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GOE 652 AIRFOIL (goe652-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: GOE 652 AIRFOIL (goe652-il)
Reynolds number: 500,000
Max Cl/Cd: 102.76 at α=2.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe652-il-500000-n5.txt
Download as CSV file: xf-goe652-il-500000-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 =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.500  -0.0185   0.06269   0.05832  -0.1692   0.8267   0.0520
 -11.250  -0.0450   0.05656   0.05200  -0.1733   0.8181   0.0525
 -11.000  -0.0353   0.05512   0.05055  -0.1739   0.8109   0.0529
 -10.750  -0.0264   0.05354   0.04894  -0.1746   0.8044   0.0533
 -10.500  -0.0205   0.05166   0.04702  -0.1754   0.7984   0.0536
 -10.250  -0.0172   0.04965   0.04500  -0.1761   0.7922   0.0541
 -10.000  -0.0140   0.04772   0.04303  -0.1766   0.7856   0.0545
  -9.750  -0.0129   0.04573   0.04098  -0.1770   0.7796   0.0549
  -9.500  -0.0139   0.04386   0.03909  -0.1769   0.7744   0.0554
  -9.250  -0.0139   0.04204   0.03726  -0.1770   0.7688   0.0559
  -9.000  -0.0089   0.04007   0.03523  -0.1783   0.7631   0.0564
  -8.750   0.0005   0.03824   0.03333  -0.1799   0.7577   0.0569
  -8.500   0.0124   0.03637   0.03141  -0.1821   0.7529   0.0574
  -8.250   0.0275   0.03449   0.02949  -0.1847   0.7476   0.0579
  -8.000   0.0471   0.03300   0.02800  -0.1872   0.7423   0.0585
  -7.750   0.0692   0.03117   0.02613  -0.1909   0.7375   0.0593
  -7.500   0.0953   0.02916   0.02406  -0.1957   0.7331   0.0601
  -7.250   0.1261   0.02715   0.02201  -0.2013   0.7289   0.0611
  -7.000   0.1617   0.02511   0.01990  -0.2077   0.7242   0.0622
  -6.750   0.2005   0.02325   0.01794  -0.2141   0.7192   0.0633
  -6.500   0.2473   0.02093   0.01551  -0.2230   0.7135   0.0648
  -6.250   0.2971   0.01870   0.01319  -0.2319   0.7075   0.0668
  -6.000   0.3436   0.01702   0.01138  -0.2388   0.7005   0.0690
  -5.750   0.3935   0.01513   0.00934  -0.2466   0.6941   0.0716
  -5.500   0.4363   0.01389   0.00797  -0.2515   0.6886   0.0745
  -5.250   0.4740   0.01319   0.00720  -0.2543   0.6827   0.0772
  -5.000   0.5088   0.01274   0.00668  -0.2562   0.6767   0.0805
  -4.750   0.5421   0.01243   0.00629  -0.2575   0.6714   0.0837
  -4.500   0.5752   0.01214   0.00596  -0.2587   0.6661   0.0875
  -4.250   0.6073   0.01191   0.00569  -0.2595   0.6592   0.0914
  -4.000   0.6385   0.01175   0.00546  -0.2601   0.6517   0.0958
  -3.750   0.6698   0.01159   0.00526  -0.2607   0.6451   0.0999
  -3.500   0.7008   0.01147   0.00510  -0.2612   0.6380   0.1043
  -3.250   0.7311   0.01138   0.00495  -0.2615   0.6310   0.1082
  -3.000   0.7615   0.01131   0.00484  -0.2618   0.6248   0.1126
  -2.750   0.7917   0.01124   0.00474  -0.2620   0.6174   0.1168
  -2.500   0.8212   0.01122   0.00467  -0.2622   0.6098   0.1218
  -2.250   0.8508   0.01119   0.00461  -0.2623   0.6034   0.1263
  -2.000   0.8804   0.01117   0.00457  -0.2623   0.5956   0.1313
  -1.500   0.9382   0.01122   0.00454  -0.2622   0.5802   0.1408
  -1.250   0.9668   0.01127   0.00454  -0.2620   0.5725   0.1461
  -1.000   0.9949   0.01134   0.00458  -0.2618   0.5657   0.1518
  -0.750   1.0238   0.01138   0.00461  -0.2617   0.5593   0.1578
  -0.500   1.0519   0.01146   0.00465  -0.2615   0.5517   0.1626
  -0.250   1.0793   0.01157   0.00472  -0.2611   0.5445   0.1671
   0.000   1.1076   0.01164   0.00477  -0.2609   0.5376   0.1715
   0.250   1.1352   0.01174   0.00484  -0.2605   0.5300   0.1754
   0.500   1.1622   0.01187   0.00494  -0.2601   0.5232   0.1795
   0.750   1.1900   0.01196   0.00502  -0.2598   0.5164   0.1838
   1.000   1.2167   0.01211   0.00511  -0.2593   0.5086   0.1872
   1.250   1.2432   0.01225   0.00523  -0.2587   0.5005   0.1911
   1.500   1.2694   0.01240   0.00536  -0.2582   0.4895   0.1952
   1.750   1.2943   0.01262   0.00551  -0.2573   0.4778   0.1990
   2.000   1.3184   0.01287   0.00568  -0.2564   0.4639   0.2023
   2.250   1.3431   0.01307   0.00584  -0.2556   0.4504   0.2059
   2.500   1.3665   0.01334   0.00606  -0.2545   0.4359   0.2099
   2.750   1.3884   0.01367   0.00631  -0.2532   0.4190   0.2139
   3.000   1.4090   0.01406   0.00659  -0.2517   0.4010   0.2175
   3.250   1.4286   0.01448   0.00690  -0.2500   0.3847   0.2206
   3.500   1.4486   0.01485   0.00722  -0.2484   0.3713   0.2244
   3.750   1.4663   0.01524   0.00756  -0.2464   0.3605   0.2282
   4.000   1.4830   0.01565   0.00792  -0.2442   0.3505   0.2322
   4.250   1.5005   0.01605   0.00829  -0.2422   0.3428   0.2361
   4.500   1.5198   0.01640   0.00862  -0.2405   0.3371   0.2393
   4.750   1.5387   0.01677   0.00898  -0.2388   0.3326   0.2432
   5.000   1.5567   0.01719   0.00941  -0.2370   0.3283   0.2480
   5.250   1.5755   0.01758   0.00982  -0.2353   0.3249   0.2527
   5.500   1.5953   0.01794   0.01020  -0.2338   0.3222   0.2571
   5.750   1.6145   0.01833   0.01061  -0.2322   0.3194   0.2611
   6.000   1.6333   0.01876   0.01107  -0.2307   0.3165   0.2666
   6.250   1.6509   0.01924   0.01159  -0.2289   0.3137   0.2722
   6.500   1.6676   0.01980   0.01215  -0.2271   0.3105   0.2774
   6.750   1.6829   0.02044   0.01279  -0.2251   0.3071   0.2820
   7.000   1.7008   0.02097   0.01337  -0.2236   0.3047   0.2870
   7.250   1.7194   0.02147   0.01392  -0.2221   0.3025   0.2934
   7.500   1.7373   0.02202   0.01452  -0.2206   0.2996   0.2999
   7.750   1.7541   0.02265   0.01518  -0.2190   0.2966   0.3051
   8.000   1.7699   0.02336   0.01592  -0.2173   0.2936   0.3106
   8.250   1.7849   0.02414   0.01672  -0.2156   0.2906   0.3164
   8.500   1.7984   0.02503   0.01764  -0.2138   0.2876   0.3221
   8.750   1.8145   0.02578   0.01843  -0.2122   0.2850   0.3277
   9.000   1.8319   0.02646   0.01918  -0.2109   0.2824   0.3341
   9.250   1.8477   0.02725   0.02003  -0.2094   0.2791   0.3405
   9.500   1.8624   0.02815   0.02095  -0.2079   0.2752   0.3461
   9.750   1.8747   0.02924   0.02206  -0.2061   0.2712   0.3508
  10.000   1.8866   0.03040   0.02324  -0.2044   0.2674   0.3564
  10.250   1.9028   0.03124   0.02416  -0.2032   0.2645   0.3633
  10.500   1.9170   0.03226   0.02523  -0.2017   0.2606   0.3695
  10.750   1.9294   0.03344   0.02645  -0.2002   0.2556   0.3750
  11.000   1.9381   0.03497   0.02798  -0.1985   0.2502   0.3805
  11.250   1.9514   0.03613   0.02919  -0.1971   0.2438   0.3869
  11.500   1.9597   0.03777   0.03083  -0.1955   0.2362   0.3926
  11.750   1.9695   0.03932   0.03242  -0.1940   0.2294   0.3993
  12.000   1.9760   0.04122   0.03431  -0.1924   0.2201   0.4058
  12.250   1.9807   0.04335   0.03643  -0.1908   0.2087   0.4119
  12.500   1.9824   0.04587   0.03893  -0.1891   0.1976   0.4182
  12.750   1.9841   0.04847   0.04152  -0.1876   0.1889   0.4251
  13.000   1.9874   0.05097   0.04403  -0.1862   0.1823   0.4318
  13.250   1.9901   0.05360   0.04668  -0.1849   0.1770   0.4392
  13.500   1.9955   0.05599   0.04912  -0.1838   0.1734   0.4488
  13.750   2.0014   0.05837   0.05156  -0.1828   0.1698   0.4592
  14.000   2.0046   0.06112   0.05437  -0.1818   0.1664   0.4707
  14.250   2.0069   0.06404   0.05734  -0.1809   0.1630   0.4830
  14.500   2.0134   0.06648   0.05988  -0.1802   0.1607   0.4996
  14.750   2.0198   0.06898   0.06248  -0.1795   0.1583   0.5254
  15.000   2.0248   0.07170   0.06531  -0.1789   0.1557   0.5653
  15.250   2.0274   0.07476   0.06853  -0.1784   0.1530   0.6616
  15.500   2.0266   0.07765   0.07166  -0.1774   0.1505   1.0000
  15.750   2.0298   0.08065   0.07472  -0.1769   0.1484   1.0000
  16.000   2.0365   0.08317   0.07731  -0.1764   0.1462   1.0000
  16.250   2.0396   0.08624   0.08044  -0.1761   0.1436   1.0000
  16.500   2.0418   0.08943   0.08368  -0.1758   0.1409   1.0000
  16.750   2.0402   0.09325   0.08754  -0.1756   0.1382   1.0000
  17.000   2.0420   0.09654   0.09089  -0.1755   0.1357   1.0000
  17.250   2.0459   0.09954   0.09396  -0.1754   0.1331   1.0000
  17.500   2.0475   0.10289   0.09737  -0.1755   0.1298   1.0000
  17.750   2.0456   0.10680   0.10133  -0.1757   0.1266   1.0000
  18.000   2.0449   0.11051   0.10509  -0.1760   0.1238   1.0000
  18.250   2.0472   0.11375   0.10840  -0.1762   0.1203   1.0000
  18.500   2.0448   0.11775   0.11245  -0.1768   0.1166   1.0000
  18.750   2.0417   0.12185   0.11658  -0.1775   0.1133   1.0000
  19.000   2.0401   0.12569   0.12049  -0.1782   0.1090   1.0000
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