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GOE 610-B MOD. AIRFOIL (goe610bm-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: GOE 610-B MOD. AIRFOIL (goe610bm-il)
Reynolds number: 500,000
Max Cl/Cd: 107.29 at α=4.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe610bm-il-500000-n5.txt
Download as CSV file: xf-goe610bm-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 610-B MOD. 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
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.2689   0.09236   0.09020  -0.0334   0.9404   0.0074
  -7.500  -0.2600   0.09039   0.08820  -0.0341   0.9263   0.0081
  -7.250  -0.2536   0.08751   0.08529  -0.0354   0.9130   0.0084
  -6.750  -0.2367   0.07801   0.07572  -0.0434   0.8884   0.0069
  -6.500  -0.2221   0.07407   0.07174  -0.0476   0.8765   0.0069
  -6.250  -0.2045   0.06974   0.06736  -0.0527   0.8649   0.0069
  -6.000  -0.1833   0.06477   0.06231  -0.0590   0.8531   0.0070
  -5.750  -0.1587   0.05975   0.05723  -0.0659   0.8401   0.0072
  -5.500  -0.1322   0.05593   0.05331  -0.0715   0.8272   0.0074
  -5.250  -0.1028   0.05192   0.04919  -0.0774   0.8153   0.0078
  -5.000  -0.0709   0.04779   0.04493  -0.0834   0.8038   0.0085
  -4.750  -0.0279   0.04003   0.03692  -0.0936   0.7934   0.0096
  -4.500   0.0236   0.02912   0.02548  -0.1051   0.7844   0.0107
  -4.250   0.0736   0.01599   0.01092  -0.1133   0.7777   0.0152
  -4.000   0.1009   0.01659   0.01152  -0.1132   0.7665   0.0158
  -3.750   0.1286   0.01686   0.01175  -0.1133   0.7560   0.0166
  -3.500   0.1574   0.01646   0.01117  -0.1136   0.7461   0.0182
  -3.250   0.1875   0.01547   0.00985  -0.1141   0.7368   0.0212
  -3.000   0.2170   0.01500   0.00916  -0.1144   0.7279   0.0225
  -2.750   0.2468   0.01384   0.00772  -0.1151   0.7191   0.0244
  -2.500   0.2758   0.01338   0.00713  -0.1155   0.7093   0.0256
  -2.250   0.3049   0.01297   0.00658  -0.1158   0.6999   0.0269
  -2.000   0.3338   0.01265   0.00614  -0.1161   0.6903   0.0285
  -1.750   0.3630   0.01219   0.00553  -0.1163   0.6792   0.0296
  -1.500   0.3921   0.01178   0.00499  -0.1166   0.6666   0.0304
  -1.250   0.4210   0.01142   0.00451  -0.1168   0.6523   0.0309
  -1.000   0.4498   0.01111   0.00408  -0.1170   0.6356   0.0312
  -0.750   0.4784   0.01092   0.00376  -0.1171   0.6142   0.0319
  -0.500   0.5067   0.01075   0.00344  -0.1173   0.5891   0.0322
  -0.250   0.5352   0.01058   0.00313  -0.1174   0.5675   0.0321
   0.000   0.5638   0.01045   0.00288  -0.1176   0.5514   0.0320
   0.250   0.5923   0.01036   0.00269  -0.1178   0.5383   0.0320
   0.500   0.6209   0.01030   0.00255  -0.1180   0.5271   0.0321
   0.750   0.6495   0.01026   0.00244  -0.1182   0.5176   0.0323
   1.000   0.6780   0.01024   0.00237  -0.1184   0.5099   0.0328
   1.250   0.7065   0.01025   0.00233  -0.1186   0.5022   0.0334
   1.500   0.7348   0.01028   0.00233  -0.1187   0.4954   0.0342
   1.750   0.7634   0.01029   0.00229  -0.1189   0.4889   0.0401
   2.250   0.8206   0.01009   0.00250  -0.1196   0.4769   0.2272
   2.500   0.8487   0.00926   0.00278  -0.1203   0.4696   0.7168
   3.000   0.8985   0.00896   0.00285  -0.1189   0.4511   1.0000
   3.250   0.9263   0.00911   0.00295  -0.1190   0.4416   1.0000
   3.500   0.9542   0.00925   0.00306  -0.1191   0.4346   1.0000
   3.750   0.9821   0.00939   0.00319  -0.1192   0.4276   1.0000
   4.000   1.0098   0.00954   0.00332  -0.1193   0.4195   1.0000
   4.250   1.0372   0.00971   0.00347  -0.1193   0.4102   1.0000
   4.500   1.0643   0.00992   0.00363  -0.1193   0.3928   1.0000
   4.750   1.0906   0.01024   0.00381  -0.1192   0.3623   1.0000
   5.000   1.1163   0.01064   0.00404  -0.1191   0.3260   1.0000
   5.250   1.1388   0.01154   0.00450  -0.1187   0.2496   1.0000
   5.500   1.1580   0.01295   0.00534  -0.1178   0.1498   1.0000
   5.750   1.1797   0.01390   0.00597  -0.1173   0.0982   1.0000
   6.000   1.1976   0.01536   0.00693  -0.1161   0.0204   1.0000
   6.250   1.2224   0.01576   0.00738  -0.1157   0.0136   1.0000
   6.500   1.2470   0.01617   0.00788  -0.1153   0.0120   1.0000
   6.750   1.2708   0.01666   0.00847  -0.1148   0.0105   1.0000
   7.000   1.2931   0.01733   0.00926  -0.1140   0.0089   1.0000
   7.250   1.3161   0.01784   0.00984  -0.1133   0.0080   1.0000
   7.500   1.3383   0.01842   0.01050  -0.1126   0.0073   1.0000
   7.750   1.3595   0.01908   0.01126  -0.1117   0.0067   1.0000
   8.000   1.3792   0.01985   0.01211  -0.1106   0.0062   1.0000
   8.250   1.3943   0.02104   0.01340  -0.1088   0.0058   1.0000
   8.500   1.4125   0.02182   0.01427  -0.1074   0.0055   1.0000
   8.750   1.4300   0.02261   0.01514  -0.1060   0.0050   1.0000
   9.000   1.4451   0.02351   0.01612  -0.1042   0.0046   1.0000
   9.250   1.4572   0.02455   0.01724  -0.1020   0.0044   1.0000
   9.500   1.4672   0.02562   0.01840  -0.0995   0.0042   1.0000
   9.750   1.4723   0.02680   0.01970  -0.0963   0.0041   1.0000
  10.000   1.4758   0.02823   0.02122  -0.0932   0.0039   1.0000
  10.250   1.4752   0.03013   0.02323  -0.0900   0.0038   1.0000
  10.500   1.4742   0.03226   0.02547  -0.0871   0.0037   1.0000
  10.750   1.4767   0.03422   0.02756  -0.0849   0.0036   1.0000
  11.000   1.4784   0.03640   0.02986  -0.0828   0.0035   1.0000
  11.250   1.4789   0.03879   0.03238  -0.0808   0.0035   1.0000
  11.500   1.4791   0.04134   0.03505  -0.0791   0.0034   1.0000
  11.750   1.4790   0.04401   0.03785  -0.0774   0.0033   1.0000
  12.000   1.4792   0.04674   0.04072  -0.0759   0.0032   1.0000
  12.250   1.4797   0.04951   0.04362  -0.0746   0.0031   1.0000
  12.500   1.4805   0.05227   0.04651  -0.0735   0.0030   1.0000
  12.750   1.4808   0.05514   0.04951  -0.0727   0.0029   1.0000
  13.000   1.4807   0.05811   0.05261  -0.0721   0.0028   1.0000
  13.250   1.4797   0.06123   0.05585  -0.0718   0.0027   1.0000
  13.500   1.4774   0.06460   0.05936  -0.0716   0.0026   1.0000
  13.750   1.4745   0.06816   0.06308  -0.0717   0.0025   1.0000
  14.000   1.4706   0.07197   0.06703  -0.0719   0.0025   1.0000
  14.250   1.4656   0.07605   0.07125  -0.0723   0.0025   1.0000
  14.500   1.4597   0.08040   0.07574  -0.0730   0.0024   1.0000
  14.750   1.4530   0.08501   0.08050  -0.0739   0.0024   1.0000
  15.000   1.4449   0.08993   0.08557  -0.0749   0.0024   1.0000
  15.250   1.4359   0.09511   0.09089  -0.0763   0.0024   1.0000
  15.500   1.4254   0.10068   0.09661  -0.0779   0.0023   1.0000
  15.750   1.4141   0.10657   0.10267  -0.0798   0.0023   1.0000
  16.250   1.3887   0.11938   0.11581  -0.0848   0.0023   1.0000
  16.500   1.3765   0.12613   0.12274  -0.0880   0.0023   1.0000
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