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GOE 207 (AVIATIK V8) AIRFOIL (goe207-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 207 (AVIATIK V8) AIRFOIL (goe207-il)
Reynolds number: 1,000,000
Max Cl/Cd: 120.17 at α=6.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe207-il-1000000.txt
Download as CSV file: xf-goe207-il-1000000.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 =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.3352   0.12697   0.12544   0.0028   1.0000   0.0143
 -10.250  -0.3291   0.12379   0.12227   0.0007   1.0000   0.0143
 -10.000  -0.3220   0.12004   0.11853  -0.0003   1.0000   0.0144
  -9.750  -0.3136   0.11684   0.11534  -0.0009   1.0000   0.0145
  -9.500  -0.3039   0.11392   0.11243  -0.0023   0.9715   0.0146
  -9.250  -0.2970   0.11155   0.10982  -0.0027   0.8841   0.0147
  -9.000  -0.2900   0.10913   0.10725  -0.0033   0.8463   0.0149
  -8.750  -0.2822   0.10659   0.10459  -0.0043   0.8149   0.0151
  -8.500  -0.2739   0.10399   0.10187  -0.0054   0.7864   0.0154
  -8.250  -0.2654   0.10133   0.09912  -0.0068   0.7611   0.0157
  -7.750  -0.2476   0.09572   0.09334  -0.0101   0.7194   0.0169
  -7.500  -0.2394   0.09288   0.09044  -0.0126   0.7012   0.0170
  -7.250  -0.2286   0.08994   0.08744  -0.0164   0.6833   0.0171
  -7.000  -0.2129   0.08667   0.08409  -0.0214   0.6648   0.0171
  -6.750  -0.1949   0.08327   0.08061  -0.0268   0.6458   0.0172
  -6.250  -0.1639   0.07609   0.07326  -0.0321   0.6068   0.0173
  -5.750  -0.1286   0.07062   0.06761  -0.0366   0.5705   0.0176
  -5.500  -0.1072   0.06788   0.06481  -0.0399   0.5565   0.0178
  -5.250  -0.0840   0.06510   0.06196  -0.0434   0.5453   0.0181
  -5.000  -0.0593   0.06228   0.05906  -0.0471   0.5355   0.0186
  -4.750  -0.0328   0.05937   0.05608  -0.0509   0.5266   0.0192
  -4.500  -0.0006   0.05633   0.05293  -0.0556   0.5182   0.0200
  -4.250   0.0365   0.05321   0.04969  -0.0612   0.5101   0.0202
  -4.000   0.0735   0.05007   0.04640  -0.0663   0.5025   0.0203
  -3.750   0.1054   0.04709   0.04331  -0.0695   0.4957   0.0203
  -3.500   0.1281   0.04369   0.03984  -0.0713   0.4886   0.0205
  -3.250   0.1533   0.04155   0.03766  -0.0728   0.4819   0.0207
  -3.000   0.1812   0.03959   0.03562  -0.0746   0.4743   0.0209
  -2.750   0.2108   0.03769   0.03362  -0.0765   0.4673   0.0212
  -2.500   0.2417   0.03577   0.03161  -0.0784   0.4596   0.0217
  -2.250   0.2734   0.03388   0.02959  -0.0802   0.4521   0.0223
  -2.000   0.3074   0.03198   0.02756  -0.0819   0.4441   0.0233
  -1.750   0.3471   0.03012   0.02545  -0.0836   0.4360   0.0237
  -1.500   0.3799   0.02823   0.02341  -0.0848   0.4271   0.0238
  -1.250   0.4103   0.02558   0.02061  -0.0865   0.4182   0.0241
  -1.000   0.4388   0.02441   0.01935  -0.0874   0.4079   0.0244
  -0.750   0.4683   0.02334   0.01817  -0.0883   0.3986   0.0248
  -0.500   0.4988   0.02227   0.01695  -0.0890   0.3886   0.0256
  -0.250   0.5335   0.02111   0.01559  -0.0892   0.3798   0.0276
   0.000   0.5658   0.01998   0.01425  -0.0896   0.3709   0.0277
   0.250   0.5970   0.01807   0.01216  -0.0907   0.3621   0.0282
   0.500   0.6261   0.01743   0.01142  -0.0913   0.3537   0.0287
   0.750   0.6557   0.01678   0.01066  -0.0918   0.3452   0.0292
   1.000   0.6858   0.01609   0.00984  -0.0922   0.3371   0.0302
   1.250   0.7175   0.01552   0.00899  -0.0918   0.3291   0.0324
   2.750   0.8947   0.01153   0.00425  -0.0933   0.2936   0.0320
   3.000   0.9237   0.01121   0.00389  -0.0935   0.2896   0.0319
   3.250   0.9523   0.01113   0.00378  -0.0937   0.2849   0.0323
   3.500   0.9811   0.01102   0.00361  -0.0939   0.2795   0.0331
   3.750   1.0099   0.01097   0.00357  -0.0941   0.2763   0.0341
   4.000   1.0384   0.01099   0.00359  -0.0943   0.2722   0.0352
   4.250   1.0666   0.01108   0.00366  -0.0944   0.2675   0.0371
   4.500   1.0949   0.01115   0.00371  -0.0946   0.2625   0.0389
   4.750   1.1232   0.01121   0.00377  -0.0947   0.2579   0.0430
   5.000   1.1512   0.01132   0.00391  -0.0948   0.2523   0.0646
   5.250   1.1790   0.01144   0.00407  -0.0949   0.2479   0.1051
   5.500   1.2022   0.01018   0.00435  -0.0944   0.2449   1.0000
   5.750   1.2300   0.01035   0.00449  -0.0945   0.2411   1.0000
   6.000   1.2573   0.01057   0.00465  -0.0945   0.2361   1.0000
   6.250   1.2849   0.01074   0.00480  -0.0946   0.2315   1.0000
   6.500   1.3123   0.01092   0.00496  -0.0947   0.2264   1.0000
   6.750   1.3390   0.01120   0.00518  -0.0947   0.2195   1.0000
   7.000   1.3662   0.01138   0.00535  -0.0948   0.2127   1.0000
   7.250   1.3925   0.01170   0.00559  -0.0947   0.2016   1.0000
   7.500   1.4167   0.01231   0.00600  -0.0945   0.1721   1.0000
   7.750   1.4300   0.01445   0.00759  -0.0931   0.0883   1.0000
   8.000   1.4454   0.01616   0.00900  -0.0918   0.0277   1.0000
   8.250   1.4695   0.01661   0.00948  -0.0914   0.0254   1.0000
   8.500   1.4923   0.01719   0.01010  -0.0909   0.0232   1.0000
   8.750   1.5153   0.01771   0.01066  -0.0904   0.0219   1.0000
   9.000   1.5381   0.01821   0.01119  -0.0899   0.0209   1.0000
   9.250   1.5600   0.01877   0.01177  -0.0893   0.0199   1.0000
   9.500   1.5801   0.01948   0.01253  -0.0885   0.0187   1.0000
   9.750   1.5989   0.02026   0.01338  -0.0875   0.0179   1.0000
  10.000   1.6190   0.02084   0.01401  -0.0867   0.0173   1.0000
  10.250   1.6377   0.02151   0.01472  -0.0857   0.0167   1.0000
  10.500   1.6549   0.02224   0.01550  -0.0845   0.0161   1.0000
  10.750   1.6698   0.02305   0.01636  -0.0830   0.0156   1.0000
  11.000   1.6807   0.02405   0.01741  -0.0811   0.0151   1.0000
  11.250   1.6793   0.02555   0.01903  -0.0775   0.0147   1.0000
  11.500   1.6794   0.02722   0.02080  -0.0748   0.0144   1.0000
  11.750   1.6870   0.02860   0.02225  -0.0734   0.0141   1.0000
  12.000   1.6919   0.03041   0.02415  -0.0723   0.0138   1.0000
  12.250   1.6945   0.03269   0.02653  -0.0717   0.0136   1.0000
  12.500   1.6951   0.03543   0.02937  -0.0714   0.0133   1.0000
  12.750   1.6936   0.03867   0.03271  -0.0716   0.0131   1.0000
  13.000   1.6896   0.04238   0.03654  -0.0720   0.0129   1.0000
  13.250   1.6827   0.04665   0.04092  -0.0728   0.0127   1.0000
  13.500   1.6723   0.05148   0.04587  -0.0737   0.0126   1.0000
  13.750   1.6586   0.05682   0.05134  -0.0747   0.0125   1.0000
  14.000   1.6414   0.06264   0.05730  -0.0758   0.0124   1.0000
  14.250   1.6214   0.06884   0.06362  -0.0769   0.0124   1.0000
  14.500   1.6001   0.07525   0.07016  -0.0781   0.0123   1.0000
  14.750   1.5800   0.08167   0.07670  -0.0795   0.0123   1.0000
  15.000   1.5598   0.08829   0.08343  -0.0810   0.0123   1.0000
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