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GOE 300 (FRIEDRICHSHAFEN G20) AIRFOIL (goe300-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 300 (FRIEDRICHSHAFEN G20) AIRFOIL (goe300-il)
Reynolds number: 500,000
Max Cl/Cd: 107.59 at α=6°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe300-il-500000.txt
Download as CSV file: xf-goe300-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 300 (FRIEDRICHSHAFEN G20) AIRFOIL           
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.2853   0.11128   0.10901  -0.0235   1.0000   0.0223
  -9.500  -0.2827   0.10781   0.10556  -0.0271   1.0000   0.0232
  -9.250  -0.2824   0.10473   0.10251  -0.0304   1.0000   0.0233
  -9.000  -0.2713   0.10109   0.09889  -0.0294   1.0000   0.0236
  -8.750  -0.2626   0.09862   0.09645  -0.0295   1.0000   0.0239
  -8.500  -0.2562   0.09636   0.09422  -0.0299   1.0000   0.0243
  -8.250  -0.2557   0.09448   0.09239  -0.0293   0.9998   0.0247
  -8.000  -0.2365   0.09076   0.08866  -0.0340   0.9942   0.0256
  -7.750  -0.2177   0.08595   0.08385  -0.0436   0.9808   0.0274
  -7.500  -0.1970   0.08025   0.07813  -0.0552   0.9667   0.0276
  -7.250  -0.1835   0.07732   0.07519  -0.0535   0.9577   0.0279
  -7.000  -0.1698   0.07480   0.07265  -0.0545   0.9442   0.0283
  -6.750  -0.1562   0.07227   0.07009  -0.0561   0.9294   0.0288
  -6.500  -0.1414   0.06950   0.06726  -0.0585   0.9146   0.0297
  -6.250  -0.1069   0.06329   0.06087  -0.0732   0.8984   0.0322
  -6.000  -0.0961   0.06000   0.05755  -0.0725   0.8858   0.0326
  -5.750  -0.0807   0.05788   0.05537  -0.0722   0.8726   0.0330
  -5.500  -0.0610   0.05560   0.05302  -0.0735   0.8588   0.0337
  -5.250  -0.0379   0.05289   0.05022  -0.0761   0.8443   0.0350
  -5.000   0.0081   0.04646   0.04344  -0.0863   0.8304   0.0376
  -4.750   0.0234   0.04377   0.04070  -0.0863   0.8150   0.0382
  -4.500   0.0435   0.04253   0.03939  -0.0860   0.7985   0.0391
  -4.250   0.0822   0.03909   0.03563  -0.0902   0.7832   0.0435
  -4.000   0.1119   0.03492   0.03117  -0.0924   0.7683   0.0437
  -3.750   0.1350   0.03175   0.02782  -0.0932   0.7523   0.0433
  -3.500   0.1599   0.02935   0.02523  -0.0940   0.7360   0.0449
  -3.250   0.1904   0.02342   0.01875  -0.0955   0.7230   0.0447
  -3.000   0.2135   0.02643   0.02195  -0.0945   0.7055   0.0491
  -2.750   0.2458   0.01831   0.01286  -0.0957   0.6957   0.0514
  -2.500   0.2716   0.01934   0.01399  -0.0955   0.6810   0.0527
  -2.250   0.2968   0.02103   0.01583  -0.0953   0.6670   0.0564
  -2.000   0.3262   0.01784   0.01217  -0.0954   0.6567   0.0574
  -1.750   0.3543   0.01503   0.00876  -0.0952   0.6470   0.0607
  -1.500   0.3814   0.01533   0.00914  -0.0952   0.6359   0.0625
  -1.250   0.4087   0.01532   0.00910  -0.0951   0.6260   0.0648
  -1.000   0.4365   0.01422   0.00773  -0.0949   0.6170   0.0662
  -0.750   0.4646   0.01351   0.00682  -0.0947   0.6082   0.0683
  -0.250   0.5201   0.01242   0.00539  -0.0943   0.5903   0.0707
   0.000   0.5473   0.01185   0.00474  -0.0941   0.5811   0.0728
   0.250   0.5749   0.01161   0.00445  -0.0939   0.5715   0.0742
   0.500   0.6024   0.01140   0.00419  -0.0937   0.5634   0.0756
   0.750   0.6299   0.01121   0.00395  -0.0935   0.5546   0.0772
   1.000   0.6574   0.01109   0.00378  -0.0933   0.5454   0.0793
   1.250   0.6846   0.01100   0.00362  -0.0931   0.5357   0.0810
   1.500   0.7122   0.01090   0.00350  -0.0929   0.5269   0.0821
   1.750   0.7389   0.01063   0.00318  -0.0926   0.5185   0.0845
   2.000   0.7664   0.01051   0.00310  -0.0925   0.5093   0.0871
   2.250   0.7935   0.01053   0.00310  -0.0923   0.5001   0.0904
   2.500   0.8208   0.01053   0.00309  -0.0921   0.4898   0.0939
   2.750   0.8480   0.01051   0.00305  -0.0919   0.4788   0.0968
   3.000   0.8748   0.01049   0.00303  -0.0917   0.4664   0.1023
   3.250   0.9016   0.01056   0.00307  -0.0914   0.4522   0.1083
   3.500   0.9282   0.01061   0.00310  -0.0912   0.4374   0.1166
   4.000   0.9813   0.01081   0.00328  -0.0907   0.4099   0.1414
   4.250   1.0078   0.01090   0.00340  -0.0905   0.3978   0.1687
   4.500   1.0327   0.00964   0.00366  -0.0903   0.3878   1.0000
   4.750   1.0585   0.00988   0.00382  -0.0899   0.3781   1.0000
   5.000   1.0847   0.01009   0.00399  -0.0896   0.3695   1.0000
   5.250   1.1101   0.01037   0.00418  -0.0892   0.3607   1.0000
   5.500   1.1363   0.01057   0.00438  -0.0890   0.3530   1.0000
   5.750   1.1616   0.01085   0.00461  -0.0886   0.3462   1.0000
   6.000   1.1878   0.01104   0.00481  -0.0883   0.3399   1.0000
   6.250   1.2130   0.01131   0.00505  -0.0880   0.3325   1.0000
   6.500   1.2386   0.01154   0.00529  -0.0876   0.3259   1.0000
   6.750   1.2639   0.01178   0.00553  -0.0873   0.3187   1.0000
   7.000   1.2890   0.01204   0.00579  -0.0869   0.3112   1.0000
   7.250   1.3140   0.01230   0.00605  -0.0865   0.3023   1.0000
   7.500   1.3389   0.01255   0.00632  -0.0861   0.2929   1.0000
   7.750   1.3630   0.01286   0.00661  -0.0856   0.2810   1.0000
   8.000   1.3870   0.01317   0.00690  -0.0851   0.2657   1.0000
   8.250   1.4093   0.01361   0.00724  -0.0844   0.2393   1.0000
   8.500   1.4281   0.01434   0.00776  -0.0833   0.2033   1.0000
   8.750   1.4464   0.01509   0.00837  -0.0821   0.1853   1.0000
   9.000   1.4659   0.01571   0.00896  -0.0810   0.1757   1.0000
   9.250   1.4841   0.01639   0.00961  -0.0797   0.1683   1.0000
   9.500   1.5048   0.01685   0.01011  -0.0788   0.1632   1.0000
   9.750   1.5231   0.01746   0.01073  -0.0776   0.1574   1.0000
  10.000   1.5403   0.01809   0.01139  -0.0762   0.1518   1.0000
  10.250   1.5605   0.01850   0.01188  -0.0752   0.1475   1.0000
  10.500   1.5762   0.01909   0.01249  -0.0736   0.1426   1.0000
  10.750   1.5897   0.01977   0.01319  -0.0717   0.1376   1.0000
  11.000   1.6085   0.02016   0.01367  -0.0705   0.1322   1.0000
  11.250   1.6220   0.02087   0.01439  -0.0688   0.1263   1.0000
  11.500   1.6383   0.02144   0.01502  -0.0675   0.1203   1.0000
  11.750   1.6510   0.02224   0.01582  -0.0658   0.1122   1.0000
  12.000   1.6640   0.02306   0.01665  -0.0643   0.1019   1.0000
  12.250   1.6707   0.02435   0.01787  -0.0623   0.0875   1.0000
  12.500   1.6702   0.02626   0.01966  -0.0599   0.0676   1.0000
  12.750   1.6614   0.02896   0.02223  -0.0572   0.0473   1.0000
  13.000   1.6538   0.03179   0.02501  -0.0551   0.0358   1.0000
  13.250   1.6505   0.03445   0.02771  -0.0536   0.0311   1.0000
  13.500   1.6461   0.03736   0.03067  -0.0525   0.0284   1.0000
  13.750   1.6439   0.04020   0.03362  -0.0516   0.0266   1.0000
  14.000   1.6420   0.04311   0.03665  -0.0510   0.0253   1.0000
  14.250   1.6367   0.04650   0.04013  -0.0506   0.0242   1.0000
  14.500   1.6279   0.05043   0.04417  -0.0505   0.0233   1.0000
  14.750   1.6145   0.05506   0.04891  -0.0506   0.0225   1.0000
  15.000   1.6108   0.05861   0.05259  -0.0507   0.0219   1.0000
  15.250   1.6047   0.06253   0.05664  -0.0511   0.0213   1.0000
  15.500   1.5968   0.06677   0.06100  -0.0516   0.0208   1.0000
  15.750   1.5877   0.07128   0.06562  -0.0522   0.0202   1.0000
  16.000   1.5775   0.07604   0.07049  -0.0531   0.0198   1.0000
  16.250   1.5652   0.08117   0.07573  -0.0541   0.0194   1.0000
  16.500   1.5511   0.08670   0.08136  -0.0554   0.0190   1.0000
  16.750   1.5354   0.09256   0.08733  -0.0569   0.0187   1.0000
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