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GOE 407 AIRFOIL (goe407-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 407 AIRFOIL (goe407-il)
Reynolds number: 50,000
Max Cl/Cd: 37.51 at α=7°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe407-il-50000-n5.txt
Download as CSV file: xf-goe407-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 407 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.3185   0.10143   0.09479  -0.0287   1.0000   0.1081
  -7.500  -0.3265   0.09969   0.09317  -0.0272   1.0000   0.1100
  -7.250  -0.3388   0.09832   0.09193  -0.0254   1.0000   0.1119
  -7.000  -0.3537   0.09728   0.09102  -0.0249   1.0000   0.1143
  -6.750  -0.3703   0.09663   0.09047  -0.0251   1.0000   0.1155
  -6.500  -0.3857   0.09618   0.09006  -0.0260   1.0000   0.1162
  -6.250  -0.3793   0.09146   0.08548  -0.0208   1.0000   0.1182
  -6.000  -0.3609   0.08787   0.08189  -0.0219   0.9946   0.1240
  -5.500  -0.3148   0.08016   0.07403  -0.0334   0.9748   0.1354
  -5.250  -0.2926   0.07691   0.07071  -0.0373   0.9646   0.1425
  -5.000  -0.2707   0.07341   0.06708  -0.0424   0.9537   0.1488
  -4.750  -0.2464   0.06995   0.06358  -0.0445   0.9463   0.1552
  -4.500  -0.2271   0.06704   0.06051  -0.0478   0.9346   0.1646
  -4.250  -0.2064   0.06470   0.05800  -0.0506   0.9239   0.1787
  -3.750  -0.1677   0.05888   0.05214  -0.0514   0.9068   0.2037
  -3.250  -0.0867   0.04977   0.04160  -0.0604   0.8902   0.0866
  -3.000  -0.0624   0.04725   0.03892  -0.0609   0.8829   0.0834
  -2.750  -0.0358   0.04471   0.03605  -0.0615   0.8751   0.0796
  -2.500  -0.0089   0.04252   0.03343  -0.0617   0.8676   0.0776
  -2.250   0.0186   0.04071   0.03133  -0.0620   0.8604   0.0782
  -2.000   0.0466   0.03902   0.02933  -0.0623   0.8534   0.0786
  -1.750   0.0757   0.03733   0.02721  -0.0623   0.8459   0.0773
  -1.500   0.1103   0.03567   0.02504  -0.0629   0.8400   0.0761
  -1.250   0.1380   0.03444   0.02347  -0.0625   0.8312   0.0758
  -1.000   0.1799   0.03274   0.02145  -0.0646   0.8265   0.0760
  -0.750   0.2052   0.03181   0.02033  -0.0640   0.8161   0.0767
  -0.500   0.2497   0.03050   0.01890  -0.0667   0.8109   0.0802
  -0.250   0.2764   0.02990   0.01812  -0.0663   0.8003   0.0831
   0.000   0.3321   0.02866   0.01654  -0.0706   0.7951   0.0862
   0.250   0.3668   0.02807   0.01577  -0.0715   0.7845   0.0887
   0.500   0.4158   0.02703   0.01466  -0.0748   0.7782   0.0939
   0.750   0.4416   0.02680   0.01433  -0.0742   0.7664   0.1011
   1.000   0.4748   0.02632   0.01387  -0.0749   0.7568   0.1133
   1.250   0.5101   0.02576   0.01334  -0.0758   0.7472   0.1335
   1.500   0.6203   0.02307   0.01251  -0.0924   0.7374   1.0000
   1.750   0.6502   0.02311   0.01230  -0.0922   0.7264   1.0000
   2.000   0.6768   0.02322   0.01224  -0.0915   0.7142   1.0000
   2.250   0.6991   0.02346   0.01235  -0.0902   0.7010   1.0000
   2.500   0.7231   0.02364   0.01241  -0.0891   0.6881   1.0000
   2.750   0.7489   0.02377   0.01244  -0.0883   0.6754   1.0000
   3.000   0.7769   0.02384   0.01239  -0.0878   0.6631   1.0000
   3.250   0.8010   0.02404   0.01252  -0.0867   0.6496   1.0000
   3.500   0.8226   0.02431   0.01276  -0.0852   0.6354   1.0000
   3.750   0.8447   0.02459   0.01298  -0.0839   0.6211   1.0000
   4.000   0.8670   0.02487   0.01323  -0.0826   0.6070   1.0000
   4.250   0.8897   0.02516   0.01350  -0.0813   0.5932   1.0000
   4.500   0.9126   0.02543   0.01374  -0.0801   0.5794   1.0000
   4.750   0.9356   0.02571   0.01400  -0.0789   0.5659   1.0000
   5.000   0.9538   0.02616   0.01449  -0.0771   0.5514   1.0000
   5.250   0.9722   0.02661   0.01497  -0.0753   0.5375   1.0000
   5.500   0.9913   0.02706   0.01545  -0.0737   0.5242   1.0000
   5.750   1.0117   0.02749   0.01590  -0.0722   0.5121   1.0000
   6.000   1.0351   0.02783   0.01625  -0.0712   0.5014   1.0000
   6.250   1.0536   0.02836   0.01684  -0.0696   0.4895   1.0000
   6.500   1.0723   0.02893   0.01746  -0.0680   0.4783   1.0000
   6.750   1.0937   0.02935   0.01790  -0.0667   0.4675   1.0000
   7.000   1.1155   0.02974   0.01833  -0.0655   0.4565   1.0000
   7.250   1.1312   0.03036   0.01901  -0.0634   0.4441   1.0000
   7.500   1.1480   0.03089   0.01958  -0.0614   0.4314   1.0000
   7.750   1.1662   0.03140   0.02013  -0.0597   0.4193   1.0000
   8.000   1.1863   0.03183   0.02054  -0.0582   0.4073   1.0000
   8.250   1.1981   0.03257   0.02140  -0.0557   0.3947   1.0000
   8.500   1.2100   0.03332   0.02224  -0.0532   0.3824   1.0000
   8.750   1.2243   0.03399   0.02298  -0.0510   0.3709   1.0000
   9.000   1.2412   0.03458   0.02363  -0.0492   0.3597   1.0000
   9.250   1.2472   0.03559   0.02483  -0.0461   0.3485   1.0000
   9.500   1.2568   0.03645   0.02581  -0.0434   0.3376   1.0000
   9.750   1.2683   0.03715   0.02656  -0.0409   0.3264   1.0000
  10.000   1.2699   0.03819   0.02776  -0.0372   0.3150   1.0000
  10.250   1.2715   0.03930   0.02904  -0.0338   0.3032   1.0000
  10.500   1.2751   0.04036   0.03020  -0.0307   0.2914   1.0000
  10.750   1.2799   0.04140   0.03129  -0.0279   0.2792   1.0000
  11.000   1.2781   0.04291   0.03294  -0.0248   0.2668   1.0000
  11.250   1.2755   0.04463   0.03480  -0.0219   0.2544   1.0000
  11.500   1.2745   0.04635   0.03661  -0.0195   0.2422   1.0000
  11.750   1.2767   0.04795   0.03824  -0.0174   0.2309   1.0000
  12.000   1.2749   0.05005   0.04050  -0.0154   0.2199   1.0000
  12.250   1.2723   0.05243   0.04301  -0.0138   0.2097   1.0000
  12.500   1.2746   0.05433   0.04492  -0.0123   0.2006   1.0000
  12.750   1.2701   0.05714   0.04790  -0.0110   0.1919   1.0000
  13.000   1.2693   0.05961   0.05045  -0.0099   0.1842   1.0000
  13.250   1.2660   0.06242   0.05340  -0.0091   0.1767   1.0000
  13.500   1.2615   0.06546   0.05653  -0.0084   0.1697   1.0000
  13.750   1.2566   0.06840   0.05953  -0.0079   0.1618   1.0000
  14.000   1.2448   0.07252   0.06379  -0.0080   0.1547   1.0000
  14.250   1.2423   0.07506   0.06625  -0.0077   0.1463   1.0000
  14.500   1.2256   0.08027   0.07167  -0.0087   0.1395   1.0000
  14.750   1.2189   0.08367   0.07498  -0.0091   0.1309   1.0000
  15.000   1.2050   0.08873   0.08019  -0.0103   0.1240   1.0000
  15.250   1.1988   0.09245   0.08386  -0.0110   0.1166   1.0000
  15.500   1.1840   0.09822   0.08985  -0.0128   0.1110   1.0000
  15.750   1.1845   0.10088   0.09239  -0.0129   0.1036   1.0000
  16.000   1.1652   0.10805   0.09988  -0.0157   0.0998   1.0000
  16.250   1.1542   0.11343   0.10537  -0.0176   0.0936   1.0000
  16.500   1.1452   0.11859   0.11059  -0.0194   0.0882   1.0000
  16.750   1.1199   0.12793   0.12018  -0.0239   0.0856   1.0000
  17.000   1.0943   0.13775   0.13014  -0.0288   0.0824   1.0000
  17.250   1.0974   0.14036   0.13271  -0.0295   0.0764   1.0000
  17.500   1.0547   0.15604   0.14848  -0.0379   0.0754   1.0000
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