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GOE 553 AIRFOIL (goe553-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: GOE 553 AIRFOIL (goe553-il)
Reynolds number: 200,000
Max Cl/Cd: 74.95 at α=6.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe553-il-200000-n5.txt
Download as CSV file: xf-goe553-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 553 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.2824   0.07358   0.07006  -0.0615   0.9632   0.0340
  -8.500  -0.3102   0.04256   0.03826  -0.1016   0.9002   0.0341
  -8.250  -0.2939   0.03810   0.03340  -0.1059   0.8765   0.0343
  -8.000  -0.2764   0.03500   0.02994  -0.1079   0.8514   0.0346
  -7.750  -0.2582   0.03240   0.02697  -0.1088   0.8267   0.0350
  -7.500  -0.2386   0.03044   0.02467  -0.1091   0.8032   0.0356
  -7.250  -0.2191   0.02851   0.02234  -0.1090   0.7814   0.0364
  -7.000  -0.1988   0.02661   0.02002  -0.1088   0.7624   0.0370
  -6.750  -0.1772   0.02493   0.01792  -0.1085   0.7458   0.0374
  -6.500  -0.1543   0.02353   0.01613  -0.1081   0.7315   0.0378
  -6.250  -0.1304   0.02236   0.01461  -0.1076   0.7186   0.0382
  -6.000  -0.1056   0.02139   0.01333  -0.1073   0.7071   0.0386
  -5.750  -0.0806   0.02051   0.01221  -0.1069   0.6972   0.0393
  -5.500  -0.0552   0.01975   0.01138  -0.1066   0.6875   0.0400
  -5.250  -0.0294   0.01913   0.01063  -0.1063   0.6792   0.0407
  -5.000  -0.0033   0.01850   0.00988  -0.1059   0.6707   0.0412
  -4.750   0.0229   0.01793   0.00918  -0.1055   0.6634   0.0417
  -4.500   0.0492   0.01739   0.00855  -0.1052   0.6556   0.0424
  -4.250   0.0755   0.01692   0.00797  -0.1048   0.6486   0.0431
  -4.000   0.1021   0.01647   0.00746  -0.1045   0.6416   0.0438
  -3.750   0.1286   0.01610   0.00700  -0.1041   0.6345   0.0446
  -3.500   0.1550   0.01574   0.00656  -0.1038   0.6284   0.0457
  -3.250   0.1814   0.01533   0.00619  -0.1035   0.6215   0.0471
  -3.000   0.2081   0.01503   0.00585  -0.1032   0.6150   0.0484
  -2.750   0.2349   0.01478   0.00554  -0.1030   0.6093   0.0496
  -2.500   0.2620   0.01453   0.00526  -0.1027   0.6026   0.0511
  -2.250   0.2892   0.01434   0.00500  -0.1025   0.5964   0.0527
  -2.000   0.3163   0.01412   0.00474  -0.1023   0.5909   0.0552
  -1.750   0.3436   0.01395   0.00455  -0.1021   0.5841   0.0593
  -1.500   0.3708   0.01377   0.00437  -0.1019   0.5778   0.0659
  -1.250   0.3980   0.01357   0.00426  -0.1017   0.5718   0.0867
  -1.000   0.4250   0.01328   0.00415  -0.1016   0.5652   0.1411
  -0.750   0.4505   0.01263   0.00406  -0.1016   0.5591   0.3164
  -0.500   0.4759   0.01231   0.00420  -0.1012   0.5526   0.4692
  -0.250   0.5023   0.01227   0.00428  -0.1007   0.5454   0.5283
   0.000   0.5285   0.01228   0.00434  -0.1001   0.5390   0.5728
   0.250   0.5543   0.01227   0.00447  -0.0995   0.5315   0.6209
   0.500   0.5800   0.01229   0.00453  -0.0988   0.5248   0.6547
   0.750   0.6067   0.01231   0.00456  -0.0983   0.5178   0.6713
   1.000   0.6333   0.01235   0.00458  -0.0979   0.5100   0.6862
   1.250   0.6597   0.01239   0.00460  -0.0974   0.5021   0.7024
   1.500   0.6858   0.01241   0.00463  -0.0970   0.4930   0.7198
   1.750   0.7115   0.01244   0.00467  -0.0964   0.4844   0.7390
   2.000   0.7367   0.01247   0.00472  -0.0957   0.4761   0.7603
   2.250   0.7623   0.01250   0.00478  -0.0950   0.4683   0.7862
   2.500   0.7879   0.01249   0.00484  -0.0944   0.4605   0.8245
   2.750   0.8249   0.01241   0.00487  -0.0961   0.4516   1.0000
   3.000   0.8512   0.01260   0.00497  -0.0958   0.4427   1.0000
   3.250   0.8775   0.01280   0.00509  -0.0956   0.4342   1.0000
   3.500   0.9035   0.01301   0.00522  -0.0952   0.4265   1.0000
   3.750   0.9297   0.01323   0.00539  -0.0950   0.4204   1.0000
   4.000   0.9558   0.01344   0.00557  -0.0947   0.4139   1.0000
   4.250   0.9813   0.01370   0.00575  -0.0943   0.4080   1.0000
   4.500   1.0071   0.01391   0.00597  -0.0939   0.4012   1.0000
   4.750   1.0322   0.01417   0.00617  -0.0935   0.3942   1.0000
   5.000   1.0573   0.01443   0.00640  -0.0930   0.3882   1.0000
   5.250   1.0827   0.01467   0.00665  -0.0926   0.3824   1.0000
   5.500   1.1071   0.01495   0.00690  -0.0921   0.3762   1.0000
   5.750   1.1317   0.01522   0.00717  -0.0916   0.3700   1.0000
   6.000   1.1562   0.01549   0.00745  -0.0911   0.3640   1.0000
   6.250   1.1799   0.01581   0.00773  -0.0904   0.3586   1.0000
   6.500   1.2041   0.01608   0.00806  -0.0899   0.3530   1.0000
   6.750   1.2277   0.01638   0.00838  -0.0892   0.3470   1.0000
   7.000   1.2504   0.01673   0.00870  -0.0885   0.3416   1.0000
   7.250   1.2738   0.01703   0.00907  -0.0878   0.3361   1.0000
   7.500   1.2964   0.01735   0.00943  -0.0871   0.3304   1.0000
   7.750   1.3179   0.01773   0.00980  -0.0861   0.3251   1.0000
   8.000   1.3399   0.01806   0.01021  -0.0853   0.3191   1.0000
   8.250   1.3602   0.01844   0.01062  -0.0842   0.3119   1.0000
   8.500   1.3794   0.01884   0.01104  -0.0829   0.3040   1.0000
   8.750   1.3973   0.01927   0.01149  -0.0815   0.2950   1.0000
   9.000   1.4151   0.01970   0.01197  -0.0801   0.2867   1.0000
   9.250   1.4295   0.02019   0.01246  -0.0781   0.2779   1.0000
   9.500   1.4442   0.02066   0.01299  -0.0762   0.2691   1.0000
   9.750   1.4557   0.02125   0.01359  -0.0739   0.2603   1.0000
  10.000   1.4687   0.02184   0.01423  -0.0719   0.2512   1.0000
  10.250   1.4798   0.02252   0.01495  -0.0698   0.2429   1.0000
  10.500   1.4892   0.02332   0.01576  -0.0676   0.2341   1.0000
  10.750   1.4989   0.02416   0.01665  -0.0656   0.2254   1.0000
  11.000   1.5058   0.02519   0.01769  -0.0634   0.2177   1.0000
  11.250   1.5130   0.02628   0.01883  -0.0615   0.2094   1.0000
  11.500   1.5180   0.02758   0.02014  -0.0595   0.2023   1.0000
  11.750   1.5230   0.02897   0.02158  -0.0578   0.1955   1.0000
  12.000   1.5261   0.03058   0.02321  -0.0562   0.1899   1.0000
  12.250   1.5315   0.03214   0.02485  -0.0549   0.1846   1.0000
  12.500   1.5342   0.03398   0.02675  -0.0537   0.1799   1.0000
  12.750   1.5362   0.03599   0.02880  -0.0526   0.1756   1.0000
  13.000   1.5413   0.03782   0.03074  -0.0518   0.1711   1.0000
  13.250   1.5422   0.04010   0.03308  -0.0511   0.1661   1.0000
  13.500   1.5401   0.04273   0.03575  -0.0504   0.1611   1.0000
  13.750   1.5440   0.04490   0.03805  -0.0500   0.1559   1.0000
  14.000   1.5422   0.04768   0.04089  -0.0497   0.1503   1.0000
  14.250   1.5403   0.05056   0.04386  -0.0495   0.1440   1.0000
  14.500   1.5375   0.05365   0.04704  -0.0495   0.1355   1.0000
  14.750   1.5341   0.05692   0.05039  -0.0496   0.1245   1.0000
  15.000   1.5250   0.06098   0.05446  -0.0501   0.1084   1.0000
  15.250   1.5083   0.06616   0.05958  -0.0509   0.0940   1.0000
  15.500   1.4914   0.07159   0.06498  -0.0520   0.0858   1.0000
  15.750   1.4767   0.07692   0.07033  -0.0533   0.0805   1.0000
  16.000   1.4649   0.08201   0.07548  -0.0546   0.0766   1.0000
  16.250   1.4555   0.08689   0.08045  -0.0559   0.0733   1.0000
  16.500   1.4445   0.09210   0.08574  -0.0575   0.0706   1.0000
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