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GOE 525 AIRFOIL (goe525-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: GOE 525 AIRFOIL (goe525-il)
Reynolds number: 1,000,000
Max Cl/Cd: 104.44 at α=2.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe525-il-1000000-n5.txt
Download as CSV file: xf-goe525-il-1000000-n5.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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.500   0.0820   0.03976   0.03658  -0.2175   0.8462   0.0233
 -11.250   0.0452   0.03425   0.03094  -0.2194   0.8364   0.0233
 -11.000   0.0243   0.03053   0.02709  -0.2206   0.8281   0.0233
 -10.750   0.0197   0.02675   0.02319  -0.2248   0.8205   0.0233
 -10.500   0.0310   0.02369   0.01996  -0.2300   0.8136   0.0234
 -10.250   0.0539   0.02132   0.01746  -0.2355   0.8078   0.0235
 -10.000   0.0844   0.01894   0.01490  -0.2422   0.8016   0.0236
  -9.750   0.1190   0.01716   0.01296  -0.2480   0.7956   0.0239
  -9.500   0.1536   0.01598   0.01167  -0.2520   0.7882   0.0241
  -9.250   0.1842   0.01523   0.01079  -0.2542   0.7781   0.0242
  -9.000   0.2143   0.01463   0.01010  -0.2558   0.7665   0.0244
  -8.750   0.2435   0.01414   0.00949  -0.2570   0.7549   0.0246
  -8.500   0.2719   0.01371   0.00895  -0.2579   0.7423   0.0248
  -8.250   0.3006   0.01334   0.00847  -0.2587   0.7292   0.0250
  -8.000   0.3285   0.01302   0.00804  -0.2592   0.7153   0.0252
  -7.750   0.3552   0.01277   0.00767  -0.2594   0.6992   0.0255
  -7.500   0.3814   0.01255   0.00731  -0.2595   0.6825   0.0258
  -7.250   0.4081   0.01232   0.00695  -0.2597   0.6678   0.0260
  -7.000   0.4350   0.01212   0.00663  -0.2598   0.6554   0.0262
  -6.750   0.4634   0.01190   0.00632  -0.2602   0.6449   0.0264
  -6.500   0.4908   0.01173   0.00605  -0.2603   0.6353   0.0266
  -6.250   0.5193   0.01156   0.00580  -0.2607   0.6266   0.0268
  -6.000   0.5467   0.01143   0.00558  -0.2608   0.6189   0.0270
  -5.750   0.5760   0.01127   0.00536  -0.2612   0.6133   0.0272
  -5.500   0.6044   0.01113   0.00517  -0.2614   0.6070   0.0273
  -5.250   0.6331   0.01094   0.00490  -0.2619   0.6006   0.0277
  -5.000   0.6627   0.01077   0.00469  -0.2624   0.5952   0.0281
  -4.750   0.6905   0.01066   0.00454  -0.2625   0.5890   0.0285
  -4.500   0.7166   0.01061   0.00443  -0.2622   0.5833   0.0288
  -4.250   0.7444   0.01052   0.00432  -0.2622   0.5788   0.0292
  -4.000   0.7719   0.01045   0.00422  -0.2622   0.5737   0.0297
  -3.750   0.7980   0.01043   0.00414  -0.2619   0.5675   0.0301
  -3.500   0.8238   0.01042   0.00409  -0.2616   0.5617   0.0307
  -3.250   0.8507   0.01040   0.00403  -0.2614   0.5557   0.0312
  -3.000   0.8765   0.01041   0.00399  -0.2610   0.5493   0.0316
  -2.750   0.9025   0.01041   0.00395  -0.2607   0.5435   0.0324
  -2.500   0.9293   0.01041   0.00393  -0.2606   0.5370   0.0332
  -2.250   0.9540   0.01048   0.00395  -0.2600   0.5289   0.0340
  -2.000   0.9797   0.01054   0.00397  -0.2597   0.5218   0.0351
  -1.750   1.0047   0.01063   0.00401  -0.2591   0.5137   0.0361
  -1.500   1.0294   0.01073   0.00407  -0.2586   0.5061   0.0382
  -1.250   1.0539   0.01084   0.00415  -0.2580   0.4968   0.0409
  -1.000   1.0780   0.01097   0.00424  -0.2574   0.4878   0.0473
  -0.750   1.1029   0.01107   0.00435  -0.2570   0.4785   0.0643
  -0.500   1.1274   0.01118   0.00447  -0.2565   0.4705   0.0868
  -0.250   1.1517   0.01130   0.00463  -0.2560   0.4617   0.1176
   0.000   1.1748   0.01148   0.00479  -0.2552   0.4538   0.1349
   0.250   1.1982   0.01166   0.00495  -0.2545   0.4459   0.1463
   0.500   1.2206   0.01189   0.00514  -0.2536   0.4380   0.1594
   0.750   1.2448   0.01203   0.00532  -0.2531   0.4306   0.1863
   1.000   1.2675   0.01222   0.00559  -0.2525   0.4221   0.2500
   1.250   1.2912   0.01238   0.00580  -0.2519   0.4161   0.2854
   1.500   1.3142   0.01259   0.00602  -0.2512   0.4101   0.3094
   1.750   1.3363   0.01285   0.00627  -0.2503   0.4045   0.3296
   2.000   1.3597   0.01304   0.00649  -0.2496   0.4004   0.3487
   2.250   1.3828   0.01324   0.00672  -0.2490   0.3966   0.3683
   2.750   1.4270   0.01375   0.00727  -0.2473   0.3882   0.4177
   3.000   1.4491   0.01402   0.00756  -0.2465   0.3844   0.4413
   3.250   1.4721   0.01425   0.00782  -0.2458   0.3809   0.4583
   3.500   1.4936   0.01453   0.00811  -0.2449   0.3768   0.4723
   3.750   1.5140   0.01488   0.00846  -0.2438   0.3722   0.4850
   4.000   1.5340   0.01526   0.00883  -0.2426   0.3676   0.4969
   4.250   1.5562   0.01554   0.00913  -0.2419   0.3648   0.5111
   4.500   1.5779   0.01584   0.00946  -0.2410   0.3614   0.5238
   4.750   1.5981   0.01621   0.00983  -0.2400   0.3576   0.5321
   5.000   1.6172   0.01664   0.01026  -0.2388   0.3536   0.5393
   5.250   1.6368   0.01706   0.01068  -0.2376   0.3498   0.5482
   5.500   1.6575   0.01743   0.01106  -0.2367   0.3454   0.5557
   5.750   1.6768   0.01787   0.01151  -0.2356   0.3407   0.5619
   6.000   1.6933   0.01847   0.01208  -0.2341   0.3348   0.5681
   6.250   1.7125   0.01893   0.01254  -0.2330   0.3301   0.5735
   6.500   1.7314   0.01941   0.01304  -0.2319   0.3251   0.5789
   6.750   1.7479   0.02004   0.01366  -0.2305   0.3196   0.5839
   7.000   1.7652   0.02063   0.01424  -0.2292   0.3154   0.5889
   7.250   1.7835   0.02116   0.01480  -0.2281   0.3110   0.5952
   7.500   1.8004   0.02180   0.01544  -0.2268   0.3058   0.6032
   7.750   1.8149   0.02258   0.01621  -0.2252   0.3009   0.6092
   8.000   1.8327   0.02317   0.01684  -0.2241   0.2974   0.6151
   8.250   1.8497   0.02384   0.01752  -0.2229   0.2930   0.6214
   8.500   1.8637   0.02470   0.01838  -0.2214   0.2878   0.6271
   8.750   1.8783   0.02553   0.01922  -0.2200   0.2831   0.6313
   9.000   1.8943   0.02630   0.02002  -0.2188   0.2783   0.6355
   9.250   1.9072   0.02728   0.02100  -0.2172   0.2729   0.6397
   9.500   1.9195   0.02834   0.02205  -0.2156   0.2670   0.6438
   9.750   1.9322   0.02940   0.02310  -0.2142   0.2599   0.6479
  10.000   1.9411   0.03075   0.02445  -0.2123   0.2529   0.6524
  10.250   1.9552   0.03174   0.02547  -0.2111   0.2484   0.6572
  10.500   1.9653   0.03306   0.02679  -0.2095   0.2424   0.6615
  10.750   1.9745   0.03449   0.02822  -0.2078   0.2363   0.6654
  11.000   1.9858   0.03577   0.02953  -0.2065   0.2308   0.6699
  11.250   1.9945   0.03731   0.03108  -0.2049   0.2258   0.6750
  11.500   2.0041   0.03879   0.03258  -0.2035   0.2211   0.6801
  11.750   2.0137   0.04031   0.03413  -0.2022   0.2164   0.6853
  12.000   2.0205   0.04211   0.03595  -0.2006   0.2104   0.6908
  12.250   2.0269   0.04401   0.03787  -0.1992   0.2052   0.6961
  12.500   2.0336   0.04590   0.03978  -0.1978   0.1987   0.7017
  12.750   2.0362   0.04827   0.04217  -0.1963   0.1923   0.7083
  13.250   2.0403   0.05332   0.04725  -0.1934   0.1758   0.7250
  13.500   2.0348   0.05681   0.05072  -0.1918   0.1633   0.7350
  13.750   2.0026   0.06366   0.05743  -0.1891   0.1324   0.7414
  14.000   1.9674   0.07133   0.06501  -0.1869   0.1040   0.7467
  14.250   1.9479   0.07732   0.07100  -0.1859   0.0892   0.7612
  14.500   1.9395   0.08150   0.07542  -0.1850   0.0825   0.9353
  14.750   1.9338   0.08567   0.07964  -0.1845   0.0780   1.0000
  15.000   1.9295   0.08978   0.08380  -0.1842   0.0742   1.0000
  15.250   1.9285   0.09344   0.08753  -0.1841   0.0717   1.0000
  15.500   1.9256   0.09740   0.09155  -0.1840   0.0684   1.0000
  15.750   1.9190   0.10197   0.09617  -0.1841   0.0648   1.0000
  16.000   1.9158   0.10603   0.10028  -0.1842   0.0612   1.0000
  16.250   1.9077   0.11088   0.10516  -0.1846   0.0561   1.0000
  16.500   1.8928   0.11687   0.11115  -0.1852   0.0460   1.0000
  16.750   1.8651   0.12502   0.11929  -0.1865   0.0306   1.0000
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