Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

GOE 346 (FRIEDRICHSHAFEN-STAAKEN) AIRFOIL (goe346-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 346 (FRIEDRICHSHAFEN-STAAKEN) AIRFOIL (goe346-il)
Reynolds number: 1,000,000
Max Cl/Cd: 100.79 at α=4°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe346-il-1000000.txt
Download as CSV file: xf-goe346-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 346 (FRIEDRICHSHAFEN-STAAKEN) 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
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.4206   0.09493   0.09330  -0.0113   1.0000   0.0132
  -8.000  -0.4145   0.09186   0.09025  -0.0130   1.0000   0.0141
  -7.750  -0.4097   0.08826   0.08668  -0.0171   1.0000   0.0147
  -7.500  -0.3994   0.08408   0.08250  -0.0228   1.0000   0.0148
  -7.250  -0.3891   0.07999   0.07841  -0.0275   1.0000   0.0148
  -7.000  -0.3815   0.07645   0.07487  -0.0301   1.0000   0.0148
  -6.750  -0.3730   0.07171   0.07014  -0.0322   0.9988   0.0150
  -6.500  -0.3504   0.06833   0.06674  -0.0358   0.9966   0.0153
  -6.250  -0.3226   0.06484   0.06322  -0.0410   0.9945   0.0156
  -6.000  -0.2932   0.06132   0.05965  -0.0465   0.9910   0.0165
  -5.750  -0.2438   0.05559   0.05375  -0.0576   0.9864   0.0184
  -5.500  -0.2089   0.05091   0.04895  -0.0633   0.9815   0.0185
  -5.250  -0.1777   0.04659   0.04451  -0.0673   0.9738   0.0186
  -4.500  -0.1102   0.03821   0.03593  -0.0719   0.9464   0.0203
  -4.250  -0.0829   0.03580   0.03339  -0.0730   0.9381   0.0218
  -4.000  -0.0472   0.03332   0.03065  -0.0739   0.9300   0.0229
  -3.750  -0.0196   0.03072   0.02786  -0.0744   0.9223   0.0230
  -3.500   0.0053   0.02565   0.02249  -0.0755   0.9147   0.0235
  -3.250   0.0299   0.02413   0.02089  -0.0758   0.9074   0.0239
  -3.000   0.0553   0.02284   0.01950  -0.0760   0.9000   0.0243
  -2.750   0.0818   0.02156   0.01811  -0.0762   0.8928   0.0248
  -2.500   0.1088   0.02026   0.01668  -0.0762   0.8850   0.0257
  -2.250   0.1390   0.01974   0.01597  -0.0755   0.8761   0.0285
  -2.000   0.1671   0.01873   0.01475  -0.0751   0.8660   0.0288
  -1.750   0.1948   0.01740   0.01320  -0.0749   0.8544   0.0289
  -1.500   0.2223   0.01620   0.01179  -0.0747   0.8404   0.0289
  -1.250   0.1182   0.04121   0.03920  -0.0320   0.8514   0.0268
   1.000   0.4983   0.00844   0.00279  -0.0737   0.6910   0.0345
   1.250   0.5259   0.00814   0.00244  -0.0736   0.6741   0.0343
   1.500   0.5532   0.00795   0.00216  -0.0734   0.6470   0.0344
   1.750   0.5797   0.00787   0.00191  -0.0731   0.6008   0.0340
   2.000   0.6059   0.00797   0.00178  -0.0728   0.5438   0.0346
   2.250   0.6323   0.00814   0.00175  -0.0726   0.4948   0.0357
   2.500   0.6590   0.00831   0.00177  -0.0725   0.4543   0.0365
   2.750   0.6855   0.00848   0.00173  -0.0723   0.4032   0.0374
   3.000   0.7115   0.00875   0.00176  -0.0721   0.3486   0.0390
   3.250   0.7378   0.00901   0.00187  -0.0719   0.3079   0.0420
   3.750   0.7906   0.00950   0.00210  -0.0716   0.2404   0.0569
   4.000   0.8124   0.00806   0.00242  -0.0710   0.2088   1.0000
   4.250   0.8388   0.00836   0.00259  -0.0708   0.1859   1.0000
   4.500   0.8652   0.00864   0.00278  -0.0706   0.1651   1.0000
   4.750   0.8911   0.00899   0.00299  -0.0704   0.1385   1.0000
   5.000   0.9141   0.00984   0.00343  -0.0698   0.0679   1.0000
   5.250   0.9384   0.01046   0.00386  -0.0694   0.0371   1.0000
   5.500   0.9647   0.01074   0.00416  -0.0691   0.0340   1.0000
   5.750   0.9907   0.01103   0.00448  -0.0688   0.0324   1.0000
   6.000   1.0164   0.01139   0.00485  -0.0685   0.0304   1.0000
   6.250   1.0414   0.01185   0.00535  -0.0681   0.0277   1.0000
   6.500   1.0661   0.01235   0.00591  -0.0676   0.0260   1.0000
   6.750   1.0918   0.01265   0.00623  -0.0673   0.0252   1.0000
   7.000   1.1170   0.01299   0.00661  -0.0669   0.0238   1.0000
   7.250   1.1420   0.01337   0.00699  -0.0666   0.0223   1.0000
   7.500   1.1655   0.01397   0.00763  -0.0660   0.0205   1.0000
   7.750   1.1879   0.01470   0.00844  -0.0652   0.0193   1.0000
   8.000   1.2130   0.01500   0.00876  -0.0648   0.0185   1.0000
   8.250   1.2375   0.01536   0.00915  -0.0644   0.0174   1.0000
   8.500   1.2621   0.01567   0.00947  -0.0641   0.0163   1.0000
   8.750   1.2840   0.01636   0.01018  -0.0633   0.0151   1.0000
   9.000   1.3050   0.01715   0.01105  -0.0623   0.0144   1.0000
   9.250   1.3283   0.01759   0.01154  -0.0618   0.0138   1.0000
   9.500   1.3509   0.01808   0.01209  -0.0611   0.0131   1.0000
   9.750   1.3734   0.01857   0.01261  -0.0604   0.0125   1.0000
  10.000   1.3952   0.01910   0.01317  -0.0597   0.0119   1.0000
  10.250   1.4102   0.02042   0.01457  -0.0580   0.0111   1.0000
  10.500   1.4289   0.02123   0.01548  -0.0568   0.0107   1.0000
  10.750   1.4492   0.02182   0.01615  -0.0559   0.0103   1.0000
  11.000   1.4675   0.02260   0.01701  -0.0547   0.0099   1.0000
  11.250   1.4851   0.02338   0.01787  -0.0534   0.0096   1.0000
  11.500   1.5021   0.02414   0.01871  -0.0521   0.0092   1.0000
  11.750   1.5183   0.02493   0.01955  -0.0507   0.0089   1.0000
  12.000   1.5316   0.02590   0.02060  -0.0489   0.0086   1.0000
  12.250   1.5353   0.02737   0.02219  -0.0457   0.0083   1.0000
  12.500   1.5232   0.03008   0.02512  -0.0407   0.0080   1.0000
  12.750   1.5274   0.03156   0.02673  -0.0383   0.0079   1.0000
  13.000   1.5327   0.03301   0.02829  -0.0362   0.0078   1.0000
  13.250   1.5363   0.03469   0.03011  -0.0343   0.0077   1.0000
  13.500   1.5376   0.03669   0.03225  -0.0325   0.0076   1.0000
  13.750   1.5375   0.03895   0.03464  -0.0310   0.0074   1.0000
  14.000   1.5362   0.04148   0.03732  -0.0298   0.0073   1.0000
  14.250   1.5338   0.04427   0.04025  -0.0290   0.0072   1.0000
  14.500   1.5309   0.04732   0.04345  -0.0287   0.0070   1.0000
  14.750   1.5254   0.05089   0.04716  -0.0288   0.0069   1.0000
  15.000   1.5192   0.05478   0.05119  -0.0295   0.0068   1.0000
  15.250   1.5107   0.05925   0.05580  -0.0306   0.0068   1.0000
  15.500   1.5009   0.06417   0.06086  -0.0323   0.0067   1.0000
  15.750   1.4883   0.06985   0.06669  -0.0346   0.0066   1.0000
  16.000   1.4755   0.07590   0.07287  -0.0374   0.0066   1.0000
  16.250   1.4552   0.08352   0.08066  -0.0411   0.0066   1.0000
  16.500   1.4328   0.09193   0.08923  -0.0453   0.0066   1.0000
  16.750   1.4095   0.10077   0.09822  -0.0499   0.0066   1.0000
  17.000   1.3797   0.11122   0.10885  -0.0553   0.0066   1.0000
  17.250   1.3503   0.12186   0.11965  -0.0609   0.0067   1.0000
  17.500   1.3165   0.13388   0.13184  -0.0674   0.0068   1.0000
  17.750   1.2797   0.14739   0.14551  -0.0750   0.0069   1.0000
<< Back to GOE 346 (FRIEDRICHSHAFEN-STAAKEN) AIRFOIL (goe346-il)

Polar data table (+)

Polar graphs


<< Back to GOE 346 (FRIEDRICHSHAFEN-STAAKEN) AIRFOIL (goe346-il)