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GOE 670 AIRFOIL (goe670-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: GOE 670 AIRFOIL (goe670-il)
Reynolds number: 200,000
Max Cl/Cd: 70.49 at α=3.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe670-il-200000-n5.txt
Download as CSV file: xf-goe670-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 670 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
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.4453   0.08678   0.08317  -0.0391   1.0000   0.0312
  -9.000  -0.4617   0.08345   0.07990  -0.0383   1.0000   0.0313
  -8.750  -0.4842   0.08057   0.07712  -0.0366   1.0000   0.0315
  -8.500  -0.4762   0.07630   0.07284  -0.0420   0.9950   0.0321
  -8.250  -0.4564   0.07473   0.07125  -0.0444   0.9915   0.0330
  -8.000  -0.4381   0.07104   0.06752  -0.0497   0.9868   0.0342
  -7.750  -0.4269   0.06475   0.06115  -0.0571   0.9803   0.0350
  -7.500  -0.4141   0.05695   0.05318  -0.0654   0.9749   0.0356
  -7.250  -0.4061   0.04877   0.04473  -0.0710   0.9676   0.0366
  -7.000  -0.4130   0.03368   0.02860  -0.0755   0.9584   0.0386
  -6.750  -0.3948   0.02836   0.02248  -0.0767   0.9547   0.0394
  -6.500  -0.3772   0.02582   0.01949  -0.0759   0.9494   0.0400
  -6.250  -0.3517   0.02419   0.01766  -0.0763   0.9457   0.0411
  -6.000  -0.3210   0.02317   0.01650  -0.0774   0.9433   0.0422
  -5.750  -0.2927   0.02196   0.01506  -0.0779   0.9405   0.0431
  -5.500  -0.2704   0.02088   0.01375  -0.0770   0.9353   0.0439
  -5.250  -0.2412   0.01978   0.01243  -0.0776   0.9326   0.0449
  -5.000  -0.2093   0.01879   0.01123  -0.0785   0.9305   0.0460
  -4.750  -0.1763   0.01789   0.01014  -0.0796   0.9289   0.0472
  -4.500  -0.1558   0.01728   0.00940  -0.0781   0.9225   0.0482
  -4.250  -0.1259   0.01669   0.00868  -0.0785   0.9194   0.0495
  -4.000  -0.0947   0.01595   0.00789  -0.0793   0.9170   0.0516
  -3.750  -0.0618   0.01544   0.00737  -0.0804   0.9150   0.0539
  -3.500  -0.0412   0.01510   0.00700  -0.0788   0.9080   0.0558
  -3.250  -0.0110   0.01465   0.00649  -0.0792   0.9043   0.0585
  -3.000   0.0216   0.01421   0.00598  -0.0800   0.9014   0.0615
  -2.750   0.0457   0.01387   0.00571  -0.0792   0.8954   0.0655
  -2.500   0.0736   0.01361   0.00544  -0.0791   0.8904   0.0709
  -2.250   0.1052   0.01332   0.00518  -0.0798   0.8869   0.0784
  -2.000   0.1326   0.01317   0.00500  -0.0795   0.8814   0.0875
  -1.750   0.1594   0.01295   0.00484  -0.0792   0.8749   0.0966
  -1.500   0.1913   0.01269   0.00457  -0.0799   0.8706   0.1060
  -1.250   0.2160   0.01254   0.00443  -0.0791   0.8620   0.1157
  -1.000   0.2473   0.01224   0.00417  -0.0796   0.8552   0.1265
  -0.750   0.2722   0.01205   0.00400  -0.0788   0.8442   0.1363
  -0.250   0.3293   0.01155   0.00356  -0.0786   0.8228   0.1639
   0.000   0.3552   0.01127   0.00338  -0.0779   0.8071   0.1937
   0.250   0.3790   0.01090   0.00327  -0.0769   0.7898   0.2759
   0.500   0.3948   0.00992   0.00317  -0.0745   0.7719   0.5584
   1.000   0.5403   0.00921   0.00320  -0.0924   0.7273   0.9958
   1.250   0.5724   0.00927   0.00313  -0.0932   0.7064   1.0000
   1.500   0.5952   0.00937   0.00308  -0.0919   0.6858   1.0000
   1.750   0.6175   0.00950   0.00307  -0.0906   0.6656   1.0000
   2.000   0.6395   0.00966   0.00310  -0.0893   0.6470   1.0000
   2.250   0.6614   0.00983   0.00316  -0.0879   0.6304   1.0000
   2.500   0.6832   0.01001   0.00326  -0.0866   0.6144   1.0000
   2.750   0.7049   0.01020   0.00337  -0.0852   0.5977   1.0000
   3.000   0.7260   0.01040   0.00350  -0.0837   0.5790   1.0000
   3.250   0.7464   0.01059   0.00363  -0.0821   0.5538   1.0000
   3.500   0.7648   0.01085   0.00376  -0.0800   0.5153   1.0000
   3.750   0.7796   0.01125   0.00390  -0.0773   0.4598   1.0000
   4.000   0.7926   0.01178   0.00412  -0.0744   0.4080   1.0000
   4.250   0.8082   0.01226   0.00440  -0.0719   0.3691   1.0000
   4.500   0.8251   0.01270   0.00469  -0.0699   0.3385   1.0000
   4.750   0.8431   0.01311   0.00500  -0.0680   0.3154   1.0000
   5.000   0.8617   0.01350   0.00530  -0.0662   0.2965   1.0000
   5.250   0.8808   0.01388   0.00562  -0.0645   0.2819   1.0000
   5.500   0.8999   0.01426   0.00596  -0.0629   0.2698   1.0000
   5.750   0.9198   0.01461   0.00630  -0.0614   0.2599   1.0000
   6.000   0.9398   0.01496   0.00666  -0.0600   0.2526   1.0000
   6.250   0.9597   0.01532   0.00702  -0.0585   0.2442   1.0000
   6.500   0.9793   0.01570   0.00740  -0.0570   0.2337   1.0000
   6.750   0.9979   0.01611   0.00779  -0.0554   0.2212   1.0000
   7.000   1.0163   0.01652   0.00816  -0.0538   0.2076   1.0000
   7.250   1.0359   0.01687   0.00854  -0.0523   0.1957   1.0000
   7.500   1.0551   0.01723   0.00891  -0.0509   0.1818   1.0000
   7.750   1.0740   0.01761   0.00933  -0.0493   0.1678   1.0000
   8.000   1.0914   0.01805   0.00973  -0.0476   0.1462   1.0000
   8.250   1.1026   0.01886   0.01026  -0.0450   0.1020   1.0000
   8.500   1.1117   0.01993   0.01111  -0.0421   0.0737   1.0000
   8.750   1.1198   0.02113   0.01208  -0.0392   0.0399   1.0000
   9.000   1.1306   0.02212   0.01304  -0.0365   0.0320   1.0000
   9.250   1.1428   0.02298   0.01400  -0.0342   0.0284   1.0000
   9.500   1.1521   0.02403   0.01513  -0.0315   0.0258   1.0000
   9.750   1.1636   0.02491   0.01612  -0.0292   0.0242   1.0000
  10.000   1.1745   0.02582   0.01715  -0.0269   0.0225   1.0000
  10.250   1.1838   0.02685   0.01827  -0.0246   0.0211   1.0000
  10.500   1.1902   0.02809   0.01959  -0.0221   0.0199   1.0000
  10.750   1.1922   0.02964   0.02124  -0.0192   0.0191   1.0000
  11.000   1.1980   0.03099   0.02271  -0.0169   0.0186   1.0000
  11.250   1.2037   0.03240   0.02427  -0.0147   0.0179   1.0000
  11.500   1.2085   0.03394   0.02592  -0.0126   0.0174   1.0000
  11.750   1.2131   0.03555   0.02764  -0.0107   0.0167   1.0000
  12.000   1.2169   0.03727   0.02947  -0.0090   0.0161   1.0000
  12.250   1.2206   0.03906   0.03136  -0.0074   0.0155   1.0000
  12.500   1.2231   0.04102   0.03340  -0.0061   0.0149   1.0000
  12.750   1.2241   0.04322   0.03569  -0.0048   0.0146   1.0000
  13.000   1.2216   0.04590   0.03845  -0.0035   0.0141   1.0000
  13.250   1.2201   0.04865   0.04128  -0.0024   0.0139   1.0000
  13.500   1.2220   0.05108   0.04386  -0.0017   0.0137   1.0000
  13.750   1.2230   0.05372   0.04668  -0.0011   0.0135   1.0000
  14.000   1.2228   0.05658   0.04970  -0.0008   0.0132   1.0000
  14.250   1.2223   0.05956   0.05284  -0.0006   0.0130   1.0000
  14.500   1.2204   0.06282   0.05626  -0.0006   0.0128   1.0000
  14.750   1.2174   0.06631   0.05992  -0.0009   0.0126   1.0000
  15.000   1.2135   0.07004   0.06381  -0.0015   0.0124   1.0000
  15.250   1.2079   0.07410   0.06804  -0.0025   0.0121   1.0000
  15.500   1.2012   0.07852   0.07264  -0.0038   0.0120   1.0000
  15.750   1.1932   0.08328   0.07756  -0.0056   0.0117   1.0000
  16.000   1.1850   0.08828   0.08272  -0.0078   0.0115   1.0000
  16.250   1.1760   0.09363   0.08824  -0.0102   0.0114   1.0000
  16.500   1.1644   0.09969   0.09448  -0.0130   0.0114   1.0000
  16.750   1.1547   0.10558   0.10051  -0.0162   0.0112   1.0000
  17.000   1.1411   0.11252   0.10764  -0.0199   0.0113   1.0000
  17.250   1.1305   0.11902   0.11428  -0.0237   0.0110   1.0000
  17.500   1.1148   0.12693   0.12237  -0.0282   0.0111   1.0000
  17.750   1.1004   0.13476   0.13037  -0.0330   0.0110   1.0000
  18.000   1.0786   0.14487   0.14068  -0.0391   0.0112   1.0000
  18.250   1.0600   0.15458   0.15055  -0.0451   0.0112   1.0000
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