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GOE 81 AIRFOIL (goe81-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 81 AIRFOIL (goe81-il)
Reynolds number: 200,000
Max Cl/Cd: 89.32 at α=-0.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe81-il-200000.txt
Download as CSV file: xf-goe81-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 81 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
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.2624   0.10673   0.10340  -0.0318   1.0000   0.0274
  -8.250  -0.2825   0.10708   0.10386  -0.0274   1.0000   0.0274
  -8.000  -0.3053   0.10762   0.10450  -0.0226   0.9998   0.0274
  -7.750  -0.2795   0.10270   0.09958  -0.0312   0.9943   0.0276
  -7.500  -0.2633   0.09729   0.09416  -0.0295   0.9930   0.0280
  -7.250  -0.2408   0.09299   0.08986  -0.0336   0.9878   0.0286
  -7.000  -0.2130   0.08874   0.08558  -0.0399   0.9830   0.0296
  -6.750  -0.1862   0.08479   0.08161  -0.0466   0.9754   0.0309
  -6.500  -0.1497   0.08077   0.07754  -0.0572   0.9685   0.0324
  -6.250  -0.0901   0.07653   0.07316  -0.0784   0.9600   0.0330
  -6.000  -0.0755   0.07141   0.06808  -0.0766   0.9581   0.0335
  -5.750  -0.0545   0.06781   0.06447  -0.0784   0.9499   0.0342
  -5.500  -0.0209   0.06404   0.06065  -0.0843   0.9449   0.0357
  -5.250   0.0121   0.06062   0.05717  -0.0903   0.9351   0.0377
  -5.000   0.0869   0.03922   0.03573  -0.0982   0.8940   0.0405
  -4.750   0.1002   0.03613   0.03262  -0.0975   0.8846   0.0413
  -4.500   0.1177   0.03351   0.02995  -0.0984   0.8734   0.0424
  -4.250   0.1404   0.03086   0.02720  -0.1005   0.8642   0.0441
  -4.000   0.1925   0.02951   0.02541  -0.1089   0.8542   0.0486
  -3.750   0.2067   0.02546   0.02137  -0.1094   0.8452   0.0494
  -3.500   0.2238   0.02287   0.01876  -0.1093   0.8373   0.0505
  -3.250   0.2452   0.02092   0.01676  -0.1100   0.8282   0.0522
  -3.000   0.2726   0.01898   0.01467  -0.1116   0.8214   0.0553
  -2.750   0.3137   0.01755   0.01281  -0.1150   0.8129   0.0602
  -2.500   0.3330   0.01520   0.01049  -0.1154   0.8066   0.0618
  -2.250   0.3561   0.01386   0.00912  -0.1158   0.7986   0.0654
  -2.000   0.3928   0.01284   0.00765  -0.1174   0.7917   0.0733
  -1.750   0.4149   0.01124   0.00609  -0.1180   0.7844   0.0755
  -1.500   0.4412   0.01023   0.00498  -0.1184   0.7771   0.0806
  -1.250   0.4716   0.00926   0.00374  -0.1193   0.7701   0.0888
  -1.000   0.4975   0.00846   0.00288  -0.1196   0.7623   0.0954
  -0.750   0.5257   0.00766   0.00190  -0.1201   0.7550   0.1058
  -0.500   0.5533   0.00704   0.00112  -0.1204   0.7468   0.1198
  -0.250   0.5797   0.00649   0.00049  -0.1206   0.7389   0.1377
   0.000   0.1088   0.02567   0.02139  -0.0751   0.7800   0.0570
   0.500   0.6836   0.01856   0.01197  -0.1278   0.7274   0.2376
   0.750   0.7087   0.01705   0.01053  -0.1278   0.7164   0.2761
   1.000   0.7362   0.01618   0.00958  -0.1276   0.7054   0.3082
   1.250   0.7816   0.01548   0.00756  -0.1251   0.6968   0.0735
   1.500   0.8083   0.01492   0.00695  -0.1245   0.6840   0.0703
   1.750   0.8350   0.01457   0.00652  -0.1239   0.6709   0.0710
   2.000   0.8617   0.01423   0.00612  -0.1234   0.6581   0.0710
   2.250   0.8883   0.01391   0.00576  -0.1229   0.6458   0.0703
   2.500   0.9150   0.01371   0.00551  -0.1224   0.6334   0.0704
   2.750   0.9412   0.01357   0.00537  -0.1219   0.6196   0.0714
   3.000   0.9675   0.01346   0.00525  -0.1214   0.6052   0.0740
   3.250   0.9936   0.01343   0.00519  -0.1210   0.5904   0.0819
   3.500   1.0196   0.01342   0.00518  -0.1204   0.5749   0.1060
   3.750   1.0415   0.01213   0.00526  -0.1191   0.5594   1.0000
   4.000   1.0669   0.01232   0.00531  -0.1185   0.5430   1.0000
   4.250   1.0923   0.01252   0.00541  -0.1179   0.5274   1.0000
   4.500   1.1175   0.01276   0.00555  -0.1174   0.5125   1.0000
   4.750   1.1424   0.01301   0.00573  -0.1168   0.4975   1.0000
   5.000   1.1669   0.01331   0.00592  -0.1162   0.4823   1.0000
   5.250   1.1911   0.01364   0.00616  -0.1155   0.4673   1.0000
   5.500   1.2152   0.01400   0.00644  -0.1149   0.4533   1.0000
   5.750   1.2392   0.01437   0.00678  -0.1143   0.4401   1.0000
   6.000   1.2629   0.01477   0.00712  -0.1136   0.4272   1.0000
   6.250   1.2866   0.01519   0.00748  -0.1130   0.4156   1.0000
   6.500   1.3104   0.01557   0.00788  -0.1124   0.4048   1.0000
   6.750   1.3342   0.01593   0.00829  -0.1117   0.3942   1.0000
   7.000   1.3574   0.01634   0.00870  -0.1111   0.3838   1.0000
   7.250   1.3802   0.01672   0.00910  -0.1103   0.3724   1.0000
   7.500   1.4027   0.01706   0.00954  -0.1095   0.3602   1.0000
   7.750   1.4243   0.01743   0.00995  -0.1085   0.3462   1.0000
   8.000   1.4448   0.01781   0.01036  -0.1074   0.3297   1.0000
   8.250   1.4641   0.01825   0.01079  -0.1061   0.3113   1.0000
   8.500   1.4828   0.01873   0.01130  -0.1048   0.2909   1.0000
   8.750   1.4994   0.01935   0.01187  -0.1031   0.2675   1.0000
   9.000   1.5142   0.02009   0.01254  -0.1013   0.2422   1.0000
   9.250   1.5273   0.02096   0.01332  -0.0993   0.2202   1.0000
   9.500   1.5404   0.02182   0.01414  -0.0972   0.2004   1.0000
   9.750   1.5512   0.02272   0.01504  -0.0949   0.1837   1.0000
  10.000   1.5602   0.02368   0.01597  -0.0923   0.1694   1.0000
  10.250   1.5679   0.02477   0.01702  -0.0897   0.1553   1.0000
  10.500   1.5753   0.02592   0.01818  -0.0872   0.1442   1.0000
  10.750   1.5815   0.02722   0.01948  -0.0848   0.1351   1.0000
  11.000   1.5883   0.02854   0.02088  -0.0826   0.1264   1.0000
  11.250   1.5949   0.02995   0.02236  -0.0806   0.1165   1.0000
  11.500   1.6001   0.03154   0.02399  -0.0786   0.1043   1.0000
  11.750   1.6065   0.03312   0.02558  -0.0770   0.0803   1.0000
  12.000   1.5991   0.03596   0.02817  -0.0746   0.0600   1.0000
  12.250   1.5896   0.03919   0.03139  -0.0724   0.0509   1.0000
  12.500   1.5820   0.04242   0.03471  -0.0707   0.0439   1.0000
  12.750   1.5779   0.04545   0.03787  -0.0693   0.0389   1.0000
  13.000   1.5727   0.04871   0.04122  -0.0683   0.0356   1.0000
  13.250   1.5662   0.05223   0.04485  -0.0675   0.0335   1.0000
  13.500   1.5622   0.05559   0.04835  -0.0669   0.0318   1.0000
  13.750   1.5571   0.05913   0.05202  -0.0665   0.0304   1.0000
  14.000   1.5502   0.06302   0.05601  -0.0664   0.0292   1.0000
  14.250   1.5402   0.06747   0.06055  -0.0665   0.0283   1.0000
  14.500   1.5299   0.07204   0.06523  -0.0668   0.0276   1.0000
  14.750   1.5234   0.07623   0.06957  -0.0671   0.0269   1.0000
  15.000   1.5166   0.08055   0.07402  -0.0676   0.0261   1.0000
  15.250   1.5099   0.08492   0.07851  -0.0682   0.0255   1.0000
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