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

GOE 702 AIRFOIL (goe702-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: GOE 702 AIRFOIL (goe702-il)
Reynolds number: 200,000
Max Cl/Cd: 61.6 at α=7.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe702-il-200000-n5.txt
Download as CSV file: xf-goe702-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 702 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
  ------ -------- --------- --------- -------- -------- --------
 -12.750  -0.6390   0.04974   0.04456  -0.0864   0.8086   0.0502
 -12.500  -0.6919   0.04041   0.03482  -0.0949   0.7950   0.0502
 -12.250  -0.7146   0.03720   0.03132  -0.0940   0.7840   0.0504
 -12.000  -0.7263   0.03503   0.02885  -0.0917   0.7753   0.0508
 -11.750  -0.7200   0.03360   0.02729  -0.0903   0.7680   0.0513
 -11.500  -0.7073   0.03259   0.02624  -0.0891   0.7612   0.0519
 -11.250  -0.6939   0.03162   0.02517  -0.0879   0.7553   0.0524
 -11.000  -0.6797   0.03060   0.02404  -0.0868   0.7500   0.0531
 -10.750  -0.6644   0.02953   0.02283  -0.0858   0.7442   0.0538
 -10.500  -0.6487   0.02843   0.02156  -0.0848   0.7386   0.0547
 -10.250  -0.6322   0.02734   0.02024  -0.0836   0.7334   0.0555
 -10.000  -0.6143   0.02628   0.01894  -0.0826   0.7277   0.0564
  -9.750  -0.5943   0.02543   0.01801  -0.0818   0.7214   0.0572
  -9.500  -0.5731   0.02478   0.01731  -0.0809   0.7154   0.0580
  -9.250  -0.5514   0.02418   0.01660  -0.0800   0.7098   0.0591
  -9.000  -0.5290   0.02353   0.01587  -0.0793   0.7030   0.0603
  -8.750  -0.5066   0.02284   0.01502  -0.0785   0.6966   0.0617
  -8.500  -0.4840   0.02218   0.01416  -0.0777   0.6912   0.0630
  -8.250  -0.4602   0.02165   0.01363  -0.0770   0.6857   0.0641
  -8.000  -0.4359   0.02116   0.01311  -0.0765   0.6806   0.0655
  -7.750  -0.4115   0.02067   0.01252  -0.0758   0.6758   0.0670
  -7.500  -0.3868   0.02018   0.01188  -0.0752   0.6714   0.0689
  -7.250  -0.3618   0.01974   0.01140  -0.0746   0.6667   0.0706
  -7.000  -0.3362   0.01939   0.01104  -0.0742   0.6614   0.0725
  -6.750  -0.3104   0.01901   0.01059  -0.0736   0.6565   0.0748
  -6.500  -0.2847   0.01862   0.01007  -0.0731   0.6519   0.0771
  -6.250  -0.2587   0.01832   0.00976  -0.0726   0.6470   0.0793
  -6.000  -0.2322   0.01803   0.00944  -0.0722   0.6412   0.0822
  -5.750  -0.2058   0.01771   0.00903  -0.0717   0.6358   0.0853
  -5.500  -0.1794   0.01747   0.00875  -0.0713   0.6310   0.0881
  -5.250  -0.1524   0.01722   0.00845  -0.0709   0.6256   0.0918
  -5.000  -0.1257   0.01695   0.00815  -0.0705   0.6192   0.0953
  -4.750  -0.0989   0.01673   0.00789  -0.0700   0.6132   0.0991
  -4.500  -0.0717   0.01653   0.00757  -0.0696   0.6073   0.1034
  -4.250  -0.0450   0.01626   0.00735  -0.0693   0.6004   0.1073
  -4.000  -0.0180   0.01607   0.00710  -0.0689   0.5939   0.1118
  -3.750   0.0092   0.01587   0.00683  -0.0685   0.5873   0.1161
  -3.500   0.0360   0.01564   0.00663  -0.0681   0.5790   0.1205
  -3.250   0.0630   0.01548   0.00638  -0.0677   0.5716   0.1252
  -3.000   0.0902   0.01528   0.00619  -0.0673   0.5627   0.1298
  -2.750   0.1170   0.01510   0.00599  -0.0669   0.5544   0.1348
  -2.500   0.1442   0.01497   0.00581  -0.0666   0.5451   0.1400
  -2.250   0.1708   0.01480   0.00562  -0.0661   0.5353   0.1454
  -2.000   0.1978   0.01467   0.00549  -0.0657   0.5243   0.1517
  -1.750   0.2244   0.01456   0.00532  -0.0653   0.5136   0.1587
  -1.500   0.2510   0.01446   0.00521  -0.0649   0.5022   0.1676
  -1.250   0.2774   0.01437   0.00512  -0.0645   0.4921   0.1777
  -1.000   0.3037   0.01431   0.00504  -0.0640   0.4822   0.1901
  -0.750   0.3301   0.01427   0.00501  -0.0636   0.4729   0.2061
  -0.500   0.3560   0.01427   0.00500  -0.0631   0.4640   0.2256
  -0.250   0.3823   0.01428   0.00503  -0.0626   0.4560   0.2462
   0.000   0.4085   0.01434   0.00507  -0.0622   0.4485   0.2650
   0.250   0.4346   0.01442   0.00511  -0.0617   0.4425   0.2826
   0.500   0.4611   0.01448   0.00519  -0.0613   0.4366   0.2994
   0.750   0.4871   0.01456   0.00526  -0.0609   0.4310   0.3144
   1.000   0.5128   0.01468   0.00533  -0.0604   0.4258   0.3280
   1.250   0.5393   0.01476   0.00543  -0.0600   0.4208   0.3417
   1.500   0.5651   0.01484   0.00553  -0.0595   0.4158   0.3559
   1.750   0.5908   0.01494   0.00564  -0.0590   0.4112   0.3706
   2.000   0.6162   0.01508   0.00575  -0.0585   0.4074   0.3865
   2.500   0.6674   0.01522   0.00603  -0.0576   0.3999   0.4265
   2.750   0.6918   0.01523   0.00618  -0.0569   0.3960   0.4648
   3.000   0.7142   0.01513   0.00631  -0.0559   0.3923   0.5325
   3.500   0.8400   0.01486   0.00691  -0.0697   0.3832   1.0000
   3.750   0.8635   0.01508   0.00710  -0.0689   0.3799   1.0000
   4.000   0.8867   0.01532   0.00730  -0.0680   0.3768   1.0000
   4.250   0.9098   0.01557   0.00749  -0.0671   0.3738   1.0000
   4.500   0.9327   0.01585   0.00769  -0.0662   0.3709   1.0000
   4.750   0.9556   0.01614   0.00791  -0.0653   0.3680   1.0000
   5.000   0.9782   0.01637   0.00817  -0.0644   0.3649   1.0000
   5.250   1.0007   0.01663   0.00844  -0.0635   0.3618   1.0000
   5.500   1.0230   0.01690   0.00870  -0.0626   0.3590   1.0000
   5.750   1.0453   0.01718   0.00896  -0.0616   0.3564   1.0000
   6.000   1.0675   0.01748   0.00922  -0.0607   0.3539   1.0000
   6.250   1.0900   0.01781   0.00948  -0.0598   0.3515   1.0000
   6.500   1.1116   0.01812   0.00981  -0.0588   0.3489   1.0000
   6.750   1.1325   0.01842   0.01017  -0.0578   0.3460   1.0000
   7.000   1.1533   0.01874   0.01051  -0.0567   0.3432   1.0000
   7.250   1.1741   0.01906   0.01085  -0.0557   0.3406   1.0000
   7.500   1.1949   0.01940   0.01119  -0.0546   0.3383   1.0000
   7.750   1.2157   0.01975   0.01152  -0.0536   0.3360   1.0000
   8.000   1.2372   0.02012   0.01184  -0.0527   0.3337   1.0000
   8.250   1.2560   0.02051   0.01228  -0.0515   0.3312   1.0000
   8.500   1.2736   0.02090   0.01276  -0.0501   0.3286   1.0000
   8.750   1.2912   0.02131   0.01322  -0.0487   0.3261   1.0000
   9.000   1.3079   0.02173   0.01368  -0.0472   0.3237   1.0000
   9.250   1.3230   0.02214   0.01412  -0.0455   0.3213   1.0000
   9.500   1.3388   0.02256   0.01454  -0.0439   0.3191   1.0000
   9.750   1.3569   0.02299   0.01495  -0.0426   0.3169   1.0000
  10.000   1.3722   0.02352   0.01551  -0.0411   0.3147   1.0000
  10.250   1.3833   0.02415   0.01625  -0.0393   0.3124   1.0000
  10.500   1.3948   0.02481   0.01700  -0.0376   0.3098   1.0000
  10.750   1.4066   0.02549   0.01775  -0.0361   0.3072   1.0000
  11.000   1.4195   0.02617   0.01848  -0.0348   0.3047   1.0000
  11.250   1.4343   0.02681   0.01915  -0.0336   0.3026   1.0000
  11.500   1.4514   0.02737   0.01969  -0.0328   0.3002   1.0000
  11.750   1.4607   0.02829   0.02068  -0.0314   0.2973   1.0000
  12.000   1.4645   0.02948   0.02201  -0.0297   0.2937   1.0000
  12.250   1.4708   0.03060   0.02322  -0.0284   0.2900   1.0000
  12.500   1.4800   0.03159   0.02423  -0.0273   0.2866   1.0000
  12.750   1.4947   0.03229   0.02488  -0.0265   0.2834   1.0000
  13.000   1.4957   0.03396   0.02671  -0.0253   0.2799   1.0000
  13.250   1.4978   0.03564   0.02851  -0.0242   0.2762   1.0000
  13.500   1.5024   0.03716   0.03012  -0.0234   0.2726   1.0000
  13.750   1.5111   0.03838   0.03133  -0.0226   0.2692   1.0000
  14.000   1.5163   0.03995   0.03295  -0.0219   0.2657   1.0000
  14.250   1.5110   0.04250   0.03568  -0.0212   0.2613   1.0000
  14.500   1.5106   0.04467   0.03793  -0.0206   0.2571   1.0000
  14.750   1.5168   0.04626   0.03952  -0.0201   0.2533   1.0000
  15.000   1.5148   0.04881   0.04217  -0.0198   0.2496   1.0000
  15.250   1.5067   0.05211   0.04564  -0.0197   0.2453   1.0000
  15.500   1.5049   0.05480   0.04840  -0.0196   0.2413   1.0000
  15.750   1.5103   0.05670   0.05030  -0.0194   0.2377   1.0000
  16.000   1.4953   0.06114   0.05492  -0.0198   0.2331   1.0000
  16.250   1.4821   0.06552   0.05942  -0.0204   0.2280   1.0000
  16.500   1.4825   0.06822   0.06214  -0.0206   0.2238   1.0000
  16.750   1.4603   0.07401   0.06809  -0.0218   0.2185   1.0000
  17.000   1.4401   0.07971   0.07390  -0.0230   0.2126   1.0000
  17.250   1.4412   0.08249   0.07668  -0.0235   0.2078   1.0000
  17.500   1.3970   0.09192   0.08631  -0.0262   0.2004   1.0000
  17.750   1.4017   0.09426   0.08864  -0.0266   0.1953   1.0000
<< Back to GOE 702 AIRFOIL (goe702-il)

Polar data table (+)

Polar graphs


<< Back to GOE 702 AIRFOIL (goe702-il)