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GOE 100 (SOPWITH) AIRFOIL (goe100-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 100 (SOPWITH) AIRFOIL (goe100-il)
Reynolds number: 200,000
Max Cl/Cd: 71.32 at α=2.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe100-il-200000.txt
Download as CSV file: xf-goe100-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 100 (SOPWITH) AIRFOIL                       
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.250  -0.3995   0.08759   0.08439  -0.0210   1.0000   0.0340
  -7.000  -0.3976   0.08471   0.08155  -0.0217   1.0000   0.0348
  -6.750  -0.3957   0.08181   0.07870  -0.0225   1.0000   0.0358
  -6.500  -0.3937   0.07892   0.07584  -0.0233   1.0000   0.0368
  -6.250  -0.3915   0.07606   0.07300  -0.0241   1.0000   0.0380
  -6.000  -0.3884   0.07319   0.07014  -0.0250   1.0000   0.0394
  -5.750  -0.3773   0.07044   0.06733  -0.0286   1.0000   0.0416
  -5.500  -0.3605   0.06781   0.06455  -0.0321   1.0000   0.0425
  -5.250  -0.3478   0.06466   0.06129  -0.0329   1.0000   0.0426
  -5.000  -0.3405   0.05891   0.05548  -0.0339   1.0000   0.0432
  -4.750  -0.3357   0.05487   0.05143  -0.0327   1.0000   0.0442
  -4.500  -0.3251   0.05205   0.04860  -0.0319   1.0000   0.0452
  -4.250  -0.3105   0.04925   0.04574  -0.0318   1.0000   0.0467
  -4.000  -0.2919   0.04624   0.04261  -0.0323   1.0000   0.0487
  -3.750  -0.2691   0.04287   0.03905  -0.0334   1.0000   0.0515
  -3.500  -0.2232   0.03972   0.03518  -0.0368   0.9983   0.0561
  -3.250  -0.1874   0.03057   0.02569  -0.0407   0.9966   0.0451
  -3.000  -0.1441   0.02529   0.01976  -0.0435   0.9948   0.0379
  -2.750  -0.1013   0.02014   0.01354  -0.0453   0.9945   0.0338
  -2.500  -0.0630   0.01829   0.01129  -0.0469   0.9921   0.0357
  -2.250  -0.0244   0.01722   0.00989  -0.0487   0.9889   0.0412
  -2.000   0.0151   0.01605   0.00862  -0.0510   0.9861   0.0535
  -1.750   0.0604   0.01493   0.00744  -0.0545   0.9831   0.0840
  -1.500   0.1030   0.01453   0.00710  -0.0577   0.9745   0.1055
  -1.250   0.1508   0.01402   0.00656  -0.0617   0.9687   0.1196
  -1.000   0.1874   0.01359   0.00617  -0.0634   0.9612   0.1376
  -0.750   0.2330   0.01288   0.00574  -0.0671   0.9569   0.2065
  -0.500   0.2692   0.01224   0.00540  -0.0689   0.9482   0.2818
  -0.250   0.3174   0.01015   0.00514  -0.0722   0.9450   1.0000
   0.000   0.3566   0.00990   0.00474  -0.0741   0.9351   1.0000
   0.250   0.3952   0.00965   0.00438  -0.0758   0.9259   1.0000
   0.500   0.4324   0.00939   0.00402  -0.0772   0.9161   1.0000
   0.750   0.4630   0.00923   0.00380  -0.0773   0.9031   1.0000
   1.000   0.4924   0.00910   0.00359  -0.0770   0.8883   1.0000
   1.250   0.5184   0.00903   0.00348  -0.0761   0.8704   1.0000
   1.500   0.5448   0.00897   0.00336  -0.0752   0.8506   1.0000
   1.750   0.5703   0.00894   0.00326  -0.0741   0.8273   1.0000
   2.000   0.5955   0.00893   0.00318  -0.0730   0.7997   1.0000
   2.250   0.6203   0.00895   0.00310  -0.0719   0.7639   1.0000
   2.500   0.6444   0.00905   0.00305  -0.0706   0.7118   1.0000
   2.750   0.6668   0.00935   0.00300  -0.0689   0.6352   1.0000
   3.000   0.6871   0.00992   0.00311  -0.0672   0.5549   1.0000
   3.250   0.7071   0.01060   0.00336  -0.0656   0.4795   1.0000
   3.500   0.7266   0.01136   0.00363  -0.0642   0.3955   1.0000
   3.750   0.7478   0.01202   0.00390  -0.0631   0.3329   1.0000
   4.000   0.7708   0.01253   0.00423  -0.0624   0.2928   1.0000
   4.250   0.7949   0.01295   0.00453  -0.0619   0.2631   1.0000
   4.500   0.8189   0.01338   0.00482  -0.0613   0.2325   1.0000
   4.750   0.8417   0.01398   0.00509  -0.0607   0.1833   1.0000
   5.000   0.8655   0.01449   0.00540  -0.0601   0.1509   1.0000
   5.250   0.8898   0.01496   0.00583  -0.0595   0.1276   1.0000
   5.500   0.9086   0.01627   0.00660  -0.0583   0.0377   1.0000
   5.750   0.9308   0.01714   0.00749  -0.0572   0.0259   1.0000
   6.000   0.9546   0.01778   0.00830  -0.0563   0.0241   1.0000
   6.250   0.9782   0.01846   0.00917  -0.0554   0.0234   1.0000
   6.500   1.0015   0.01920   0.01011  -0.0544   0.0233   1.0000
   6.750   1.0242   0.01999   0.01114  -0.0533   0.0235   1.0000
   7.000   1.0461   0.02083   0.01216  -0.0520   0.0241   1.0000
   7.250   1.0665   0.02178   0.01329  -0.0506   0.0251   1.0000
   7.500   1.0844   0.02301   0.01464  -0.0487   0.0255   1.0000
   7.750   1.1000   0.02455   0.01624  -0.0468   0.0245   1.0000
   8.000   1.1184   0.02605   0.01783  -0.0449   0.0255   1.0000
   8.250   1.1389   0.02794   0.01979  -0.0432   0.0278   1.0000
   8.500   1.1642   0.03000   0.02181  -0.0423   0.0302   1.0000
   8.750   1.1922   0.03102   0.02329  -0.0407   0.0357   1.0000
   9.000   1.2222   0.03387   0.02623  -0.0402   0.0401   1.0000
   9.250   1.2440   0.03603   0.02903  -0.0377   0.0456   1.0000
   9.500   1.2604   0.04044   0.03382  -0.0360   0.0482   1.0000
   9.750   1.2781   0.04487   0.03849  -0.0346   0.0499   1.0000
  10.000   1.2888   0.04695   0.04098  -0.0318   0.0506   1.0000
  10.250   1.2919   0.05002   0.04453  -0.0285   0.0516   1.0000
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