -6.250  -0.1626   0.02395   0.01665  -0.1029   0.8227   0.0656
  -6.000  -0.1376   0.02290   0.01535  -0.1022   0.8160   0.0672
  -5.750  -0.1122   0.02203   0.01418  -0.1016   0.8087   0.0692
  -5.500  -0.0867   0.02104   0.01312  -0.1012   0.8010   0.0711
  -5.250  -0.0599   0.02041   0.01242  -0.1008   0.7952   0.0733
  -5.000  -0.0336   0.01980   0.01172  -0.1004   0.7869   0.0761
  -4.750  -0.0067   0.01904   0.01080  -0.1000   0.7802   0.0793
  -4.500   0.0201   0.01856   0.01036  -0.0997   0.7736   0.0835
  -4.250   0.0468   0.01804   0.00975  -0.0993   0.7656   0.0897
  -4.000   0.0743   0.01761   0.00929  -0.0990   0.7597   0.0975
  -3.750   0.1006   0.01711   0.00885  -0.0987   0.7518   0.1070
  -3.500   0.1277   0.01667   0.00839  -0.0985   0.7450   0.1177
  -3.250   0.1552   0.01636   0.00803  -0.0982   0.7386   0.1285
  -3.000   0.1822   0.01612   0.00780  -0.0980   0.7303   0.1384
  -2.750   0.2099   0.01576   0.00742  -0.0978   0.7240   0.1480
  -2.500   0.2371   0.01559   0.00724  -0.0976   0.7156   0.1584
  -2.250   0.2648   0.01536   0.00701  -0.0975   0.7086   0.1719
  -2.000   0.2920   0.01513   0.00683  -0.0973   0.7013   0.1871
  -1.750   0.3192   0.01484   0.00660  -0.0971   0.6932   0.2048
  -1.500   0.3465   0.01449   0.00634  -0.0969   0.6863   0.2336
  -1.250   0.3722   0.01405   0.00620  -0.0966   0.6772   0.2952
  -1.000   0.3976   0.01346   0.00602  -0.0962   0.6705   0.4218
  -0.750   0.4174   0.01273   0.00612  -0.0945   0.6613   0.6286
  -0.500   0.4371   0.01225   0.00621  -0.0915   0.6543   0.8390
  -0.250   0.4823   0.01227   0.00628  -0.0940   0.6447   0.9497
   0.000   0.5437   0.01235   0.00613  -0.1005   0.6358   0.9912
   0.250   0.5842   0.01243   0.00611  -0.1033   0.6254   1.0000
   0.500   0.6088   0.01253   0.00601  -0.1026   0.6179   1.0000
   0.750   0.6316   0.01265   0.00608  -0.1018   0.6085   1.0000
   1.000   0.6565   0.01277   0.00603  -0.1012   0.6010   1.0000
   1.250   0.6797   0.01292   0.00613  -0.1004   0.5919   1.0000
   1.500   0.7046   0.01306   0.00612  -0.0997   0.5843   1.0000
   1.750   0.7286   0.01324   0.00624  -0.0991   0.5763   1.0000
   2.000   0.7535   0.01340   0.00630  -0.0985   0.5688   1.0000
   2.250   0.7788   0.01359   0.00639  -0.0980   0.5620   1.0000
   2.500   0.8034   0.01377   0.00653  -0.0975   0.5543   1.0000
   2.750   0.8300   0.01396   0.00658  -0.0972   0.5484   1.0000
   3.000   0.8545   0.01418   0.00680  -0.0967   0.5413   1.0000
   3.250   0.8803   0.01437   0.00693  -0.0964   0.5349   1.0000
   3.500   0.9073   0.01460   0.00705  -0.0963   0.5295   1.0000
   3.750   0.9318   0.01483   0.00731  -0.0958   0.5228   1.0000
   4.000   0.9581   0.01504   0.00745  -0.0955   0.5171   1.0000
   4.250   0.9849   0.01531   0.00763  -0.0954   0.5119   1.0000
   4.500   1.0094   0.01555   0.00792  -0.0950   0.5056   1.0000
   4.750   1.0357   0.01577   0.00808  -0.0948   0.4999   1.0000
   5.000   1.0614   0.01602   0.00828  -0.0945   0.4936   1.0000
   5.250   1.0854   0.01622   0.00849  -0.0939   0.4862   1.0000
   5.500   1.1125   0.01646   0.00861  -0.0939   0.4802   1.0000
   5.750   1.1362   0.01676   0.00897  -0.0933   0.4743   1.0000
   6.000   1.1612   0.01704   0.00925  -0.0930   0.4687   1.0000
   6.250   1.1883   0.01733   0.00947  -0.0930   0.4638   1.0000
   6.500   1.2120   0.01768   0.00987  -0.0925   0.4583   1.0000
   6.750   1.2359   0.01797   0.01020  -0.0920   0.4525   1.0000
   7.000   1.2623   0.01828   0.01045  -0.0919   0.4475   1.0000
   7.250   1.2864   0.01867   0.01088  -0.0916   0.4424   1.0000
   7.500   1.3089   0.01901   0.01129  -0.0909   0.4367   1.0000
   7.750   1.3343   0.01933   0.01158  -0.0907   0.4316   1.0000
   8.000   1.3590   0.01974   0.01199  -0.0904   0.4264   1.0000
   8.250   1.3791   0.02010   0.01245  -0.0893   0.4202   1.0000
   8.500   1.4034   0.02041   0.01274  -0.0890   0.4144   1.0000
   8.750   1.4260   0.02083   0.01319  -0.0884   0.4087   1.0000
   9.000   1.4446   0.02121   0.01367  -0.0871   0.4023   1.0000
   9.250   1.4684   0.02153   0.01395  -0.0867   0.3965   1.0000
   9.500   1.4858   0.02198   0.01449  -0.0852   0.3899   1.0000
   9.750   1.5029   0.02232   0.01489  -0.0837   0.3828   1.0000
  10.000   1.5244   0.02269   0.01522  -0.0830   0.3763   1.0000
  10.250   1.5340   0.02314   0.01582  -0.0803   0.3688   1.0000
  10.500   1.5530   0.02347   0.01608  -0.0791   0.3619   1.0000
  10.750   1.5562   0.02403   0.01680  -0.0755   0.3545   1.0000
  11.000   1.5674   0.02451   0.01730  -0.0732   0.3476   1.0000
  11.250   1.5764   0.02518   0.01804  -0.0709   0.3405   1.0000
  11.500   1.5832   0.02590   0.01882  -0.0683   0.3329   1.0000
  11.750   1.5918   0.02669   0.01964  -0.0662   0.3252   1.0000
  12.000   1.5965   0.02765   0.02066  -0.0638   0.3170   1.0000
  12.250   1.6044   0.02863   0.02168  -0.0619   0.3095   1.0000
  12.500   1.6098   0.02979   0.02291  -0.0599   0.3017   1.0000
  12.750   1.6178   0.03093   0.02405  -0.0583   0.2946   1.0000
  13.000   1.6218   0.03233   0.02553  -0.0565   0.2869   1.0000
  13.250   1.6296   0.03358   0.02676  -0.0551   0.2801   1.0000
  13.500   1.6319   0.03524   0.02854  -0.0534   0.2727   1.0000
  13.750   1.6401   0.03653   0.02975  -0.0521   0.2661   1.0000
  14.000   1.6398   0.03853   0.03190  -0.0506   0.2590   1.0000
  14.250   1.6465   0.03998   0.03328  -0.0494   0.2525   1.0000
  14.500   1.6448   0.04221   0.03567  -0.0481   0.2457   1.0000
  14.750   1.6469   0.04413   0.03758  -0.0470   0.2391   1.0000
  15.000   1.6464   0.04641   0.03994  -0.0459   0.2326   1.0000
  15.250   1.6451   0.04884   0.04243  -0.0450   0.2259   1.0000
  15.500   1.6469   0.05101   0.04460  -0.0442   0.2198   1.0000
  15.750   1.6424   0.05397   0.04770  -0.0436   0.2135   1.0000
  16.000   1.6460   0.05596   0.04959  -0.0429   0.2072   1.0000
  16.250   1.6377   0.05958   0.05342  -0.0427   0.2011   1.0000
  16.500   1.6355   0.06242   0.05626  -0.0423   0.1948   1.0000
  16.750   1.6296   0.06587   0.05981  -0.0422   0.1886   1.0000
  17.000   1.6229   0.06946   0.06346  -0.0422   0.1823   1.0000
  17.250   1.6183   0.07279   0.06682  -0.0422   0.1762   1.0000
  17.500   1.6092   0.07693   0.07110  -0.0426   0.1700   1.0000
  17.750   1.6074   0.07992   0.07402  -0.0426   0.1643   1.0000
  18.000   1.5959   0.08457   0.07888  -0.0434   0.1585   1.0000
  18.250   1.5907   0.08821   0.08251  -0.0439   0.1530   1.0000
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