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GOE 134 (MVA H.12) AIRFOIL (goe134-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 134 (MVA H.12) AIRFOIL (goe134-il)
Reynolds number: 1,000,000
Max Cl/Cd: 114.72 at α=6.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe134-il-1000000.txt
Download as CSV file: xf-goe134-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 134 (MVA H.12) 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  -0.3930   0.08688   0.08534  -0.0271   1.0000   0.0139
  -7.750  -0.4017   0.08365   0.08214  -0.0279   1.0000   0.0139
  -7.500  -0.4074   0.08036   0.07887  -0.0288   1.0000   0.0139
  -7.000  -0.3718   0.06770   0.06614  -0.0436   0.9956   0.0142
  -6.750  -0.3489   0.06432   0.06272  -0.0477   0.9941   0.0144
  -6.500  -0.3252   0.06061   0.05897  -0.0523   0.9911   0.0148
  -6.250  -0.2980   0.05643   0.05472  -0.0577   0.9884   0.0153
  -6.000  -0.2586   0.04882   0.04686  -0.0661   0.9854   0.0173
  -5.750  -0.2295   0.04275   0.04055  -0.0700   0.9811   0.0174
  -5.500  -0.2107   0.03641   0.03398  -0.0725   0.9744   0.0178
  -5.250  -0.1871   0.03473   0.03225  -0.0734   0.9680   0.0181
  -5.000  -0.1648   0.03303   0.03045  -0.0736   0.9586   0.0185
  -4.750  -0.1419   0.03109   0.02839  -0.0736   0.9477   0.0192
  -4.500  -0.1112   0.02808   0.02489  -0.0725   0.9361   0.0216
  -4.250  -0.0902   0.02267   0.01900  -0.0724   0.9230   0.0220
  -4.000  -0.0665   0.02127   0.01752  -0.0722   0.9056   0.0224
  -3.750  -0.0419   0.02026   0.01638  -0.0720   0.8838   0.0228
  -3.500  -0.0167   0.01933   0.01526  -0.0717   0.8534   0.0236
  -3.250   0.0116   0.01965   0.01520  -0.0706   0.8111   0.0265
  -3.000   0.0386   0.01890   0.01403  -0.0702   0.7727   0.0267
  -2.500   0.0925   0.01464   0.00926  -0.0706   0.7299   0.0282
  -2.250   0.1205   0.01399   0.00850  -0.0708   0.7143   0.0290
  -2.000   0.1488   0.01356   0.00792  -0.0709   0.7005   0.0308
  -1.750   0.1779   0.01427   0.00848  -0.0707   0.6869   0.0330
  -1.500   0.2062   0.01219   0.00621  -0.0710   0.6745   0.0349
  -1.250   0.2346   0.01164   0.00564  -0.0712   0.6617   0.0361
  -1.000   0.2631   0.01127   0.00521  -0.0713   0.6487   0.0378
  -0.750   0.2918   0.01111   0.00498  -0.0714   0.6351   0.0400
   0.000  -1.2020   0.02142   0.01879   0.2505   0.6726   0.0347
   0.250   0.4063   0.00955   0.00308  -0.0714   0.5766   0.0329
   0.500   0.4347   0.00928   0.00275  -0.0715   0.5606   0.0328
   0.750   0.4632   0.00912   0.00253  -0.0717   0.5451   0.0328
   1.000   0.4917   0.00899   0.00235  -0.0719   0.5306   0.0328
   1.250   0.5202   0.00899   0.00230  -0.0720   0.5164   0.0332
   1.500   0.5488   0.00889   0.00213  -0.0722   0.5025   0.0334
   1.750   0.5773   0.00882   0.00200  -0.0724   0.4884   0.0338
   2.000   0.6058   0.00881   0.00192  -0.0726   0.4738   0.0351
   2.250   0.6342   0.00884   0.00190  -0.0727   0.4590   0.0367
   2.500   0.6626   0.00890   0.00190  -0.0729   0.4445   0.0383
   2.750   0.6908   0.00898   0.00193  -0.0730   0.4304   0.0401
   3.000   0.7190   0.00907   0.00198  -0.0732   0.4164   0.0478
   3.250   0.7401   0.00708   0.00217  -0.0723   0.4042   1.0000
   3.500   0.7682   0.00724   0.00225  -0.0725   0.3903   1.0000
   3.750   0.7961   0.00743   0.00235  -0.0726   0.3742   1.0000
   4.000   0.8240   0.00762   0.00246  -0.0727   0.3595   1.0000
   4.250   0.8520   0.00778   0.00257  -0.0729   0.3484   1.0000
   4.500   0.8798   0.00796   0.00270  -0.0730   0.3363   1.0000
   4.750   0.9074   0.00815   0.00284  -0.0731   0.3233   1.0000
   5.000   0.9350   0.00836   0.00298  -0.0732   0.3101   1.0000
   5.250   0.9625   0.00855   0.00313  -0.0733   0.2995   1.0000
   5.500   0.9903   0.00871   0.00328  -0.0734   0.2909   1.0000
   5.750   1.0176   0.00892   0.00345  -0.0735   0.2788   1.0000
   6.000   1.0447   0.00915   0.00362  -0.0735   0.2665   1.0000
   6.250   1.0719   0.00937   0.00381  -0.0736   0.2560   1.0000
   6.500   1.0990   0.00958   0.00400  -0.0736   0.2451   1.0000
   6.750   1.1258   0.00983   0.00421  -0.0736   0.2317   1.0000
   7.000   1.1524   0.01009   0.00443  -0.0736   0.2194   1.0000
   7.250   1.1785   0.01040   0.00468  -0.0736   0.2030   1.0000
   7.500   1.2038   0.01081   0.00499  -0.0734   0.1802   1.0000
   7.750   1.2268   0.01149   0.00544  -0.0729   0.1413   1.0000
   8.000   1.2494   0.01219   0.00597  -0.0724   0.1108   1.0000
   8.250   1.2723   0.01284   0.00649  -0.0719   0.0875   1.0000
   8.500   1.2941   0.01358   0.00706  -0.0712   0.0620   1.0000
   8.750   1.3125   0.01469   0.00790  -0.0700   0.0271   1.0000
   9.000   1.3332   0.01548   0.00865  -0.0691   0.0167   1.0000
   9.250   1.3550   0.01611   0.00932  -0.0683   0.0145   1.0000
   9.500   1.3771   0.01667   0.00994  -0.0675   0.0135   1.0000
   9.750   1.3990   0.01721   0.01054  -0.0668   0.0127   1.0000
  10.000   1.4197   0.01783   0.01122  -0.0659   0.0119   1.0000
  10.250   1.4381   0.01863   0.01209  -0.0646   0.0110   1.0000
  10.500   1.4537   0.01962   0.01319  -0.0629   0.0103   1.0000
  10.750   1.4728   0.02023   0.01386  -0.0618   0.0101   1.0000
  11.000   1.4902   0.02093   0.01462  -0.0604   0.0097   1.0000
  11.250   1.5055   0.02170   0.01547  -0.0587   0.0093   1.0000
  11.500   1.5189   0.02252   0.01636  -0.0567   0.0089   1.0000
  11.750   1.5293   0.02341   0.01732  -0.0543   0.0086   1.0000
  12.000   1.5347   0.02443   0.01842  -0.0510   0.0084   1.0000
  12.250   1.5373   0.02574   0.01982  -0.0478   0.0082   1.0000
  12.500   1.5336   0.02762   0.02181  -0.0442   0.0079   1.0000
  12.750   1.5207   0.03042   0.02478  -0.0403   0.0077   1.0000
  13.000   1.5297   0.03175   0.02618  -0.0390   0.0076   1.0000
  13.250   1.5364   0.03334   0.02787  -0.0378   0.0074   1.0000
  13.500   1.5407   0.03530   0.02992  -0.0368   0.0072   1.0000
  13.750   1.5421   0.03773   0.03246  -0.0360   0.0071   1.0000
  14.000   1.5418   0.04053   0.03537  -0.0356   0.0070   1.0000
  14.250   1.5403   0.04368   0.03863  -0.0356   0.0068   1.0000
  14.500   1.5379   0.04708   0.04214  -0.0358   0.0067   1.0000
  14.750   1.5334   0.05081   0.04599  -0.0362   0.0066   1.0000
  15.000   1.5275   0.05484   0.05013  -0.0369   0.0065   1.0000
  15.250   1.5207   0.05909   0.05449  -0.0378   0.0064   1.0000
  15.500   1.5123   0.06362   0.05914  -0.0388   0.0063   1.0000
  15.750   1.5033   0.06838   0.06401  -0.0400   0.0063   1.0000
  16.000   1.4934   0.07337   0.06910  -0.0414   0.0062   1.0000
  16.250   1.4825   0.07857   0.07441  -0.0429   0.0062   1.0000
  16.500   1.4717   0.08390   0.07984  -0.0446   0.0061   1.0000
  16.750   1.4608   0.08934   0.08538  -0.0464   0.0060   1.0000
  17.000   1.4496   0.09488   0.09102  -0.0483   0.0060   1.0000
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