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=50,000 Ncrit=9


Details Polar file
Airfoil: GOE 346 (FRIEDRICHSHAFEN-STAAKEN) AIRFOIL (goe346-il)
Reynolds number: 50,000
Max Cl/Cd: 40.26 at α=5.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe346-il-50000.txt
Download as CSV file: xf-goe346-il-50000.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 =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.4453   0.12268   0.11539  -0.0077   1.0000   0.0975
  -9.250  -0.4485   0.12203   0.11483  -0.0109   1.0000   0.0992
  -9.000  -0.4547   0.12184   0.11475  -0.0145   1.0000   0.0998
  -8.750  -0.4295   0.11265   0.10548  -0.0108   1.0000   0.1047
  -8.500  -0.4241   0.10961   0.10248  -0.0117   1.0000   0.1088
  -8.250  -0.4247   0.10780   0.10075  -0.0139   1.0000   0.1123
  -8.000  -0.4289   0.10728   0.10034  -0.0191   1.0000   0.1139
  -7.750  -0.4162   0.10121   0.09430  -0.0161   1.0000   0.1174
  -7.500  -0.4084   0.09783   0.09095  -0.0165   1.0000   0.1231
  -7.250  -0.4063   0.09659   0.08977  -0.0229   1.0000   0.1278
  -7.000  -0.3972   0.09169   0.08493  -0.0206   1.0000   0.1327
  -6.750  -0.3903   0.08919   0.08247  -0.0234   1.0000   0.1407
  -6.250  -0.3746   0.08288   0.07623  -0.0259   1.0000   0.1547
  -6.000  -0.3670   0.07941   0.07279  -0.0266   1.0000   0.1607
  -5.750  -0.3557   0.07774   0.07107  -0.0318   1.0000   0.1718
  -5.500  -0.3498   0.07341   0.06685  -0.0274   1.0000   0.1807
  -5.250  -0.3408   0.07036   0.06383  -0.0279   1.0000   0.1922
  -5.000  -0.3316   0.06746   0.06095  -0.0282   1.0000   0.2071
  -4.750  -0.3194   0.06531   0.05873  -0.0308   1.0000   0.2316
  -4.500  -0.3150   0.06184   0.05539  -0.0269   1.0000   0.2516
  -4.250  -0.3083   0.05911   0.05269  -0.0251   1.0000   0.2823
  -4.000  -0.0076   0.03730   0.03030  -0.0211   1.0000   1.0000
  -3.750   0.0046   0.03552   0.02858  -0.0222   1.0000   1.0000
  -3.500   0.0165   0.03383   0.02696  -0.0232   1.0000   1.0000
  -3.250  -0.3065   0.04919   0.04323  -0.0053   1.0000   0.4860
  -3.000  -0.3106   0.04661   0.04083   0.0032   1.0000   0.5346
  -2.750  -0.3124   0.04431   0.03865   0.0109   1.0000   0.5828
  -2.500  -0.3114   0.04203   0.03645   0.0172   1.0000   0.6273
  -2.250  -0.3055   0.03985   0.03433   0.0211   1.0000   0.6682
  -2.000  -0.3002   0.03745   0.03203   0.0263   1.0000   0.7021
  -1.750  -0.2821   0.03507   0.02967   0.0263   1.0000   0.7249
  -1.500  -0.2232   0.03227   0.02668   0.0125   1.0000   0.7124
  -1.250  -0.0072   0.03111   0.02299  -0.0461   1.0000   0.3807
  -1.000   0.0363   0.03064   0.02182  -0.0495   1.0000   0.3040
  -0.750   0.0720   0.03018   0.02078  -0.0508   1.0000   0.2604
  -0.500   0.1035   0.02953   0.01971  -0.0513   1.0000   0.2302
  -0.250   0.1320   0.02867   0.01863  -0.0514   1.0000   0.2097
   0.000   0.1597   0.02819   0.01786  -0.0514   1.0000   0.1937
   0.250   0.1859   0.02789   0.01729  -0.0512   1.0000   0.1823
   0.500   0.2111   0.02761   0.01680  -0.0510   1.0000   0.1737
   0.750   0.2349   0.02747   0.01649  -0.0506   1.0000   0.1690
   1.000   0.2591   0.02737   0.01625  -0.0504   1.0000   0.1690
   1.250   0.2825   0.02742   0.01619  -0.0502   1.0000   0.1705
   1.500   0.3058   0.02752   0.01624  -0.0502   1.0000   0.1708
   1.750   0.3287   0.02773   0.01644  -0.0502   1.0000   0.1711
   2.000   0.3518   0.02802   0.01677  -0.0506   1.0000   0.1729
   2.250   0.3813   0.02843   0.01724  -0.0524   0.9971   0.1778
   2.500   0.4506   0.02872   0.01769  -0.0612   0.9766   0.2036
   2.750   0.5104   0.02737   0.01813  -0.0674   0.9549   1.0000
   3.000   0.5715   0.02793   0.01831  -0.0731   0.9285   1.0000
   3.250   0.6286   0.02812   0.01839  -0.0778   0.8999   1.0000
   3.500   0.6838   0.02796   0.01827  -0.0816   0.8708   1.0000
   3.750   0.7357   0.02745   0.01789  -0.0839   0.8417   1.0000
   4.000   0.7807   0.02671   0.01734  -0.0844   0.8117   1.0000
   4.250   0.8219   0.02571   0.01649  -0.0835   0.7802   1.0000
   4.500   0.8545   0.02486   0.01577  -0.0810   0.7429   1.0000
   4.750   0.8863   0.02396   0.01496  -0.0781   0.7017   1.0000
   5.000   0.9124   0.02358   0.01455  -0.0748   0.6528   1.0000
   5.250   0.9377   0.02353   0.01436  -0.0719   0.6035   1.0000
   5.500   0.9621   0.02390   0.01453  -0.0694   0.5574   1.0000
   5.750   0.9846   0.02451   0.01499  -0.0671   0.5132   1.0000
   6.000   1.0046   0.02510   0.01538  -0.0646   0.4685   1.0000
   6.250   1.0234   0.02575   0.01589  -0.0624   0.4260   1.0000
   6.500   1.0416   0.02645   0.01648  -0.0602   0.3848   1.0000
   6.750   1.0568   0.02720   0.01708  -0.0577   0.3380   1.0000
   7.000   1.0705   0.02855   0.01825  -0.0551   0.2822   1.0000
   7.250   1.0799   0.03110   0.02019  -0.0518   0.2044   1.0000
   7.500   1.0978   0.03350   0.02236  -0.0499   0.1648   1.0000
   7.750   1.1222   0.03596   0.02468  -0.0489   0.1461   1.0000
   8.000   1.1447   0.03831   0.02719  -0.0478   0.1327   1.0000
   8.250   1.1658   0.04105   0.03028  -0.0466   0.1231   1.0000
   8.500   1.1890   0.04419   0.03343  -0.0458   0.1173   1.0000
   8.750   1.2024   0.04779   0.03777  -0.0439   0.1129   1.0000
   9.000   1.2174   0.05088   0.04115  -0.0424   0.1077   1.0000
   9.250   1.2334   0.05484   0.04524  -0.0414   0.1049   1.0000
   9.500   1.2392   0.05963   0.05051  -0.0395   0.1045   1.0000
   9.750   1.2396   0.06455   0.05593  -0.0375   0.1044   1.0000
  10.000   1.2352   0.06956   0.06143  -0.0356   0.1044   1.0000
  10.250   1.2271   0.07467   0.06690  -0.0338   0.1045   1.0000
  10.500   1.1529   0.08224   0.07521  -0.0316   0.1111   1.0000
  10.750   1.1205   0.08857   0.08168  -0.0324   0.1131   1.0000
  11.000   1.0939   0.09576   0.08894  -0.0351   0.1150   1.0000
  11.250   1.0796   0.10277   0.09597  -0.0377   0.1167   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)