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GOE 371 AIRFOIL (goe371-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 371 AIRFOIL (goe371-il)
Reynolds number: 1,000,000
Max Cl/Cd: 129.75 at α=4.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe371-il-1000000.txt
Download as CSV file: xf-goe371-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 371 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.3330   0.09147   0.08991  -0.0274   1.0000   0.0122
  -8.000  -0.3379   0.08904   0.08752  -0.0271   1.0000   0.0123
  -7.750  -0.3397   0.08676   0.08527  -0.0271   0.9995   0.0123
  -7.500  -0.3187   0.08188   0.08039  -0.0343   0.9953   0.0123
  -7.250  -0.2964   0.07687   0.07537  -0.0416   0.9901   0.0124
  -7.000  -0.2774   0.07107   0.06955  -0.0483   0.9854   0.0127
  -6.750  -0.2542   0.06762   0.06610  -0.0531   0.9808   0.0129
  -6.500  -0.2280   0.06376   0.06221  -0.0593   0.9741   0.0132
  -6.250  -0.1930   0.05956   0.05798  -0.0675   0.9701   0.0143
  -6.000  -0.1461   0.05224   0.05053  -0.0813   0.9584   0.0161
  -5.750  -0.1124   0.04650   0.04466  -0.0888   0.9441   0.0162
  -5.500  -0.0858   0.04144   0.03943  -0.0933   0.9262   0.0162
  -5.000  -0.0472   0.03394   0.03158  -0.0970   0.8872   0.0173
  -4.750  -0.0249   0.03269   0.03020  -0.0972   0.8701   0.0185
  -4.500   0.0054   0.02858   0.02574  -0.0979   0.8538   0.0210
  -4.250   0.0229   0.02387   0.02071  -0.0985   0.8389   0.0197
  -4.000   0.0459   0.01829   0.01451  -0.0978   0.8264   0.0205
  -3.750   0.0700   0.01776   0.01388  -0.0978   0.8147   0.0229
  -3.500   0.0954   0.01749   0.01353  -0.0976   0.8044   0.0245
  -3.250   0.1245   0.01831   0.01420  -0.0969   0.7951   0.0277
  -3.000   0.1467   0.01424   0.00969  -0.0964   0.7872   0.0266
  -2.750   0.1719   0.01275   0.00785  -0.0959   0.7800   0.0294
  -2.500   0.1980   0.01209   0.00715  -0.0956   0.7725   0.0306
  -2.250   0.2244   0.01151   0.00646  -0.0953   0.7655   0.0319
  -2.000   0.2512   0.01023   0.00491  -0.0947   0.7586   0.0305
  -1.750   0.2779   0.00996   0.00461  -0.0944   0.7523   0.0325
  -1.500   0.3048   0.00921   0.00375  -0.0940   0.7457   0.0319
  -1.000   0.3584   0.00832   0.00273  -0.0932   0.7322   0.0316
  -0.500   0.4115   0.00778   0.00209  -0.0923   0.7140   0.0322
  -0.250   0.4380   0.00755   0.00181  -0.0919   0.7028   0.0326
   0.000   0.4644   0.00738   0.00159  -0.0915   0.6904   0.0331
   0.250   0.4910   0.00726   0.00142  -0.0911   0.6760   0.0342
   0.500   0.5175   0.00718   0.00128  -0.0907   0.6582   0.0350
   0.750   0.5434   0.00716   0.00117  -0.0901   0.6309   0.0355
   1.000   0.5675   0.00731   0.00110  -0.0893   0.5780   0.0360
   1.250   0.5916   0.00753   0.00110  -0.0885   0.5331   0.0364
   1.500   0.6169   0.00768   0.00113  -0.0880   0.5072   0.0373
   1.750   0.6431   0.00776   0.00112  -0.0875   0.4900   0.0398
   2.000   0.6694   0.00782   0.00115  -0.0872   0.4774   0.0479
   2.250   0.7104   0.00602   0.00146  -0.0910   0.4651   1.0000
   2.500   0.7365   0.00614   0.00152  -0.0906   0.4548   1.0000
   2.750   0.7625   0.00627   0.00160  -0.0901   0.4458   1.0000
   3.000   0.7886   0.00639   0.00168  -0.0897   0.4372   1.0000
   3.250   0.8147   0.00651   0.00177  -0.0893   0.4280   1.0000
   3.500   0.8405   0.00665   0.00187  -0.0889   0.4169   1.0000
   3.750   0.8663   0.00680   0.00197  -0.0885   0.4062   1.0000
   4.000   0.8922   0.00694   0.00207  -0.0880   0.3934   1.0000
   4.250   0.9180   0.00708   0.00219  -0.0876   0.3802   1.0000
   4.500   0.9433   0.00727   0.00232  -0.0871   0.3631   1.0000
   4.750   0.9679   0.00753   0.00246  -0.0865   0.3342   1.0000
   5.000   0.9892   0.00809   0.00272  -0.0854   0.2719   1.0000
   5.250   1.0105   0.00866   0.00306  -0.0844   0.2249   1.0000
   5.500   1.0336   0.00907   0.00334  -0.0836   0.1990   1.0000
   5.750   1.0575   0.00939   0.00359  -0.0829   0.1822   1.0000
   6.000   1.0818   0.00968   0.00383  -0.0823   0.1692   1.0000
   6.250   1.1058   0.00999   0.00410  -0.0817   0.1553   1.0000
   6.500   1.1291   0.01035   0.00437  -0.0810   0.1375   1.0000
   6.750   1.1520   0.01076   0.00468  -0.0802   0.1146   1.0000
   7.000   1.1712   0.01153   0.00518  -0.0789   0.0737   1.0000
   7.250   1.1911   0.01221   0.00572  -0.0777   0.0483   1.0000
   7.500   1.2081   0.01319   0.00646  -0.0760   0.0180   1.0000
   7.750   1.2301   0.01364   0.00697  -0.0750   0.0150   1.0000
   8.000   1.2513   0.01417   0.00753  -0.0739   0.0134   1.0000
   8.250   1.2705   0.01490   0.00835  -0.0724   0.0117   1.0000
   8.500   1.2917   0.01538   0.00889  -0.0714   0.0112   1.0000
   8.750   1.3120   0.01592   0.00949  -0.0702   0.0107   1.0000
   9.000   1.3320   0.01645   0.01008  -0.0690   0.0100   1.0000
   9.250   1.3509   0.01706   0.01073  -0.0676   0.0093   1.0000
   9.500   1.3661   0.01796   0.01170  -0.0657   0.0086   1.0000
   9.750   1.3737   0.01940   0.01329  -0.0626   0.0081   1.0000
  10.000   1.3902   0.02004   0.01400  -0.0609   0.0079   1.0000
  10.250   1.4050   0.02071   0.01475  -0.0590   0.0077   1.0000
  10.500   1.4162   0.02144   0.01555  -0.0564   0.0075   1.0000
  10.750   1.4230   0.02241   0.01661  -0.0532   0.0073   1.0000
  11.000   1.4316   0.02331   0.01759  -0.0505   0.0071   1.0000
  11.250   1.4385   0.02435   0.01872  -0.0478   0.0069   1.0000
  11.500   1.4460   0.02540   0.01985  -0.0453   0.0066   1.0000
  11.750   1.4538   0.02645   0.02097  -0.0431   0.0064   1.0000
  12.000   1.4571   0.02792   0.02254  -0.0406   0.0063   1.0000
  12.250   1.4610   0.02940   0.02409  -0.0384   0.0061   1.0000
  12.500   1.4635   0.03107   0.02583  -0.0365   0.0059   1.0000
  12.750   1.4607   0.03337   0.02825  -0.0343   0.0058   1.0000
  13.000   1.4381   0.03797   0.03304  -0.0314   0.0055   1.0000
  13.250   1.4404   0.04009   0.03528  -0.0304   0.0054   1.0000
  13.500   1.4477   0.04171   0.03700  -0.0299   0.0053   1.0000
  13.750   1.4487   0.04414   0.03955  -0.0293   0.0053   1.0000
  14.000   1.4452   0.04724   0.04278  -0.0287   0.0052   1.0000
  14.250   1.4421   0.05039   0.04606  -0.0285   0.0051   1.0000
  14.500   1.4376   0.05387   0.04967  -0.0286   0.0051   1.0000
  14.750   1.4308   0.05783   0.05378  -0.0291   0.0050   1.0000
  15.000   1.4254   0.06178   0.05786  -0.0300   0.0050   1.0000
  15.250   1.4163   0.06655   0.06277  -0.0313   0.0049   1.0000
  15.500   1.4049   0.07189   0.06827  -0.0329   0.0049   1.0000
  15.750   1.3975   0.07688   0.07338  -0.0350   0.0048   1.0000
  16.000   1.3860   0.08271   0.07936  -0.0374   0.0048   1.0000
  16.250   1.3715   0.08927   0.08608  -0.0403   0.0048   1.0000
  16.500   1.3620   0.09516   0.09209  -0.0433   0.0047   1.0000
  16.750   1.3470   0.10224   0.09931  -0.0468   0.0048   1.0000
  17.000   1.3330   0.10942   0.10663  -0.0505   0.0047   1.0000
  17.250   1.3168   0.11727   0.11462  -0.0548   0.0047   1.0000
  17.500   1.2994   0.12574   0.12325  -0.0596   0.0047   1.0000
  17.750   1.2841   0.13410   0.13174  -0.0645   0.0048   1.0000
  18.000   1.2692   0.14264   0.14041  -0.0697   0.0047   1.0000
  18.250   1.2503   0.15249   0.15040  -0.0757   0.0048   1.0000
  18.500   1.2354   0.16166   0.15969  -0.0814   0.0048   1.0000
  18.750   1.2153   0.17260   0.17076  -0.0882   0.0049   1.0000
  19.000   1.1936   0.18461   0.18289  -0.0956   0.0050   1.0000
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