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GOE 652 AIRFOIL (goe652-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 652 AIRFOIL (goe652-il)
Reynolds number: 200,000
Max Cl/Cd: 77.29 at α=5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe652-il-200000.txt
Download as CSV file: xf-goe652-il-200000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750   0.2605   0.10387   0.09948  -0.1364   0.9203   0.0938
  -9.500   0.2834   0.10110   0.09669  -0.1400   0.9158   0.0957
  -9.250   0.2854   0.09933   0.09484  -0.1498   0.9104   0.0992
  -9.000   0.3205   0.09485   0.09034  -0.1517   0.9074   0.0997
  -8.750   0.3377   0.09261   0.08810  -0.1514   0.8997   0.1003
  -8.500   0.3614   0.09022   0.08568  -0.1536   0.8944   0.1014
  -8.250   0.3864   0.08771   0.08312  -0.1572   0.8898   0.1032
  -8.000   0.3946   0.08618   0.08159  -0.1575   0.8815   0.1054
  -7.750   0.3877   0.08473   0.08010  -0.1608   0.8722   0.1079
  -7.500   0.4199   0.08168   0.07700  -0.1622   0.8682   0.1088
  -7.250   0.4302   0.08039   0.07572  -0.1607   0.8605   0.1098
  -7.000   0.4438   0.07884   0.07417  -0.1609   0.8536   0.1113
  -6.750   0.4588   0.07703   0.07230  -0.1625   0.8479   0.1141
  -6.500   0.4240   0.07736   0.07268  -0.1625   0.8364   0.1168
  -6.250   0.4533   0.07433   0.06963  -0.1622   0.8319   0.1173
  -6.000   0.4783   0.07220   0.06745  -0.1626   0.8270   0.1184
  -5.750   0.4927   0.07081   0.06605  -0.1621   0.8207   0.1198
  -5.500   0.4979   0.06974   0.06501  -0.1605   0.8125   0.1216
  -5.250   0.4560   0.07013   0.06538  -0.1615   0.8029   0.1263
  -5.000   0.4897   0.06702   0.06226  -0.1606   0.7978   0.1271
  -4.750   0.5074   0.06546   0.06073  -0.1587   0.7909   0.1280
  -4.500   0.5249   0.06398   0.05922  -0.1583   0.7850   0.1297
  -4.250   0.5404   0.06245   0.05764  -0.1589   0.7801   0.1322
  -4.000   0.4969   0.06295   0.05825  -0.1579   0.7693   0.1366
  -3.750   0.4871   0.05503   0.05024  -0.1614   0.7632   0.1164
  -3.500   0.5173   0.05509   0.05025  -0.1631   0.7585   0.1261
  -3.250   0.5256   0.05421   0.04942  -0.1599   0.7515   0.1255
  -3.000   0.5368   0.05292   0.04814  -0.1580   0.7447   0.1241
  -2.750   0.7295   0.02149   0.01530  -0.2492   0.7398   0.1548
  -2.500   0.7717   0.02083   0.01441  -0.2525   0.7358   0.1625
  -2.250   0.7906   0.02134   0.01510  -0.2500   0.7292   0.1655
  -2.000   0.8308   0.02062   0.01411  -0.2533   0.7226   0.1743
  -1.750   0.8554   0.02087   0.01450  -0.2515   0.7172   0.1773
  -1.500   0.8819   0.02118   0.01483  -0.2503   0.7119   0.1815
  -1.250   0.9176   0.02051   0.01399  -0.2527   0.7042   0.1900
  -1.000   0.9410   0.02081   0.01440  -0.2509   0.6982   0.1931
  -0.750   0.9711   0.02087   0.01442  -0.2507   0.6935   0.1983
  -0.500   1.0079   0.02029   0.01368  -0.2531   0.6876   0.2064
  -0.250   1.0306   0.02054   0.01404  -0.2516   0.6810   0.2098
   0.000   1.0601   0.02052   0.01399  -0.2514   0.6755   0.2153
   0.250   1.1012   0.01992   0.01311  -0.2543   0.6707   0.2237
   0.500   1.1223   0.02016   0.01351  -0.2526   0.6638   0.2271
   0.750   1.1491   0.02021   0.01358  -0.2520   0.6573   0.2323
   1.000   1.1883   0.01968   0.01276  -0.2544   0.6516   0.2410
   1.250   1.2129   0.01980   0.01298  -0.2534   0.6451   0.2448
   1.500   1.2374   0.01989   0.01313  -0.2524   0.6375   0.2494
   1.750   1.2710   0.01967   0.01272  -0.2533   0.6311   0.2571
   2.000   1.3002   0.01955   0.01256  -0.2535   0.6241   0.2627
   2.250   1.3240   0.01966   0.01274  -0.2523   0.6162   0.2669
   2.500   1.3535   0.01965   0.01264  -0.2523   0.6094   0.2729
   2.750   1.3821   0.01963   0.01252  -0.2524   0.6013   0.2799
   3.000   1.4077   0.01957   0.01250  -0.2517   0.5928   0.2846
   3.250   1.4357   0.01967   0.01253  -0.2513   0.5852   0.2897
   3.500   1.4579   0.01976   0.01266  -0.2501   0.5749   0.2954
   3.750   1.4889   0.01975   0.01239  -0.2504   0.5654   0.3025
   4.000   1.5080   0.01985   0.01262  -0.2486   0.5537   0.3068
   4.250   1.5330   0.02001   0.01269  -0.2478   0.5430   0.3119
   4.500   1.5532   0.02021   0.01287  -0.2462   0.5304   0.3182
   4.750   1.5763   0.02042   0.01296  -0.2452   0.5182   0.3247
   5.000   1.5968   0.02066   0.01316  -0.2436   0.5058   0.3295
   5.250   1.6142   0.02100   0.01352  -0.2416   0.4927   0.3348
   5.500   1.6346   0.02138   0.01375  -0.2401   0.4811   0.3420
   5.750   1.6515   0.02175   0.01409  -0.2381   0.4690   0.3481
   6.000   1.6686   0.02218   0.01450  -0.2361   0.4589   0.3535
   6.250   1.6831   0.02263   0.01493  -0.2337   0.4489   0.3598
   6.500   1.7011   0.02314   0.01530  -0.2319   0.4405   0.3676
   6.750   1.7151   0.02361   0.01585  -0.2295   0.4317   0.3734
   7.000   1.7328   0.02417   0.01631  -0.2278   0.4241   0.3810
   7.250   1.7487   0.02475   0.01689  -0.2258   0.4170   0.3890
   7.500   1.7652   0.02530   0.01749  -0.2240   0.4105   0.3955
   7.750   1.7857   0.02590   0.01798  -0.2228   0.4046   0.4048
   8.000   1.8026   0.02653   0.01867  -0.2212   0.3992   0.4131
   8.250   1.8183   0.02719   0.01941  -0.2193   0.3939   0.4213
   8.500   1.8373   0.02785   0.02000  -0.2180   0.3886   0.4309
   8.750   1.8616   0.02843   0.02053  -0.2175   0.3835   0.4403
   9.000   1.8738   0.02926   0.02145  -0.2153   0.3788   0.4501
   9.250   1.8886   0.03003   0.02232  -0.2136   0.3739   0.4589
   9.500   1.9077   0.03076   0.02301  -0.2124   0.3692   0.4700
   9.750   1.9365   0.03129   0.02347  -0.2125   0.3644   0.4819
  10.000   1.9449   0.03232   0.02464  -0.2100   0.3603   0.4923
  10.250   1.9565   0.03328   0.02572  -0.2079   0.3557   0.5027
  10.500   1.9710   0.03418   0.02664  -0.2063   0.3508   0.5149
  10.750   1.9988   0.03475   0.02707  -0.2062   0.3448   0.5315
  11.000   1.9980   0.03619   0.02874  -0.2029   0.3401   0.5419
  11.250   2.0035   0.03749   0.03012  -0.2004   0.3345   0.5558
  11.500   2.0181   0.03843   0.03105  -0.1989   0.3289   0.5744
  11.750   2.0322   0.03951   0.03218  -0.1974   0.3235   0.5974
  12.000   2.0317   0.04123   0.03411  -0.1946   0.3182   0.6222
  12.250   2.0375   0.04264   0.03568  -0.1925   0.3126   0.6779
  12.500   2.0594   0.04319   0.03619  -0.1918   0.3064   1.0000
  12.750   2.0512   0.04566   0.03888  -0.1888   0.3013   1.0000
  13.000   2.0516   0.04770   0.04099  -0.1866   0.2954   1.0000
  13.250   2.0622   0.04912   0.04232  -0.1851   0.2897   1.0000
  13.500   2.0617   0.05144   0.04475  -0.1831   0.2839   1.0000
  13.750   2.0580   0.05407   0.04750  -0.1811   0.2776   1.0000
  14.000   2.0640   0.05594   0.04931  -0.1796   0.2717   1.0000
  14.250   2.0624   0.05867   0.05215  -0.1780   0.2656   1.0000
  14.500   2.0586   0.06166   0.05526  -0.1764   0.2593   1.0000
  14.750   2.0645   0.06371   0.05722  -0.1752   0.2537   1.0000
  15.000   2.0609   0.06696   0.06061  -0.1740   0.2478   1.0000
  15.250   2.0584   0.07014   0.06387  -0.1729   0.2418   1.0000
  15.500   2.0641   0.07235   0.06600  -0.1720   0.2367   1.0000
  15.750   2.0599   0.07598   0.06979  -0.1712   0.2311   1.0000
  16.000   2.0585   0.07926   0.07314  -0.1705   0.2257   1.0000
  16.250   2.0634   0.08167   0.07546  -0.1698   0.2208   1.0000
  16.500   2.0596   0.08546   0.07940  -0.1694   0.2157   1.0000
  16.750   2.0573   0.08904   0.08305  -0.1691   0.2107   1.0000
  17.000   2.0629   0.09141   0.08533  -0.1686   0.2059   1.0000
  17.250   2.0587   0.09536   0.08941  -0.1685   0.2012   1.0000
  17.500   2.0558   0.09912   0.09325  -0.1685   0.1964   1.0000
  17.750   2.0623   0.10133   0.09535  -0.1681   0.1917   1.0000
  18.000   2.0592   0.10516   0.09929  -0.1683   0.1872   1.0000
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