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GOE 547 AIRFOIL (goe547-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 547 AIRFOIL (goe547-il)
Reynolds number: 200,000
Max Cl/Cd: 86.86 at α=6°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe547-il-200000.txt
Download as CSV file: xf-goe547-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 547 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
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.3910   0.10158   0.09820  -0.0346   1.0000   0.0597
  -8.750  -0.3994   0.09981   0.09648  -0.0327   1.0000   0.0609
  -8.500  -0.4099   0.09801   0.09474  -0.0309   1.0000   0.0620
  -8.250  -0.3094   0.07999   0.07689  -0.0489   0.9862   0.0694
  -8.000  -0.2873   0.07687   0.07374  -0.0500   0.9842   0.0721
  -7.750  -0.2823   0.07290   0.06977  -0.0524   0.9789   0.0744
  -7.500  -0.2819   0.06767   0.06455  -0.0577   0.9739   0.0777
  -7.250  -0.3151   0.05651   0.05319  -0.0789   0.9605   0.0805
  -7.000  -0.3100   0.04942   0.04612  -0.0809   0.9560   0.0819
  -6.750  -0.2906   0.04756   0.04432  -0.0788   0.9513   0.0833
  -6.500  -0.2685   0.04463   0.04136  -0.0802   0.9479   0.0859
  -6.250  -0.2591   0.03864   0.03515  -0.0865   0.9414   0.0923
  -6.000  -0.2489   0.03261   0.02887  -0.0907   0.9351   0.0981
  -5.750  -0.2242   0.02790   0.02366  -0.0960   0.9318   0.1106
  -5.500  -0.2504   0.03247   0.02676  -0.0947   0.9344   0.0656
  -5.250  -0.2184   0.02873   0.02260  -0.0969   0.9322   0.0632
  -5.000  -0.1974   0.02695   0.02046  -0.0960   0.9252   0.0637
  -4.750  -0.1662   0.02485   0.01799  -0.0969   0.9214   0.0631
  -4.500  -0.1305   0.02310   0.01591  -0.0985   0.9191   0.0630
  -4.250  -0.0920   0.02169   0.01421  -0.1005   0.9174   0.0636
  -4.000  -0.0708   0.02096   0.01332  -0.0992   0.9097   0.0647
  -3.750  -0.0344   0.02028   0.01244  -0.1006   0.9065   0.0668
  -3.500   0.0035   0.01892   0.01100  -0.1026   0.9046   0.0684
  -3.250   0.0429   0.01777   0.00988  -0.1049   0.9032   0.0713
  -3.000   0.0662   0.01729   0.00941  -0.1039   0.8961   0.0745
  -2.750   0.1016   0.01667   0.00875  -0.1053   0.8924   0.0794
  -2.500   0.1397   0.01577   0.00793  -0.1074   0.8901   0.0900
  -2.250   0.1775   0.01473   0.00705  -0.1094   0.8881   0.1264
  -2.000   0.1962   0.01409   0.00701  -0.1079   0.8798   0.2653
  -1.750   0.2299   0.01356   0.00680  -0.1091   0.8760   0.3623
  -1.500   0.2664   0.01306   0.00661  -0.1108   0.8733   0.4645
  -1.250   0.2863   0.01291   0.00671  -0.1090   0.8653   0.5417
  -1.000   0.3160   0.01250   0.00658  -0.1091   0.8608   0.6314
  -0.750   0.3493   0.01189   0.00636  -0.1096   0.8578   0.7387
  -0.500   0.4561   0.01131   0.00613  -0.1259   0.8595   1.0000
  -0.250   0.4806   0.01138   0.00609  -0.1252   0.8522   1.0000
   0.000   0.5093   0.01137   0.00598  -0.1253   0.8458   1.0000
   0.250   0.5422   0.01133   0.00583  -0.1262   0.8410   1.0000
   0.500   0.5619   0.01147   0.00592  -0.1245   0.8321   1.0000
   0.750   0.5956   0.01141   0.00578  -0.1255   0.8276   1.0000
   1.000   0.6146   0.01158   0.00591  -0.1236   0.8185   1.0000
   1.250   0.6484   0.01146   0.00571  -0.1245   0.8127   1.0000
   1.500   0.6691   0.01150   0.00571  -0.1228   0.8019   1.0000
   1.750   0.6960   0.01141   0.00557  -0.1222   0.7922   1.0000
   2.000   0.7264   0.01126   0.00534  -0.1222   0.7827   1.0000
   2.250   0.7474   0.01130   0.00537  -0.1206   0.7716   1.0000
   2.500   0.7731   0.01132   0.00536  -0.1198   0.7627   1.0000
   2.750   0.8001   0.01132   0.00533  -0.1194   0.7539   1.0000
   3.000   0.8222   0.01141   0.00543  -0.1181   0.7441   1.0000
   3.250   0.8503   0.01144   0.00544  -0.1179   0.7363   1.0000
   3.500   0.8727   0.01154   0.00557  -0.1166   0.7265   1.0000
   3.750   0.8970   0.01162   0.00566  -0.1157   0.7172   1.0000
   4.000   0.9243   0.01166   0.00568  -0.1153   0.7079   1.0000
   4.250   0.9457   0.01176   0.00584  -0.1138   0.6964   1.0000
   4.500   0.9686   0.01184   0.00593  -0.1126   0.6838   1.0000
   4.750   0.9914   0.01191   0.00601  -0.1113   0.6699   1.0000
   5.000   1.0142   0.01202   0.00614  -0.1100   0.6564   1.0000
   5.250   1.0358   0.01213   0.00626  -0.1085   0.6402   1.0000
   5.500   1.0568   0.01226   0.00639  -0.1068   0.6225   1.0000
   5.750   1.0770   0.01241   0.00651  -0.1050   0.6021   1.0000
   6.000   1.0936   0.01259   0.00669  -0.1025   0.5769   1.0000
   6.250   1.1088   0.01281   0.00688  -0.0997   0.5465   1.0000
   6.500   1.1206   0.01311   0.00707  -0.0963   0.5044   1.0000
   6.750   1.1276   0.01363   0.00733  -0.0921   0.4494   1.0000
   7.000   1.1318   0.01435   0.00775  -0.0876   0.3964   1.0000
   7.250   1.1341   0.01517   0.00829  -0.0828   0.3503   1.0000
   7.500   1.1375   0.01600   0.00892  -0.0784   0.3102   1.0000
   7.750   1.1428   0.01684   0.00959  -0.0745   0.2762   1.0000
   8.000   1.1495   0.01768   0.01028  -0.0710   0.2410   1.0000
   8.250   1.1555   0.01862   0.01104  -0.0676   0.2032   1.0000
   8.500   1.1607   0.01968   0.01187  -0.0642   0.1568   1.0000
   8.750   1.1632   0.02100   0.01292  -0.0607   0.1231   1.0000
   9.000   1.1670   0.02234   0.01413  -0.0574   0.0947   1.0000
   9.250   1.1663   0.02409   0.01560  -0.0536   0.0599   1.0000
   9.500   1.1668   0.02579   0.01727  -0.0501   0.0491   1.0000
   9.750   1.1677   0.02752   0.01900  -0.0469   0.0435   1.0000
  10.000   1.1762   0.02878   0.02035  -0.0447   0.0395   1.0000
  10.250   1.1802   0.03043   0.02201  -0.0422   0.0369   1.0000
  10.500   1.1843   0.03223   0.02386  -0.0397   0.0352   1.0000
  10.750   1.1940   0.03366   0.02539  -0.0378   0.0337   1.0000
  11.000   1.2038   0.03517   0.02700  -0.0361   0.0322   1.0000
  11.250   1.2141   0.03667   0.02855  -0.0344   0.0308   1.0000
  11.500   1.2246   0.03826   0.03015  -0.0330   0.0296   1.0000
  11.750   1.2397   0.04023   0.03215  -0.0317   0.0281   1.0000
  12.000   1.2541   0.04181   0.03388  -0.0304   0.0272   1.0000
  12.250   1.2698   0.04359   0.03583  -0.0293   0.0266   1.0000
  12.500   1.2853   0.04561   0.03805  -0.0281   0.0261   1.0000
  12.750   1.2981   0.04786   0.04051  -0.0269   0.0256   1.0000
  13.000   1.3079   0.05043   0.04332  -0.0256   0.0253   1.0000
  13.250   1.3129   0.05331   0.04645  -0.0240   0.0251   1.0000
  13.500   1.3137   0.05618   0.04956  -0.0225   0.0248   1.0000
  13.750   1.3120   0.05914   0.05274  -0.0211   0.0245   1.0000
  14.000   1.3096   0.06212   0.05589  -0.0199   0.0241   1.0000
  14.250   1.2987   0.06610   0.06016  -0.0187   0.0241   1.0000
  14.500   1.2881   0.06998   0.06428  -0.0179   0.0240   1.0000
  14.750   1.2817   0.07343   0.06785  -0.0176   0.0236   1.0000
  15.000   1.2603   0.07881   0.07355  -0.0177   0.0239   1.0000
  15.250   1.2474   0.08338   0.07830  -0.0183   0.0236   1.0000
  15.500   1.2000   0.09317   0.08859  -0.0213   0.0246   1.0000
  15.750   1.1714   0.10112   0.09680  -0.0247   0.0249   1.0000
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