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

GOE 735 AIRFOIL (goe735-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: GOE 735 AIRFOIL (goe735-il)
Reynolds number: 200,000
Max Cl/Cd: 55.43 at α=6.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe735-il-200000-n5.txt
Download as CSV file: xf-goe735-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 735 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
  ------ -------- --------- --------- -------- -------- --------
 -16.750  -0.7578   0.08302   0.07843  -0.0518   1.0000   0.0527
 -16.500  -0.8029   0.07235   0.06758  -0.0590   1.0000   0.0531
 -16.250  -0.8338   0.06418   0.05927  -0.0647   1.0000   0.0536
 -16.000  -0.8555   0.05771   0.05267  -0.0692   1.0000   0.0541
 -15.500  -0.8750   0.04788   0.04249  -0.0774   0.9115   0.0554
 -15.250  -0.8742   0.04421   0.03852  -0.0809   0.8735   0.0564
 -15.000  -0.8799   0.04126   0.03531  -0.0816   0.8509   0.0574
 -14.750  -0.8845   0.03881   0.03260  -0.0814   0.8351   0.0583
 -14.500  -0.8831   0.03719   0.03090  -0.0806   0.8220   0.0590
 -14.250  -0.8812   0.03579   0.02940  -0.0794   0.8103   0.0599
 -14.000  -0.8790   0.03454   0.02803  -0.0778   0.8002   0.0609
 -13.750  -0.8760   0.03334   0.02669  -0.0760   0.7907   0.0621
 -13.500  -0.8723   0.03215   0.02531  -0.0740   0.7823   0.0635
 -13.250  -0.8666   0.03109   0.02411  -0.0721   0.7734   0.0648
 -13.000  -0.8587   0.03036   0.02331  -0.0700   0.7659   0.0658
 -12.750  -0.8495   0.02964   0.02252  -0.0679   0.7580   0.0671
 -12.500  -0.8400   0.02891   0.02168  -0.0658   0.7501   0.0686
 -12.250  -0.8299   0.02814   0.02072  -0.0636   0.7434   0.0703
 -12.000  -0.8182   0.02745   0.01995  -0.0615   0.7354   0.0717
 -11.750  -0.8060   0.02697   0.01941  -0.0593   0.7282   0.0731
 -11.500  -0.7931   0.02649   0.01885  -0.0571   0.7214   0.0747
 -11.250  -0.7791   0.02595   0.01820  -0.0550   0.7137   0.0766
 -11.000  -0.7650   0.02541   0.01747  -0.0528   0.7067   0.0786
 -10.750  -0.7503   0.02504   0.01708  -0.0507   0.6995   0.0799
 -10.500  -0.7337   0.02468   0.01667  -0.0489   0.6916   0.0815
 -10.250  -0.7158   0.02427   0.01615  -0.0472   0.6845   0.0835
 -10.000  -0.6964   0.02382   0.01555  -0.0458   0.6771   0.0856
  -9.750  -0.6768   0.02338   0.01505  -0.0445   0.6690   0.0874
  -9.500  -0.6572   0.02306   0.01466  -0.0430   0.6618   0.0891
  -9.250  -0.6361   0.02270   0.01427  -0.0418   0.6529   0.0912
  -9.000  -0.6147   0.02234   0.01377  -0.0406   0.6450   0.0934
  -8.750  -0.5925   0.02195   0.01324  -0.0395   0.6372   0.0956
  -8.500  -0.5706   0.02158   0.01287  -0.0385   0.6284   0.0974
  -8.250  -0.5485   0.02131   0.01253  -0.0374   0.6205   0.0996
  -8.000  -0.5253   0.02101   0.01216  -0.0365   0.6112   0.1021
  -7.750  -0.5020   0.02073   0.01171  -0.0355   0.6033   0.1046
  -7.500  -0.4784   0.02034   0.01132  -0.0347   0.5949   0.1067
  -7.250  -0.4549   0.02005   0.01098  -0.0338   0.5864   0.1088
  -7.000  -0.4309   0.01978   0.01065  -0.0330   0.5783   0.1112
  -6.750  -0.4064   0.01950   0.01028  -0.0323   0.5699   0.1135
  -6.500  -0.3818   0.01926   0.00988  -0.0315   0.5628   0.1158
  -6.250  -0.3574   0.01889   0.00954  -0.0308   0.5551   0.1180
  -6.000  -0.3331   0.01863   0.00924  -0.0301   0.5477   0.1202
  -5.750  -0.3084   0.01841   0.00895  -0.0294   0.5409   0.1226
  -5.500  -0.2833   0.01818   0.00866  -0.0287   0.5336   0.1253
  -5.250  -0.2582   0.01800   0.00837  -0.0281   0.5270   0.1280
  -5.000  -0.2340   0.01772   0.00809  -0.0273   0.5214   0.1307
  -4.750  -0.2093   0.01750   0.00787  -0.0266   0.5149   0.1334
  -4.500  -0.1845   0.01733   0.00764  -0.0260   0.5088   0.1366
  -4.250  -0.1594   0.01720   0.00742  -0.0253   0.5033   0.1401
  -4.000  -0.1347   0.01699   0.00723  -0.0246   0.4974   0.1436
  -3.750  -0.1102   0.01681   0.00705  -0.0239   0.4920   0.1474
  -3.500  -0.0855   0.01669   0.00686  -0.0232   0.4872   0.1517
  -3.250  -0.0602   0.01659   0.00671  -0.0226   0.4824   0.1563
  -3.000  -0.0361   0.01640   0.00658  -0.0218   0.4770   0.1617
  -2.750  -0.0113   0.01628   0.00645  -0.0211   0.4719   0.1681
  -2.500   0.0131   0.01619   0.00631  -0.0204   0.4673   0.1747
  -2.250   0.0375   0.01607   0.00621  -0.0197   0.4631   0.1832
  -2.000   0.0622   0.01595   0.00614  -0.0190   0.4586   0.1935
  -1.500   0.1105   0.01574   0.00600  -0.0175   0.4500   0.2249
  -1.000   0.1572   0.01547   0.00593  -0.0158   0.4418   0.2800
  -0.750   0.1798   0.01531   0.00593  -0.0148   0.4376   0.3181
  -0.500   0.2019   0.01516   0.00591  -0.0137   0.4337   0.3600
  -0.250   0.2229   0.01498   0.00588  -0.0124   0.4303   0.4091
   0.250   0.2575   0.01437   0.00594  -0.0082   0.4239   0.5802
   0.500   0.2777   0.01405   0.00607  -0.0064   0.4200   0.6807
   0.750   0.3214   0.01402   0.00639  -0.0091   0.4155   0.7906
   1.000   0.3793   0.01429   0.00668  -0.0146   0.4111   0.8425
   1.250   0.4259   0.01459   0.00693  -0.0181   0.4075   0.8696
   1.500   0.4664   0.01486   0.00720  -0.0203   0.4037   0.8870
   1.750   0.5021   0.01514   0.00746  -0.0217   0.4000   0.9020
   2.000   0.5385   0.01551   0.00778  -0.0230   0.3964   0.9191
   2.250   0.5773   0.01592   0.00810  -0.0248   0.3929   0.9345
   2.500   0.6186   0.01628   0.00836  -0.0272   0.3896   0.9440
   2.750   0.6532   0.01652   0.00861  -0.0286   0.3860   0.9512
   3.000   0.6931   0.01676   0.00883  -0.0311   0.3825   0.9573
   3.250   0.7264   0.01702   0.00906  -0.0323   0.3793   0.9652
   3.500   0.7665   0.01722   0.00919  -0.0349   0.3763   0.9695
   3.750   0.7990   0.01743   0.00931  -0.0361   0.3736   0.9740
   4.000   0.8269   0.01766   0.00952  -0.0364   0.3708   0.9787
   4.250   0.8624   0.01782   0.00971  -0.0383   0.3674   0.9816
   4.500   0.8980   0.01800   0.00990  -0.0402   0.3640   0.9856
   4.750   0.9318   0.01822   0.01009  -0.0418   0.3612   0.9900
   5.000   0.9654   0.01840   0.01024  -0.0434   0.3585   0.9934
   5.250   0.9978   0.01859   0.01037  -0.0447   0.3562   0.9962
   5.500   1.0294   0.01882   0.01057  -0.0460   0.3537   0.9989
   5.750   1.0529   0.01906   0.01088  -0.0457   0.3509   1.0000
   6.000   1.0693   0.01933   0.01118  -0.0441   0.3481   1.0000
   6.250   1.0855   0.01960   0.01146  -0.0424   0.3456   1.0000
   6.500   1.1013   0.01987   0.01175  -0.0407   0.3433   1.0000
   6.750   1.1170   0.02016   0.01201  -0.0389   0.3412   1.0000
   7.000   1.1329   0.02045   0.01226  -0.0372   0.3391   1.0000
   7.250   1.1480   0.02077   0.01256  -0.0353   0.3369   1.0000
   7.500   1.1590   0.02115   0.01302  -0.0329   0.3345   1.0000
   7.750   1.1693   0.02154   0.01346  -0.0304   0.3321   1.0000
   8.000   1.1788   0.02193   0.01388  -0.0277   0.3297   1.0000
   8.250   1.1872   0.02231   0.01429  -0.0249   0.3273   1.0000
   8.500   1.1926   0.02267   0.01465  -0.0216   0.3251   1.0000
   8.750   1.1975   0.02301   0.01497  -0.0182   0.3230   1.0000
   9.000   1.2074   0.02338   0.01529  -0.0156   0.3211   1.0000
   9.250   1.2080   0.02396   0.01594  -0.0121   0.3189   1.0000
   9.500   1.2084   0.02467   0.01674  -0.0089   0.3165   1.0000
   9.750   1.2114   0.02542   0.01755  -0.0062   0.3139   1.0000
  10.000   1.2168   0.02618   0.01835  -0.0039   0.3114   1.0000
  10.250   1.2241   0.02692   0.01911  -0.0020   0.3090   1.0000
  10.500   1.2350   0.02756   0.01974  -0.0005   0.3067   1.0000
  10.750   1.2500   0.02809   0.02023   0.0007   0.3048   1.0000
  11.000   1.2554   0.02912   0.02132   0.0024   0.3026   1.0000
  11.250   1.2556   0.03049   0.02281   0.0042   0.3000   1.0000
  11.500   1.2579   0.03183   0.02424   0.0057   0.2973   1.0000
  11.750   1.2619   0.03313   0.02559   0.0070   0.2946   1.0000
  12.000   1.2692   0.03425   0.02674   0.0081   0.2920   1.0000
  12.250   1.2821   0.03503   0.02751   0.0089   0.2899   1.0000
  12.500   1.2991   0.03558   0.02802   0.0096   0.2878   1.0000
  12.750   1.2877   0.03821   0.03083   0.0109   0.2849   1.0000
  13.000   1.2808   0.04067   0.03342   0.0119   0.2818   1.0000
  13.250   1.2782   0.04286   0.03569   0.0127   0.2789   1.0000
  13.500   1.2819   0.04458   0.03745   0.0132   0.2762   1.0000
  13.750   1.2961   0.04540   0.03825   0.0136   0.2741   1.0000
  14.000   1.3077   0.04646   0.03932   0.0141   0.2716   1.0000
  14.250   1.2682   0.05265   0.04576   0.0142   0.2668   1.0000
  14.500   1.2532   0.05667   0.04989   0.0141   0.2628   1.0000
  14.750   1.2591   0.05850   0.05174   0.0142   0.2601   1.0000
  15.000   1.2786   0.05882   0.05204   0.0145   0.2583   1.0000
  15.250   1.1907   0.07176   0.06529   0.0126   0.2497   1.0000
  15.500   1.1866   0.07501   0.06858   0.0122   0.2461   1.0000
  15.750   1.2065   0.07526   0.06883   0.0124   0.2443   1.0000
  16.000   1.2343   0.07454   0.06808   0.0128   0.2430   1.0000
  16.500   1.1056   0.09725   0.09111   0.0080   0.2256   1.0000
  16.750   1.1499   0.09408   0.08791   0.0089   0.2267   1.0000
<< Back to GOE 735 AIRFOIL (goe735-il)

Polar data table (+)

Polar graphs


<< Back to GOE 735 AIRFOIL (goe735-il)