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GOE 531 AIRFOIL (goe531-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: GOE 531 AIRFOIL (goe531-il)
Reynolds number: 500,000
Max Cl/Cd: 66.05 at α=3.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe531-il-500000-n5.txt
Download as CSV file: xf-goe531-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 531 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
  ------ -------- --------- --------- -------- -------- --------
 -12.500   0.5942   0.10212   0.09700  -0.2371   0.6812   0.0293
 -12.250   0.6016   0.10022   0.09511  -0.2377   0.6802   0.0293
 -12.000   0.6085   0.09833   0.09322  -0.2383   0.6790   0.0294
 -11.750   0.6159   0.09649   0.09137  -0.2389   0.6778   0.0294
 -11.500   0.6231   0.09465   0.08953  -0.2393   0.6766   0.0295
 -11.250   0.6303   0.09287   0.08775  -0.2397   0.6754   0.0294
 -11.000   0.6437   0.09168   0.08656  -0.2400   0.6744   0.0298
 -10.750   0.6533   0.09026   0.08514  -0.2404   0.6733   0.0300
 -10.500   0.6617   0.08870   0.08357  -0.2408   0.6722   0.0301
 -10.250   0.6720   0.08742   0.08228  -0.2411   0.6711   0.0308
  -8.750   0.7049   0.07686   0.07181  -0.2411   0.6655   0.0292
  -8.250   0.7123   0.07362   0.06863  -0.2402   0.6632   0.0295
  -8.000   0.7188   0.07239   0.06742  -0.2397   0.6622   0.0296
  -7.750   0.7293   0.07167   0.06672  -0.2392   0.6611   0.0300
  -7.500   0.7368   0.07074   0.06581  -0.2386   0.6601   0.0304
  -7.250   0.7415   0.06958   0.06467  -0.2377   0.6590   0.0307
  -7.000   0.7442   0.06834   0.06345  -0.2365   0.6578   0.0308
  -6.750   0.7449   0.06707   0.06219  -0.2350   0.6566   0.0307
  -6.500   0.7446   0.06589   0.06103  -0.2332   0.6554   0.0307
  -6.250   0.7436   0.06488   0.06002  -0.2311   0.6540   0.0310
  -6.000   0.7407   0.06389   0.05905  -0.2287   0.6526   0.0311
  -5.750   0.7361   0.06296   0.05813  -0.2260   0.6513   0.0312
  -5.500   0.7256   0.06226   0.05749  -0.2219   0.6505   0.0314
  -5.250   0.7133   0.06159   0.05690  -0.2172   0.6494   0.0315
  -5.000   0.7011   0.06083   0.05620  -0.2127   0.6483   0.0318
  -4.750   0.6920   0.05988   0.05531  -0.2090   0.6469   0.0319
  -4.500   0.6822   0.05872   0.05419  -0.2055   0.6454   0.0323
  -4.250   0.6695   0.05635   0.05186  -0.2033   0.6438   0.0333
  -4.000   0.6709   0.05545   0.05099  -0.2013   0.6423   0.0334
  -3.750   0.6750   0.05473   0.05029  -0.1995   0.6408   0.0336
  -3.500   0.6817   0.05359   0.04916  -0.1987   0.6395   0.0338
  -3.250   0.6908   0.05242   0.04799  -0.1984   0.6383   0.0342
  -3.000   0.7030   0.05094   0.04649  -0.1989   0.6370   0.0345
  -2.750   0.7198   0.04918   0.04470  -0.2006   0.6358   0.0351
  -2.500   0.7484   0.04488   0.04030  -0.2077   0.6345   0.0373
  -2.250   0.7643   0.04412   0.03955  -0.2078   0.6333   0.0376
  -2.000   0.7739   0.04346   0.03894  -0.2067   0.6319   0.0379
  -1.750   0.7890   0.04242   0.03791  -0.2070   0.6303   0.0385
  -1.250   0.9673   0.01870   0.01262  -0.2571   0.6288   0.0558
  -1.000   0.9864   0.01873   0.01266  -0.2559   0.6274   0.0564
  -0.750   1.0061   0.01848   0.01235  -0.2551   0.6260   0.0571
  -0.500   1.0260   0.01822   0.01198  -0.2542   0.6247   0.0581
  -0.250   1.0463   0.01794   0.01155  -0.2534   0.6234   0.0591
   0.000   1.0676   0.01771   0.01115  -0.2527   0.6221   0.0603
   0.250   1.0893   0.01764   0.01099  -0.2520   0.6209   0.0611
   0.500   1.1116   0.01770   0.01104  -0.2513   0.6196   0.0619
   0.750   1.1356   0.01771   0.01100  -0.2509   0.6183   0.0627
   1.000   1.1581   0.01774   0.01097  -0.2503   0.6168   0.0636
   1.250   1.1687   0.01804   0.01127  -0.2476   0.6153   0.0646
   1.500   1.1818   0.01830   0.01150  -0.2454   0.6137   0.0654
   1.750   1.1949   0.01861   0.01177  -0.2432   0.6120   0.0663
   2.000   1.2093   0.01889   0.01205  -0.2413   0.6102   0.0671
   2.250   1.2251   0.01917   0.01235  -0.2396   0.6086   0.0679
   2.500   1.2413   0.01945   0.01263  -0.2380   0.6070   0.0686
   2.750   1.2592   0.01969   0.01286  -0.2367   0.6055   0.0696
   3.000   1.2795   0.01987   0.01300  -0.2358   0.6041   0.0707
   3.250   1.3018   0.02000   0.01309  -0.2352   0.6029   0.0719
   3.500   1.3263   0.02008   0.01311  -0.2350   0.6016   0.0730
   3.750   1.3417   0.02044   0.01350  -0.2333   0.5999   0.0740
   4.000   1.3420   0.02141   0.01455  -0.2294   0.5974   0.0748
   4.250   1.3495   0.02217   0.01536  -0.2266   0.5950   0.0755
   4.500   1.3584   0.02293   0.01615  -0.2241   0.5928   0.0764
   4.750   1.3715   0.02353   0.01676  -0.2222   0.5909   0.0777
   5.000   1.3891   0.02393   0.01716  -0.2211   0.5892   0.0790
   5.250   1.4096   0.02421   0.01743  -0.2204   0.5878   0.0803
   5.500   1.4323   0.02437   0.01760  -0.2200   0.5866   0.0818
   5.750   1.4572   0.02445   0.01768  -0.2199   0.5854   0.0834
   6.000   1.4595   0.02568   0.01898  -0.2167   0.5831   0.0844
   6.250   1.4466   0.02782   0.02122  -0.2114   0.5792   0.0852
   6.500   1.4502   0.02914   0.02257  -0.2086   0.5761   0.0866
   6.750   1.4627   0.02993   0.02337  -0.2069   0.5734   0.0881
   7.000   1.4858   0.03005   0.02350  -0.2066   0.5714   0.0906
   7.250   1.5111   0.03007   0.02351  -0.2066   0.5700   0.0936
   7.500   1.5218   0.03102   0.02450  -0.2048   0.5676   0.0961
   7.750   1.4902   0.03489   0.02850  -0.1979   0.5617   0.0961
   8.000   1.4944   0.03640   0.03005  -0.1954   0.5587   0.0990
   8.250   1.5123   0.03692   0.03061  -0.1946   0.5570   0.1054
   8.500   1.5357   0.03703   0.03075  -0.1944   0.5554   0.1183
   8.750   1.5659   0.03660   0.03035  -0.1950   0.5536   0.1472
   9.000   1.5251   0.04160   0.03549  -0.1876   0.5464   0.1450
   9.250   1.5268   0.04342   0.03736  -0.1850   0.5419   0.1602
   9.500   1.5489   0.04361   0.03758  -0.1847   0.5400   0.1777
   9.750   1.5774   0.04327   0.03724  -0.1851   0.5382   0.1935
  10.000   1.6047   0.04304   0.03701  -0.1854   0.5369   0.2036
  10.250   1.5482   0.04979   0.04393  -0.1769   0.5283   0.2005
  10.500   1.5598   0.05090   0.04508  -0.1756   0.5257   0.2079
  10.750   1.5817   0.05109   0.04529  -0.1754   0.5238   0.2165
  11.000   1.6077   0.05093   0.04514  -0.1755   0.5222   0.2254
  11.250   1.5913   0.05451   0.04881  -0.1715   0.5162   0.2292
  11.500   1.5781   0.05792   0.05230  -0.1680   0.5106   0.2317
  11.750   1.5982   0.05827   0.05265  -0.1676   0.5080   0.2385
  12.000   1.6240   0.05810   0.05251  -0.1678   0.5063   0.2468
  12.250   1.6523   0.05770   0.05211  -0.1682   0.5046   0.2549
  12.750   1.6263   0.06468   0.05924  -0.1615   0.4907   0.2604
  13.000   1.6547   0.06422   0.05878  -0.1620   0.4886   0.2664
  13.250   1.6206   0.06992   0.06460  -0.1570   0.4782   0.2671
  13.500   1.6454   0.06976   0.06442  -0.1572   0.4733   0.2734
  13.750   1.6348   0.07323   0.06796  -0.1544   0.4645   0.2758
  14.000   1.6478   0.07432   0.06907  -0.1536   0.4575   0.2809
  14.250   1.6546   0.07609   0.07087  -0.1524   0.4508   0.2857
  14.750   1.6645   0.07992   0.07470  -0.1497   0.4273   0.2945
  15.000   1.6736   0.08131   0.07600  -0.1486   0.4076   0.3003
  15.250   1.6650   0.08448   0.07895  -0.1462   0.3751   0.3054
  15.500   1.6418   0.08933   0.08358  -0.1429   0.3456   0.3071
  15.750   1.6305   0.09303   0.08720  -0.1406   0.3285   0.3113
  16.000   1.6237   0.09633   0.09044  -0.1388   0.3146   0.3163
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