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GOE 207 (AVIATIK V8) AIRFOIL (goe207-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: GOE 207 (AVIATIK V8) AIRFOIL (goe207-il)
Reynolds number: 500,000
Max Cl/Cd: 96.89 at α=6.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe207-il-500000-n5.txt
Download as CSV file: xf-goe207-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 207 (AVIATIK V8) 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.3042   0.11823   0.11578  -0.0017   0.8535   0.0173
  -9.500  -0.2984   0.11540   0.11280  -0.0028   0.8168   0.0173
  -9.250  -0.2920   0.11253   0.10979  -0.0042   0.7850   0.0173
  -9.000  -0.2853   0.10963   0.10677  -0.0058   0.7580   0.0174
  -8.750  -0.2778   0.10662   0.10366  -0.0070   0.7349   0.0174
  -8.500  -0.2690   0.10382   0.10078  -0.0075   0.7136   0.0175
  -8.250  -0.2600   0.10129   0.09817  -0.0085   0.6941   0.0178
  -8.000  -0.2508   0.09878   0.09559  -0.0097   0.6753   0.0181
  -7.750  -0.2416   0.09619   0.09294  -0.0112   0.6571   0.0184
  -7.500  -0.2326   0.09354   0.09021  -0.0128   0.6391   0.0188
  -7.250  -0.2243   0.09093   0.08754  -0.0145   0.6218   0.0193
  -7.000  -0.2119   0.08797   0.08452  -0.0176   0.6054   0.0198
  -6.750  -0.1965   0.08481   0.08128  -0.0217   0.5906   0.0201
  -6.500  -0.1787   0.08158   0.07798  -0.0264   0.5773   0.0201
  -6.250  -0.1569   0.07819   0.07450  -0.0325   0.5653   0.0202
  -6.000  -0.1339   0.07477   0.07099  -0.0381   0.5540   0.0203
  -5.750  -0.1110   0.07134   0.06747  -0.0427   0.5441   0.0203
  -5.250  -0.0767   0.06558   0.06161  -0.0453   0.5250   0.0206
  -5.000  -0.0545   0.06294   0.05889  -0.0480   0.5157   0.0208
  -4.750  -0.0300   0.06029   0.05618  -0.0512   0.5065   0.0211
  -4.500  -0.0039   0.05766   0.05345  -0.0545   0.4978   0.0215
  -4.250   0.0239   0.05500   0.05070  -0.0579   0.4892   0.0221
  -4.000   0.0596   0.05215   0.04771  -0.0627   0.4817   0.0234
  -3.750   0.0958   0.04925   0.04466  -0.0673   0.4746   0.0235
  -3.250   0.1639   0.04382   0.03891  -0.0739   0.4595   0.0236
  -3.000   0.1955   0.04136   0.03630  -0.0762   0.4509   0.0237
  -2.750   0.2187   0.03891   0.03380  -0.0775   0.4430   0.0239
  -2.500   0.2447   0.03712   0.03193  -0.0787   0.4343   0.0241
  -2.250   0.2733   0.03548   0.03021  -0.0802   0.4264   0.0246
  -2.000   0.3041   0.03380   0.02839  -0.0818   0.4176   0.0253
  -1.750   0.3361   0.03206   0.02651  -0.0833   0.4094   0.0259
  -1.500   0.3747   0.03033   0.02451  -0.0849   0.4005   0.0273
  -1.250   0.4088   0.02859   0.02256  -0.0861   0.3923   0.0275
  -1.000   0.4411   0.02695   0.02071  -0.0871   0.3835   0.0275
  -0.750   0.4726   0.02544   0.01903  -0.0879   0.3753   0.0276
  -0.500   0.5005   0.02388   0.01736  -0.0892   0.3664   0.0280
  -0.250   0.5288   0.02307   0.01648  -0.0899   0.3578   0.0288
   0.000   0.5589   0.02220   0.01546  -0.0905   0.3493   0.0300
   0.250   0.5904   0.02113   0.01422  -0.0911   0.3417   0.0308
   0.750   0.6552   0.01825   0.01086  -0.0920   0.3288   0.0260
   1.000   0.6863   0.01714   0.00953  -0.0923   0.3226   0.0259
   1.250   0.7169   0.01611   0.00828  -0.0925   0.3173   0.0260
   1.500   0.7473   0.01510   0.00706  -0.0927   0.3123   0.0265
   1.750   0.7768   0.01433   0.00608  -0.0927   0.3070   0.0272
   2.000   0.8056   0.01389   0.00548  -0.0928   0.3015   0.0272
   2.250   0.8343   0.01357   0.00507  -0.0929   0.2961   0.0275
   2.500   0.8627   0.01330   0.00472  -0.0931   0.2903   0.0279
   2.750   0.8910   0.01318   0.00456  -0.0932   0.2851   0.0284
   3.000   0.9194   0.01310   0.00448  -0.0933   0.2809   0.0291
   3.250   0.9477   0.01307   0.00444  -0.0935   0.2769   0.0298
   3.500   0.9758   0.01312   0.00445  -0.0936   0.2725   0.0311
   3.750   1.0039   0.01317   0.00448  -0.0937   0.2686   0.0321
   4.000   1.0322   0.01315   0.00449  -0.0938   0.2648   0.0330
   4.250   1.0603   0.01322   0.00456  -0.0939   0.2613   0.0343
   4.500   1.0881   0.01333   0.00466  -0.0940   0.2581   0.0359
   4.750   1.1157   0.01347   0.00479  -0.0941   0.2550   0.0380
   5.000   1.1434   0.01358   0.00494  -0.0941   0.2522   0.0451
   5.250   1.1711   0.01369   0.00512  -0.0942   0.2477   0.0713
   5.500   1.1983   0.01386   0.00530  -0.0942   0.2427   0.0950
   6.000   1.2465   0.01293   0.00579  -0.0932   0.2345   1.0000
   6.250   1.2734   0.01315   0.00598  -0.0932   0.2295   1.0000
   6.500   1.2998   0.01344   0.00622  -0.0931   0.2239   1.0000
   6.750   1.3264   0.01369   0.00645  -0.0931   0.2184   1.0000
   7.000   1.3525   0.01399   0.00670  -0.0930   0.2102   1.0000
   7.250   1.3783   0.01431   0.00700  -0.0929   0.2021   1.0000
   7.500   1.4034   0.01470   0.00732  -0.0927   0.1904   1.0000
   7.750   1.4187   0.01639   0.00850  -0.0916   0.1158   1.0000
   8.000   1.4388   0.01736   0.00938  -0.0909   0.0948   1.0000
   8.250   1.4502   0.01931   0.01102  -0.0892   0.0318   1.0000
   8.500   1.4717   0.01994   0.01168  -0.0885   0.0272   1.0000
   8.750   1.4928   0.02058   0.01236  -0.0878   0.0249   1.0000
   9.000   1.5134   0.02121   0.01306  -0.0871   0.0231   1.0000
   9.250   1.5337   0.02181   0.01372  -0.0863   0.0216   1.0000
   9.500   1.5526   0.02251   0.01447  -0.0853   0.0204   1.0000
   9.750   1.5690   0.02337   0.01539  -0.0841   0.0193   1.0000
  10.000   1.5860   0.02409   0.01619  -0.0830   0.0186   1.0000
  10.250   1.6007   0.02490   0.01708  -0.0815   0.0178   1.0000
  10.500   1.6127   0.02580   0.01804  -0.0797   0.0170   1.0000
  10.750   1.6195   0.02688   0.01918  -0.0773   0.0164   1.0000
  11.000   1.6240   0.02829   0.02069  -0.0751   0.0158   1.0000
  11.250   1.6261   0.03014   0.02264  -0.0733   0.0154   1.0000
  11.500   1.6307   0.03202   0.02462  -0.0723   0.0151   1.0000
  11.750   1.6338   0.03427   0.02698  -0.0716   0.0147   1.0000
  12.000   1.6349   0.03695   0.02978  -0.0714   0.0144   1.0000
  12.250   1.6339   0.04009   0.03305  -0.0715   0.0141   1.0000
  12.500   1.6306   0.04370   0.03677  -0.0719   0.0138   1.0000
  12.750   1.6248   0.04778   0.04100  -0.0725   0.0136   1.0000
  13.000   1.6161   0.05237   0.04571  -0.0734   0.0134   1.0000
  13.250   1.6046   0.05741   0.05089  -0.0744   0.0132   1.0000
  13.500   1.5901   0.06287   0.05649  -0.0755   0.0131   1.0000
  13.750   1.5734   0.06864   0.06239  -0.0766   0.0130   1.0000
  14.000   1.5549   0.07470   0.06858  -0.0777   0.0129   1.0000
  14.250   1.5361   0.08093   0.07495  -0.0791   0.0128   1.0000
  14.500   1.5180   0.08725   0.08140  -0.0805   0.0127   1.0000
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