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GOE 187 (SCHTTE-LANZ 2U10) AIRFOIL (goe187-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 187 (SCHTTE-LANZ 2U10) AIRFOIL (goe187-il)
Reynolds number: 1,000,000
Max Cl/Cd: 118.89 at α=5.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe187-il-1000000.txt
Download as CSV file: xf-goe187-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 187 (SCHTTE-LANZ 2U10) 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.3589   0.09401   0.09251  -0.0137   1.0000   0.0062
  -7.750  -0.3545   0.09075   0.08927  -0.0158   1.0000   0.0063
  -7.500  -0.3511   0.08749   0.08604  -0.0182   1.0000   0.0063
  -7.250  -0.2538   0.06615   0.06480  -0.0285   0.9773   0.0066
  -7.000  -0.2462   0.06215   0.06075  -0.0314   0.9340   0.0067
  -6.750  -0.2424   0.05875   0.05722  -0.0333   0.8949   0.0068
  -6.500  -0.2349   0.05499   0.05334  -0.0362   0.8648   0.0069
  -6.250  -0.2244   0.05109   0.04934  -0.0396   0.8398   0.0070
  -6.000  -0.2114   0.04707   0.04520  -0.0431   0.8169   0.0072
  -5.750  -0.1960   0.04301   0.04104  -0.0465   0.7967   0.0075
  -5.500  -0.1784   0.03900   0.03691  -0.0498   0.7785   0.0078
  -5.250  -0.1588   0.03496   0.03274  -0.0529   0.7629   0.0082
  -0.750   0.3178   0.00981   0.00370  -0.0637   0.6117   0.0139
  -0.500   0.3458   0.00948   0.00332  -0.0637   0.5990   0.0152
  -0.250   0.3737   0.00912   0.00288  -0.0636   0.5829   0.0161
   0.000   0.4017   0.00899   0.00266  -0.0636   0.5625   0.0179
   0.250   0.4295   0.00883   0.00238  -0.0635   0.5389   0.0188
   0.500   0.4570   0.00837   0.00179  -0.0634   0.5136   0.0215
   0.750   0.4847   0.00840   0.00169  -0.0634   0.4827   0.0246
   1.000   0.5121   0.00853   0.00167  -0.0634   0.4514   0.0272
   1.250   0.5398   0.00848   0.00147  -0.0634   0.4298   0.0337
   1.500   0.5677   0.00854   0.00144  -0.0634   0.4137   0.0406
   1.750   0.5959   0.00646   0.00158  -0.0643   0.4003   1.0000
   2.000   0.6235   0.00660   0.00162  -0.0643   0.3889   1.0000
   2.250   0.6513   0.00672   0.00166  -0.0643   0.3796   1.0000
   2.500   0.6790   0.00684   0.00172  -0.0643   0.3711   1.0000
   3.000   0.7344   0.00709   0.00186  -0.0644   0.3553   1.0000
   3.250   0.7620   0.00722   0.00195  -0.0644   0.3482   1.0000
   3.500   0.7897   0.00733   0.00203  -0.0645   0.3419   1.0000
   3.750   0.8172   0.00747   0.00214  -0.0645   0.3346   1.0000
   4.000   0.8449   0.00759   0.00224  -0.0645   0.3279   1.0000
   4.250   0.8723   0.00774   0.00235  -0.0646   0.3201   1.0000
   4.500   0.8998   0.00786   0.00246  -0.0646   0.3130   1.0000
   4.750   0.9271   0.00803   0.00260  -0.0646   0.3040   1.0000
   5.000   0.9545   0.00816   0.00273  -0.0647   0.2956   1.0000
   5.250   0.9817   0.00832   0.00287  -0.0647   0.2871   1.0000
   5.500   1.0087   0.00851   0.00302  -0.0647   0.2763   1.0000
   5.750   1.0355   0.00871   0.00320  -0.0647   0.2623   1.0000
   6.000   1.0608   0.00912   0.00344  -0.0645   0.2249   1.0000
   6.250   1.0826   0.01004   0.00399  -0.0639   0.1609   1.0000
   6.500   1.1070   0.01056   0.00439  -0.0636   0.1331   1.0000
   6.750   1.1302   0.01123   0.00485  -0.0632   0.0990   1.0000
   7.000   1.1554   0.01161   0.00520  -0.0629   0.0901   1.0000
   7.250   1.1803   0.01199   0.00556  -0.0627   0.0842   1.0000
   7.500   1.2054   0.01235   0.00592  -0.0625   0.0783   1.0000
   7.750   1.2311   0.01259   0.00621  -0.0623   0.0738   1.0000
   8.000   1.2552   0.01303   0.00659  -0.0620   0.0590   1.0000
   8.250   1.2711   0.01451   0.00776  -0.0605   0.0125   1.0000
   8.500   1.2935   0.01513   0.00844  -0.0598   0.0102   1.0000
   8.750   1.3142   0.01593   0.00936  -0.0588   0.0084   1.0000
   9.000   1.3365   0.01646   0.00998  -0.0582   0.0079   1.0000
   9.250   1.3576   0.01711   0.01070  -0.0574   0.0072   1.0000
   9.500   1.3777   0.01783   0.01149  -0.0564   0.0066   1.0000
   9.750   1.3960   0.01868   0.01243  -0.0552   0.0061   1.0000
  10.000   1.4045   0.02042   0.01436  -0.0527   0.0054   1.0000
  10.250   1.4225   0.02113   0.01514  -0.0515   0.0052   1.0000
  10.500   1.4384   0.02197   0.01606  -0.0500   0.0049   1.0000
  10.750   1.4507   0.02300   0.01721  -0.0481   0.0046   1.0000
  11.000   1.4592   0.02411   0.01842  -0.0456   0.0044   1.0000
  11.250   1.4631   0.02532   0.01972  -0.0425   0.0043   1.0000
  11.500   1.4666   0.02669   0.02119  -0.0398   0.0041   1.0000
  11.750   1.4693   0.02828   0.02289  -0.0376   0.0040   1.0000
  12.000   1.4716   0.03010   0.02481  -0.0358   0.0039   1.0000
  12.250   1.4730   0.03221   0.02701  -0.0345   0.0037   1.0000
  12.500   1.4720   0.03476   0.02967  -0.0336   0.0036   1.0000
  12.750   1.4678   0.03788   0.03290  -0.0330   0.0035   1.0000
  13.000   1.4603   0.04160   0.03675  -0.0328   0.0035   1.0000
  13.250   1.4484   0.04596   0.04125  -0.0328   0.0034   1.0000
  13.500   1.4338   0.05072   0.04615  -0.0328   0.0033   1.0000
  13.750   1.4155   0.05589   0.05146  -0.0325   0.0032   1.0000
  14.000   1.4093   0.05990   0.05560  -0.0330   0.0032   1.0000
  14.250   1.4054   0.06377   0.05960  -0.0340   0.0032   1.0000
  14.500   1.3993   0.06800   0.06396  -0.0350   0.0031   1.0000
  14.750   1.3931   0.07244   0.06852  -0.0363   0.0031   1.0000
  15.000   1.3852   0.07721   0.07342  -0.0377   0.0030   1.0000
  15.250   1.3765   0.08224   0.07858  -0.0392   0.0030   1.0000
  15.500   1.3673   0.08748   0.08394  -0.0410   0.0030   1.0000
  15.750   1.3575   0.09291   0.08950  -0.0430   0.0029   1.0000
  16.000   1.3474   0.09854   0.09525  -0.0451   0.0029   1.0000
  16.250   1.3370   0.10436   0.10119  -0.0475   0.0028   1.0000
  16.500   1.3263   0.11030   0.10725  -0.0500   0.0028   1.0000
  16.750   1.3144   0.11654   0.11362  -0.0527   0.0028   1.0000
  17.000   1.3031   0.12287   0.12007  -0.0556   0.0028   1.0000
  17.250   1.2911   0.12947   0.12679  -0.0588   0.0028   1.0000
  17.500   1.2801   0.13604   0.13348  -0.0621   0.0027   1.0000
  17.750   1.2683   0.14294   0.14050  -0.0657   0.0027   1.0000
  18.000   1.2565   0.15008   0.14776  -0.0695   0.0027   1.0000
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