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GOE 525 AIRFOIL (goe525-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 525 AIRFOIL (goe525-il)
Reynolds number: 1,000,000
Max Cl/Cd: 120.59 at α=0.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe525-il-1000000.txt
Download as CSV file: xf-goe525-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 525 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.500   0.3909   0.08916   0.08689  -0.1930   0.9224   0.0251
 -11.250   0.3874   0.08418   0.08188  -0.1969   0.9149   0.0274
 -11.000   0.4016   0.08044   0.07809  -0.2004   0.9104   0.0276
 -10.750   0.4119   0.07942   0.07706  -0.1993   0.9036   0.0278
 -10.500   0.4279   0.07769   0.07530  -0.2006   0.8970   0.0280
 -10.250   0.4411   0.07615   0.07372  -0.2012   0.8899   0.0284
 -10.000   0.4513   0.07436   0.07191  -0.2018   0.8825   0.0287
  -9.750   0.4634   0.07235   0.06985  -0.2031   0.8759   0.0293
  -9.500   0.4689   0.07023   0.06773  -0.2034   0.8686   0.0304
  -9.000   0.2058   0.02567   0.02260  -0.2317   0.8325   0.0287
  -8.750   0.2329   0.02239   0.01910  -0.2410   0.8251   0.0290
  -8.500   0.2665   0.02009   0.01661  -0.2483   0.8184   0.0294
  -8.250   0.3000   0.01823   0.01449  -0.2534   0.8123   0.0298
  -8.000   0.3323   0.01672   0.01277  -0.2568   0.8065   0.0300
  -7.750   0.3637   0.01558   0.01145  -0.2592   0.7996   0.0303
  -7.500   0.3949   0.01471   0.01038  -0.2611   0.7929   0.0305
  -7.250   0.4253   0.01395   0.00950  -0.2624   0.7858   0.0308
  -7.000   0.4550   0.01339   0.00878  -0.2634   0.7777   0.0311
  -6.750   0.4845   0.01290   0.00819  -0.2641   0.7691   0.0313
  -6.500   0.5125   0.01259   0.00773  -0.2644   0.7589   0.0315
  -6.250   0.5420   0.01180   0.00684  -0.2653   0.7480   0.0319
  -6.000   0.5701   0.01129   0.00625  -0.2658   0.7364   0.0324
  -5.750   0.5965   0.01107   0.00595  -0.2657   0.7229   0.0330
  -5.500   0.6221   0.01091   0.00569  -0.2654   0.7076   0.0334
  -5.250   0.6480   0.01075   0.00544  -0.2652   0.6922   0.0339
  -5.000   0.6740   0.01061   0.00520  -0.2649   0.6781   0.0343
  -4.750   0.7004   0.01049   0.00499  -0.2647   0.6664   0.0347
  -4.250   0.7538   0.01030   0.00464  -0.2645   0.6462   0.0356
  -4.000   0.7791   0.01029   0.00453  -0.2640   0.6368   0.0360
  -3.750   0.8089   0.01007   0.00426  -0.2646   0.6294   0.0367
  -3.500   0.8363   0.00997   0.00410  -0.2647   0.6218   0.0376
  -3.250   0.8637   0.00992   0.00401  -0.2646   0.6157   0.0385
  -3.000   0.8905   0.00988   0.00393  -0.2645   0.6094   0.0397
  -2.750   0.9147   0.00991   0.00390  -0.2637   0.6026   0.0408
  -2.500   0.9420   0.00984   0.00380  -0.2637   0.5968   0.0421
  -2.250   0.9687   0.00980   0.00374  -0.2635   0.5906   0.0441
  -2.000   0.9929   0.00986   0.00373  -0.2628   0.5843   0.0462
  -1.750   1.0197   0.00983   0.00370  -0.2626   0.5787   0.0506
  -1.500   1.0464   0.00980   0.00369  -0.2625   0.5723   0.0626
  -1.250   1.0723   0.00976   0.00374  -0.2623   0.5653   0.1113
  -1.000   1.0992   0.00976   0.00381  -0.2622   0.5595   0.1422
  -0.750   1.1244   0.00983   0.00388  -0.2618   0.5524   0.1601
  -0.500   1.1479   0.00995   0.00399  -0.2610   0.5450   0.1786
  -0.250   1.1743   0.00997   0.00408  -0.2609   0.5377   0.2171
   0.000   1.1972   0.01009   0.00424  -0.2601   0.5293   0.2621
   0.250   1.2219   0.01019   0.00437  -0.2595   0.5213   0.2916
   0.500   1.2436   0.01038   0.00454  -0.2585   0.5115   0.3191
   0.750   1.2674   0.01051   0.00470  -0.2578   0.5019   0.3474
   1.000   1.2881   0.01075   0.00492  -0.2566   0.4915   0.3779
   1.250   1.3108   0.01092   0.00513  -0.2558   0.4820   0.4143
   1.500   1.3318   0.01118   0.00537  -0.2546   0.4731   0.4397
   1.750   1.3544   0.01139   0.00558  -0.2537   0.4651   0.4597
   2.000   1.3743   0.01171   0.00586  -0.2523   0.4572   0.4773
   2.250   1.3969   0.01193   0.00608  -0.2515   0.4508   0.4945
   2.500   1.4171   0.01224   0.00637  -0.2502   0.4434   0.5082
   2.750   1.4386   0.01252   0.00663  -0.2492   0.4374   0.5208
   3.000   1.4605   0.01278   0.00689  -0.2482   0.4315   0.5323
   3.250   1.4803   0.01313   0.00721  -0.2469   0.4257   0.5408
   3.500   1.5010   0.01345   0.00751  -0.2458   0.4207   0.5495
   3.750   1.5232   0.01371   0.00777  -0.2450   0.4164   0.5570
   4.000   1.5439   0.01403   0.00810  -0.2439   0.4116   0.5658
   4.250   1.5629   0.01445   0.00847  -0.2425   0.4064   0.5741
   4.500   1.5842   0.01474   0.00880  -0.2416   0.4027   0.5815
   4.750   1.6055   0.01505   0.00911  -0.2406   0.3989   0.5886
   5.000   1.6256   0.01542   0.00947  -0.2395   0.3946   0.5951
   5.250   1.6441   0.01587   0.00992  -0.2382   0.3896   0.6015
   5.500   1.6644   0.01624   0.01029  -0.2371   0.3853   0.6069
   5.750   1.6848   0.01660   0.01065  -0.2361   0.3807   0.6120
   6.000   1.7035   0.01705   0.01111  -0.2349   0.3759   0.6174
   6.250   1.7205   0.01761   0.01164  -0.2334   0.3708   0.6229
   6.500   1.7416   0.01796   0.01201  -0.2326   0.3677   0.6280
   6.750   1.7611   0.01837   0.01246  -0.2315   0.3637   0.6328
   7.000   1.7789   0.01890   0.01299  -0.2303   0.3591   0.6380
   7.250   1.7946   0.01955   0.01361  -0.2287   0.3537   0.6439
   7.500   1.8147   0.01996   0.01407  -0.2278   0.3506   0.6503
   7.750   1.8331   0.02047   0.01461  -0.2267   0.3468   0.6570
   8.000   1.8501   0.02108   0.01522  -0.2254   0.3424   0.6631
   8.250   1.8652   0.02180   0.01594  -0.2239   0.3375   0.6684
   8.500   1.8833   0.02235   0.01653  -0.2228   0.3340   0.6736
   8.750   1.9005   0.02297   0.01717  -0.2216   0.3294   0.6790
   9.000   1.9150   0.02377   0.01797  -0.2201   0.3237   0.6841
   9.250   1.9298   0.02457   0.01878  -0.2187   0.3180   0.6894
   9.500   1.9456   0.02531   0.01955  -0.2175   0.3126   0.6949
   9.750   1.9581   0.02631   0.02053  -0.2158   0.3061   0.7003
  10.000   1.9726   0.02717   0.02142  -0.2145   0.3011   0.7067
  10.250   1.9864   0.02810   0.02237  -0.2131   0.2953   0.7134
  10.500   1.9972   0.02927   0.02354  -0.2115   0.2890   0.7204
  10.750   2.0110   0.03024   0.02455  -0.2102   0.2843   0.7286
  11.000   2.0232   0.03136   0.02570  -0.2088   0.2782   0.7381
  11.250   2.0317   0.03278   0.02714  -0.2070   0.2720   0.7504
  11.500   2.0454   0.03382   0.02826  -0.2059   0.2671   0.7764
  11.750   2.0550   0.03493   0.02958  -0.2043   0.2616   1.0000
  12.000   2.0621   0.03659   0.03123  -0.2026   0.2562   1.0000
  12.250   2.0745   0.03781   0.03248  -0.2015   0.2516   1.0000
  12.500   2.0821   0.03949   0.03416  -0.1999   0.2462   1.0000
  12.750   2.0886   0.04130   0.03597  -0.1984   0.2407   1.0000
  13.000   2.0985   0.04282   0.03753  -0.1972   0.2366   1.0000
  13.250   2.1053   0.04466   0.03939  -0.1958   0.2315   1.0000
  13.500   2.1085   0.04692   0.04165  -0.1942   0.2261   1.0000
  13.750   2.1174   0.04862   0.04340  -0.1932   0.2212   1.0000
  14.000   2.1185   0.05120   0.04597  -0.1917   0.2147   1.0000
  14.250   2.1219   0.05357   0.04837  -0.1904   0.2082   1.0000
  14.500   2.1228   0.05628   0.05108  -0.1891   0.2012   1.0000
  14.750   2.1226   0.05919   0.05401  -0.1879   0.1946   1.0000
  15.000   2.1186   0.06261   0.05743  -0.1866   0.1855   1.0000
  15.250   2.1127   0.06635   0.06116  -0.1854   0.1744   1.0000
  15.500   2.0959   0.07158   0.06634  -0.1841   0.1585   1.0000
  15.750   2.0598   0.07958   0.07422  -0.1826   0.1316   1.0000
  16.000   2.0202   0.08843   0.08299  -0.1816   0.1074   1.0000
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