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GOE 701 AIRFOIL (goe701-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: GOE 701 AIRFOIL (goe701-il)
Reynolds number: 200,000
Max Cl/Cd: 73.75 at α=4.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe701-il-200000-n5.txt
Download as CSV file: xf-goe701-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 701 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.5356   0.03557   0.03084  -0.1088   0.9475   0.0493
  -9.750  -0.5246   0.03064   0.02515  -0.1114   0.9429   0.0510
  -9.500  -0.5131   0.02898   0.02327  -0.1098   0.9337   0.0520
  -9.250  -0.4835   0.02820   0.02247  -0.1109   0.9303   0.0531
  -9.000  -0.4532   0.02715   0.02131  -0.1123   0.9276   0.0542
  -8.750  -0.4370   0.02611   0.02009  -0.1108   0.9189   0.0553
  -8.500  -0.4111   0.02482   0.01856  -0.1113   0.9143   0.0567
  -8.250  -0.3822   0.02344   0.01686  -0.1122   0.9111   0.0583
  -8.000  -0.3653   0.02244   0.01558  -0.1105   0.9021   0.0593
  -7.750  -0.3371   0.02138   0.01439  -0.1110   0.8977   0.0605
  -7.500  -0.3102   0.02068   0.01362  -0.1111   0.8924   0.0616
  -7.250  -0.2852   0.02016   0.01304  -0.1106   0.8855   0.0630
  -7.000  -0.2545   0.01953   0.01229  -0.1113   0.8812   0.0647
  -6.750  -0.2290   0.01892   0.01153  -0.1109   0.8746   0.0664
  -6.500  -0.2018   0.01825   0.01068  -0.1108   0.8685   0.0680
  -6.250  -0.1702   0.01757   0.00988  -0.1116   0.8642   0.0696
  -6.000  -0.1463   0.01720   0.00949  -0.1108   0.8564   0.0712
  -5.750  -0.1165   0.01683   0.00906  -0.1111   0.8507   0.0734
  -5.500  -0.0879   0.01646   0.00859  -0.1112   0.8448   0.0761
  -5.250  -0.0616   0.01607   0.00807  -0.1107   0.8378   0.0786
  -5.000  -0.0312   0.01569   0.00766  -0.1112   0.8325   0.0811
  -4.750  -0.0060   0.01547   0.00742  -0.1105   0.8252   0.0839
  -4.500   0.0224   0.01521   0.00706  -0.1105   0.8189   0.0878
  -4.250   0.0507   0.01493   0.00671  -0.1105   0.8131   0.0918
  -4.000   0.0761   0.01476   0.00654  -0.1099   0.8057   0.0958
  -3.750   0.1054   0.01455   0.00622  -0.1100   0.8001   0.1009
  -3.500   0.1307   0.01434   0.00597  -0.1093   0.7931   0.1053
  -3.250   0.1574   0.01418   0.00581  -0.1090   0.7864   0.1103
  -3.000   0.1860   0.01405   0.00558  -0.1090   0.7808   0.1159
  -2.750   0.2103   0.01389   0.00541  -0.1081   0.7733   0.1205
  -2.500   0.2379   0.01374   0.00524  -0.1079   0.7672   0.1254
  -2.250   0.2638   0.01364   0.00511  -0.1074   0.7606   0.1306
  -2.000   0.2897   0.01353   0.00496  -0.1069   0.7536   0.1353
  -1.750   0.3176   0.01340   0.00483  -0.1067   0.7480   0.1406
  -1.500   0.3416   0.01334   0.00477  -0.1058   0.7402   0.1462
  -1.250   0.3684   0.01325   0.00467  -0.1055   0.7338   0.1526
  -1.000   0.3940   0.01320   0.00463  -0.1049   0.7269   0.1601
  -0.750   0.4194   0.01313   0.00455  -0.1043   0.7197   0.1664
  -0.500   0.4461   0.01304   0.00447  -0.1039   0.7134   0.1730
  -0.250   0.4701   0.01300   0.00443  -0.1029   0.7047   0.1810
   0.000   0.4960   0.01291   0.00435  -0.1024   0.6964   0.1906
   0.250   0.5196   0.01285   0.00431  -0.1013   0.6857   0.2009
   0.500   0.5437   0.01280   0.00425  -0.1004   0.6751   0.2129
   0.750   0.5679   0.01273   0.00418  -0.0995   0.6637   0.2266
   1.000   0.5906   0.01267   0.00415  -0.0983   0.6511   0.2429
   1.250   0.6133   0.01261   0.00415  -0.0971   0.6393   0.2648
   1.500   0.6366   0.01253   0.00417  -0.0961   0.6297   0.3031
   1.750   0.6580   0.01235   0.00423  -0.0948   0.6199   0.3828
   2.250   0.7997   0.01148   0.00466  -0.1128   0.5930   1.0000
   2.500   0.8201   0.01162   0.00471  -0.1112   0.5817   1.0000
   2.750   0.8403   0.01176   0.00479  -0.1095   0.5701   1.0000
   3.000   0.8604   0.01192   0.00488  -0.1079   0.5584   1.0000
   3.250   0.8800   0.01209   0.00498  -0.1061   0.5463   1.0000
   3.500   0.8989   0.01228   0.00509  -0.1042   0.5331   1.0000
   3.750   0.9173   0.01248   0.00522  -0.1022   0.5188   1.0000
   4.000   0.9352   0.01270   0.00537  -0.1001   0.5037   1.0000
   4.250   0.9528   0.01292   0.00553  -0.0980   0.4889   1.0000
   4.500   0.9699   0.01316   0.00571  -0.0959   0.4740   1.0000
   4.750   0.9861   0.01343   0.00590  -0.0935   0.4581   1.0000
   5.000   1.0012   0.01372   0.00612  -0.0910   0.4407   1.0000
   5.250   1.0151   0.01404   0.00635  -0.0882   0.4226   1.0000
   5.500   1.0277   0.01440   0.00661  -0.0853   0.4036   1.0000
   5.750   1.0392   0.01476   0.00688  -0.0821   0.3858   1.0000
   6.000   1.0499   0.01513   0.00719  -0.0789   0.3685   1.0000
   6.250   1.0602   0.01555   0.00752  -0.0756   0.3511   1.0000
   6.500   1.0709   0.01600   0.00788  -0.0725   0.3346   1.0000
   6.750   1.0822   0.01647   0.00829  -0.0696   0.3197   1.0000
   7.250   1.1068   0.01747   0.00918  -0.0644   0.2941   1.0000
   7.500   1.1196   0.01800   0.00967  -0.0620   0.2830   1.0000
   7.750   1.1314   0.01859   0.01020  -0.0595   0.2728   1.0000
   8.000   1.1451   0.01914   0.01073  -0.0574   0.2629   1.0000
   8.250   1.1581   0.01974   0.01131  -0.0552   0.2553   1.0000
   8.500   1.1726   0.02030   0.01187  -0.0533   0.2478   1.0000
   9.000   1.2008   0.02150   0.01309  -0.0496   0.2357   1.0000
   9.250   1.2137   0.02218   0.01378  -0.0477   0.2290   1.0000
   9.500   1.2269   0.02287   0.01447  -0.0459   0.2231   1.0000
   9.750   1.2416   0.02350   0.01516  -0.0443   0.2172   1.0000
  10.000   1.2540   0.02427   0.01593  -0.0425   0.2120   1.0000
  10.250   1.2674   0.02500   0.01671  -0.0409   0.2068   1.0000
  10.500   1.2815   0.02571   0.01749  -0.0395   0.2012   1.0000
  10.750   1.2923   0.02662   0.01839  -0.0377   0.1955   1.0000
  11.000   1.3057   0.02740   0.01925  -0.0363   0.1902   1.0000
  11.250   1.3176   0.02828   0.02018  -0.0348   0.1832   1.0000
  11.500   1.3278   0.02930   0.02123  -0.0333   0.1773   1.0000
  11.750   1.3406   0.03018   0.02220  -0.0320   0.1711   1.0000
  12.000   1.3492   0.03136   0.02339  -0.0305   0.1647   1.0000
  12.250   1.3613   0.03234   0.02446  -0.0293   0.1579   1.0000
  12.500   1.3692   0.03362   0.02578  -0.0279   0.1511   1.0000
  12.750   1.3792   0.03481   0.02703  -0.0267   0.1437   1.0000
  13.000   1.3854   0.03631   0.02854  -0.0254   0.1357   1.0000
  13.250   1.3918   0.03785   0.03011  -0.0242   0.1261   1.0000
  13.500   1.3964   0.03958   0.03187  -0.0230   0.1163   1.0000
  13.750   1.3996   0.04150   0.03379  -0.0218   0.1070   1.0000
  14.000   1.3999   0.04375   0.03604  -0.0207   0.0957   1.0000
  14.250   1.3993   0.04616   0.03844  -0.0197   0.0846   1.0000
  14.500   1.3963   0.04890   0.04116  -0.0188   0.0705   1.0000
  14.750   1.3815   0.05297   0.04508  -0.0180   0.0458   1.0000
  15.000   1.3701   0.05689   0.04896  -0.0174   0.0391   1.0000
  15.250   1.3633   0.06045   0.05259  -0.0172   0.0361   1.0000
  15.500   1.3574   0.06404   0.05629  -0.0171   0.0341   1.0000
  15.750   1.3504   0.06790   0.06026  -0.0173   0.0327   1.0000
  16.250   1.3348   0.07622   0.06883  -0.0184   0.0306   1.0000
  16.500   1.3270   0.08057   0.07334  -0.0192   0.0297   1.0000
  16.750   1.3178   0.08525   0.07816  -0.0203   0.0289   1.0000
  17.000   1.3067   0.09034   0.08341  -0.0216   0.0282   1.0000
  17.250   1.2937   0.09584   0.08905  -0.0233   0.0276   1.0000
  17.500   1.2795   0.10170   0.09504  -0.0253   0.0272   1.0000
  17.750   1.2643   0.10786   0.10134  -0.0276   0.0268   1.0000
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