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GOE 652 AIRFOIL (goe652-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: GOE 652 AIRFOIL (goe652-il)
Reynolds number: 200,000
Max Cl/Cd: 77.96 at α=3.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe652-il-200000-n5.txt
Download as CSV file: xf-goe652-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 652 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
  ------ -------- --------- --------- -------- -------- --------
 -10.000   0.2722   0.09530   0.09019  -0.1473   0.8589   0.0602
  -9.750   0.2847   0.09277   0.08762  -0.1492   0.8517   0.0604
  -9.500   0.2986   0.09019   0.08497  -0.1515   0.8456   0.0610
  -9.250   0.3053   0.08787   0.08264  -0.1522   0.8383   0.0615
  -9.000   0.3132   0.08540   0.08014  -0.1533   0.8313   0.0616
  -8.750   0.3217   0.08269   0.07737  -0.1549   0.8251   0.0618
  -8.500   0.3273   0.08008   0.07473  -0.1559   0.8190   0.0620
  -8.250   0.3295   0.07730   0.07194  -0.1565   0.8124   0.0624
  -8.000   0.3203   0.07252   0.06711  -0.1585   0.8060   0.0635
  -7.750   0.3394   0.07178   0.06634  -0.1589   0.8011   0.0641
  -7.500   0.3495   0.07053   0.06511  -0.1586   0.7952   0.0646
  -6.500   0.1697   0.03670   0.03083  -0.1788   0.7628   0.0764
  -6.250   0.1954   0.03573   0.02984  -0.1810   0.7583   0.0776
  -6.000   0.2230   0.03252   0.02652  -0.1889   0.7535   0.0797
  -5.750   0.2650   0.02829   0.02207  -0.2017   0.7480   0.0828
  -5.500   0.2997   0.02720   0.02099  -0.2056   0.7431   0.0848
  -5.250   0.3544   0.02435   0.01793  -0.2170   0.7388   0.0891
  -5.000   0.4017   0.02284   0.01633  -0.2239   0.7347   0.0926
  -4.750   0.4555   0.02067   0.01398  -0.2333   0.7286   0.0978
  -4.500   0.4979   0.01959   0.01286  -0.2382   0.7216   0.1017
  -4.250   0.5433   0.01847   0.01154  -0.2435   0.7157   0.1070
  -4.000   0.5813   0.01792   0.01091  -0.2463   0.7104   0.1118
  -3.750   0.6167   0.01746   0.01039  -0.2485   0.7044   0.1168
  -3.500   0.6507   0.01715   0.01002  -0.2500   0.6985   0.1217
  -3.250   0.6852   0.01684   0.00959  -0.2515   0.6927   0.1267
  -3.000   0.7167   0.01667   0.00939  -0.2523   0.6860   0.1317
  -2.750   0.7486   0.01647   0.00912  -0.2531   0.6790   0.1370
  -2.500   0.7797   0.01639   0.00900  -0.2536   0.6735   0.1419
  -2.250   0.8118   0.01625   0.00874  -0.2544   0.6684   0.1478
  -2.000   0.8405   0.01627   0.00881  -0.2544   0.6617   0.1525
  -1.750   0.8713   0.01618   0.00859  -0.2548   0.6548   0.1588
  -1.500   0.9009   0.01621   0.00859  -0.2549   0.6487   0.1633
  -1.250   0.9291   0.01622   0.00859  -0.2547   0.6407   0.1685
  -1.000   0.9589   0.01616   0.00842  -0.2549   0.6329   0.1737
  -0.750   0.9872   0.01623   0.00848  -0.2547   0.6263   0.1778
  -0.500   1.0155   0.01627   0.00851  -0.2546   0.6194   0.1827
  -0.250   1.0449   0.01626   0.00838  -0.2547   0.6129   0.1878
   0.000   1.0731   0.01634   0.00846  -0.2544   0.6070   0.1917
   0.250   1.1004   0.01642   0.00856  -0.2541   0.6002   0.1963
   0.500   1.1287   0.01647   0.00853  -0.2539   0.5933   0.2014
   0.750   1.1569   0.01654   0.00852  -0.2537   0.5871   0.2057
   1.000   1.1835   0.01665   0.00869  -0.2533   0.5801   0.2097
   1.250   1.2103   0.01677   0.00879  -0.2528   0.5727   0.2144
   1.500   1.2377   0.01689   0.00878  -0.2524   0.5657   0.2194
   1.750   1.2639   0.01699   0.00891  -0.2519   0.5577   0.2236
   2.000   1.2893   0.01716   0.00907  -0.2512   0.5495   0.2277
   2.250   1.3148   0.01734   0.00922  -0.2505   0.5417   0.2324
   2.500   1.3400   0.01751   0.00936  -0.2498   0.5331   0.2373
   2.750   1.3650   0.01770   0.00945  -0.2491   0.5250   0.2417
   3.000   1.3891   0.01789   0.00970  -0.2482   0.5162   0.2458
   3.250   1.4118   0.01815   0.00993  -0.2470   0.5064   0.2503
   3.500   1.4344   0.01840   0.01016  -0.2458   0.4960   0.2550
   3.750   1.4553   0.01871   0.01037  -0.2444   0.4845   0.2597
   4.000   1.4762   0.01899   0.01065  -0.2430   0.4724   0.2641
   4.250   1.4947   0.01936   0.01100  -0.2412   0.4605   0.2683
   4.500   1.5121   0.01973   0.01135  -0.2392   0.4479   0.2727
   4.750   1.5275   0.02014   0.01172  -0.2368   0.4360   0.2774
   5.250   1.5553   0.02117   0.01264  -0.2319   0.4110   0.2867
   5.500   1.5682   0.02180   0.01323  -0.2293   0.4000   0.2910
   5.750   1.5814   0.02246   0.01385  -0.2269   0.3900   0.2958
   6.000   1.5953   0.02314   0.01449  -0.2247   0.3824   0.3011
   6.250   1.6104   0.02381   0.01514  -0.2228   0.3752   0.3066
   6.500   1.6239   0.02458   0.01591  -0.2206   0.3687   0.3115
   6.750   1.6387   0.02534   0.01666  -0.2187   0.3633   0.3172
   7.000   1.6547   0.02605   0.01740  -0.2170   0.3578   0.3234
   7.250   1.6694   0.02688   0.01820  -0.2152   0.3525   0.3290
   7.500   1.6832   0.02778   0.01910  -0.2133   0.3476   0.3344
   7.750   1.6992   0.02858   0.01993  -0.2118   0.3434   0.3411
   8.000   1.7156   0.02937   0.02076  -0.2103   0.3393   0.3483
   8.250   1.7312   0.03023   0.02166  -0.2088   0.3352   0.3540
   8.500   1.7460   0.03116   0.02261  -0.2072   0.3312   0.3601
   8.750   1.7609   0.03213   0.02356  -0.2057   0.3278   0.3672
   9.000   1.7768   0.03305   0.02451  -0.2043   0.3246   0.3740
   9.250   1.7925   0.03394   0.02551  -0.2029   0.3212   0.3810
   9.500   1.8073   0.03492   0.02655  -0.2015   0.3175   0.3886
   9.750   1.8211   0.03599   0.02766  -0.2000   0.3137   0.3951
  10.000   1.8342   0.03713   0.02884  -0.1985   0.3100   0.4021
  10.250   1.8482   0.03826   0.02994  -0.1970   0.3067   0.4103
  10.500   1.8618   0.03937   0.03116  -0.1956   0.3034   0.4177
  10.750   1.8740   0.04059   0.03250  -0.1942   0.2996   0.4257
  11.000   1.8851   0.04191   0.03391  -0.1927   0.2952   0.4340
  11.250   1.8946   0.04339   0.03543  -0.1911   0.2907   0.4421
  11.500   1.9041   0.04491   0.03693  -0.1896   0.2864   0.4514
  11.750   1.9135   0.04644   0.03862  -0.1881   0.2818   0.4600
  12.000   1.9216   0.04813   0.04042  -0.1867   0.2765   0.4702
  12.250   1.9280   0.05000   0.04234  -0.1852   0.2712   0.4806
  12.500   1.9348   0.05192   0.04430  -0.1838   0.2664   0.4930
  12.750   1.9424   0.05381   0.04635  -0.1826   0.2606   0.5069
  13.000   1.9471   0.05602   0.04864  -0.1813   0.2546   0.5223
  13.250   1.9517   0.05831   0.05101  -0.1801   0.2491   0.5428
  13.500   1.9573   0.06058   0.05344  -0.1791   0.2423   0.5737
  13.750   1.9598   0.06323   0.05620  -0.1781   0.2359   0.6286
  14.000   1.9628   0.06561   0.05885  -0.1771   0.2294   1.0000
  14.250   1.9640   0.06859   0.06186  -0.1762   0.2223   1.0000
  14.500   1.9651   0.07164   0.06494  -0.1754   0.2156   1.0000
  14.750   1.9645   0.07499   0.06831  -0.1747   0.2086   1.0000
  15.000   1.9629   0.07851   0.07185  -0.1741   0.2024   1.0000
  15.250   1.9622   0.08200   0.07537  -0.1737   0.1965   1.0000
  15.500   1.9586   0.08590   0.07927  -0.1733   0.1913   1.0000
  15.750   1.9589   0.08933   0.08275  -0.1730   0.1868   1.0000
  16.000   1.9577   0.09299   0.08646  -0.1728   0.1824   1.0000
  16.250   1.9554   0.09683   0.09030  -0.1728   0.1783   1.0000
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