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GOE 654 AIRFOIL (goe654-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 654 AIRFOIL (goe654-il)
Reynolds number: 1,000,000
Max Cl/Cd: 118.63 at α=7.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe654-il-1000000.txt
Download as CSV file: xf-goe654-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 654 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
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.2181   0.10440   0.10279  -0.0461   0.9902   0.0220
 -10.500  -0.2075   0.10046   0.09884  -0.0493   0.9753   0.0227
 -10.250  -0.2175   0.08790   0.08627  -0.0611   0.9589   0.0241
 -10.000  -0.1749   0.08363   0.08192  -0.0707   0.9396   0.0244
  -9.750  -0.1215   0.07813   0.07631  -0.0846   0.9212   0.0247
  -9.500  -0.0737   0.07339   0.07135  -0.0967   0.8827   0.0253
  -9.250  -0.0661   0.07027   0.06800  -0.0993   0.8347   0.0257
  -9.000  -0.0679   0.06710   0.06470  -0.1003   0.8060   0.0265
  -8.750  -0.1894   0.04417   0.04145  -0.1161   0.7862   0.0282
  -8.500  -0.2367   0.03586   0.03272  -0.1145   0.7703   0.0286
  -8.250  -0.2246   0.03420   0.03098  -0.1135   0.7556   0.0288
  -8.000  -0.2134   0.03251   0.02915  -0.1124   0.7408   0.0290
  -7.750  -0.1979   0.03138   0.02792  -0.1115   0.7257   0.0292
  -7.500  -0.1839   0.02995   0.02635  -0.1104   0.7095   0.0295
  -7.250  -0.1686   0.02858   0.02481  -0.1093   0.6930   0.0298
  -7.000  -0.1528   0.02721   0.02325  -0.1082   0.6745   0.0303
  -6.750  -0.1370   0.02563   0.02143  -0.1069   0.6565   0.0312
  -6.500  -0.1295   0.02291   0.01798  -0.1043   0.6406   0.0336
  -6.250  -0.1184   0.01834   0.01276  -0.1018   0.6254   0.0286
  -6.000  -0.0945   0.01789   0.01214  -0.1010   0.6085   0.0284
  -5.750  -0.0708   0.01723   0.01131  -0.1002   0.5937   0.0284
  -5.500  -0.0467   0.01659   0.01052  -0.0995   0.5814   0.0283
  -5.250  -0.0226   0.01582   0.00960  -0.0987   0.5709   0.0283
  -5.000   0.0013   0.01466   0.00829  -0.0980   0.5622   0.0284
  -4.750   0.0249   0.01346   0.00699  -0.0973   0.5551   0.0288
  -4.500   0.0506   0.01287   0.00636  -0.0968   0.5496   0.0292
  -4.250   0.0763   0.01243   0.00587  -0.0963   0.5440   0.0294
  -4.000   0.1020   0.01206   0.00544  -0.0958   0.5387   0.0296
  -3.750   0.1284   0.01171   0.00507  -0.0954   0.5343   0.0299
  -3.500   0.1546   0.01139   0.00472  -0.0949   0.5296   0.0302
  -3.250   0.1806   0.01113   0.00441  -0.0944   0.5249   0.0305
  -3.000   0.2068   0.01087   0.00412  -0.0939   0.5209   0.0307
  -2.750   0.2335   0.01061   0.00385  -0.0935   0.5175   0.0311
  -2.500   0.2600   0.01039   0.00361  -0.0931   0.5136   0.0314
  -2.250   0.2864   0.01021   0.00339  -0.0927   0.5095   0.0319
  -2.000   0.3127   0.01011   0.00324  -0.0922   0.5049   0.0325
  -1.750   0.3402   0.00996   0.00309  -0.0920   0.5015   0.0329
  -1.500   0.3669   0.00975   0.00286  -0.0916   0.4974   0.0335
  -1.250   0.3932   0.00955   0.00262  -0.0912   0.4933   0.0342
  -1.000   0.4195   0.00946   0.00249  -0.0907   0.4888   0.0351
  -0.750   0.4471   0.00935   0.00239  -0.0905   0.4854   0.0360
  -0.500   0.4745   0.00926   0.00229  -0.0903   0.4812   0.0371
  -0.250   0.5016   0.00921   0.00222  -0.0900   0.4764   0.0382
   0.000   0.5283   0.00918   0.00215  -0.0896   0.4712   0.0401
   0.250   0.5559   0.00909   0.00209  -0.0894   0.4665   0.0440
   0.500   0.5818   0.00886   0.00204  -0.0890   0.4606   0.1095
   0.750   0.6038   0.00829   0.00206  -0.0881   0.4549   0.3320
   1.000   0.6289   0.00800   0.00210  -0.0876   0.4491   0.4521
   1.250   0.6526   0.00778   0.00216  -0.0868   0.4419   0.5656
   1.500   0.6751   0.00752   0.00222  -0.0857   0.4347   0.6836
   1.750   0.6942   0.00703   0.00235  -0.0835   0.4255   0.9148
   2.000   0.7936   0.00727   0.00249  -0.0990   0.4053   0.9988
   2.250   0.8227   0.00743   0.00255  -0.0994   0.3913   1.0000
   2.500   0.8451   0.00760   0.00263  -0.0982   0.3785   1.0000
   2.750   0.8677   0.00776   0.00272  -0.0971   0.3676   1.0000
   3.000   0.8899   0.00795   0.00283  -0.0960   0.3575   1.0000
   3.250   0.9125   0.00813   0.00295  -0.0949   0.3488   1.0000
   3.500   0.9355   0.00829   0.00306  -0.0939   0.3420   1.0000
   3.750   0.9587   0.00845   0.00318  -0.0930   0.3360   1.0000
   4.000   0.9810   0.00866   0.00333  -0.0919   0.3296   1.0000
   4.250   1.0052   0.00878   0.00344  -0.0911   0.3258   1.0000
   4.500   1.0286   0.00894   0.00357  -0.0903   0.3214   1.0000
   4.750   1.0513   0.00913   0.00372  -0.0893   0.3167   1.0000
   5.000   1.0743   0.00931   0.00387  -0.0883   0.3124   1.0000
   5.250   1.0985   0.00943   0.00400  -0.0876   0.3087   1.0000
   5.500   1.1216   0.00961   0.00414  -0.0868   0.3041   1.0000
   5.750   1.1436   0.00984   0.00433  -0.0857   0.2992   1.0000
   6.000   1.1673   0.00998   0.00448  -0.0849   0.2960   1.0000
   6.250   1.1913   0.01011   0.00462  -0.0842   0.2931   1.0000
   6.500   1.2145   0.01028   0.00478  -0.0834   0.2900   1.0000
   6.750   1.2367   0.01048   0.00497  -0.0825   0.2861   1.0000
   7.000   1.2583   0.01071   0.00518  -0.0814   0.2815   1.0000
   7.250   1.2823   0.01083   0.00532  -0.0807   0.2785   1.0000
   7.500   1.3049   0.01100   0.00549  -0.0799   0.2747   1.0000
   7.750   1.3259   0.01124   0.00570  -0.0787   0.2698   1.0000
   8.000   1.3468   0.01146   0.00592  -0.0776   0.2661   1.0000
   8.250   1.3694   0.01160   0.00610  -0.0768   0.2630   1.0000
   8.500   1.3894   0.01180   0.00630  -0.0754   0.2587   1.0000
   8.750   1.4065   0.01207   0.00654  -0.0736   0.2535   1.0000
   9.000   1.4258   0.01227   0.00676  -0.0722   0.2496   1.0000
   9.250   1.4450   0.01249   0.00699  -0.0708   0.2444   1.0000
   9.500   1.4610   0.01284   0.00731  -0.0689   0.2377   1.0000
   9.750   1.4801   0.01308   0.00757  -0.0675   0.2320   1.0000
  10.000   1.4947   0.01351   0.00794  -0.0656   0.2226   1.0000
  10.250   1.5105   0.01391   0.00832  -0.0638   0.2126   1.0000
  10.500   1.5233   0.01445   0.00880  -0.0617   0.2005   1.0000
  10.750   1.5320   0.01519   0.00946  -0.0591   0.1850   1.0000
  11.000   1.5367   0.01616   0.01032  -0.0561   0.1679   1.0000
  11.250   1.5376   0.01740   0.01145  -0.0529   0.1472   1.0000
  11.500   1.5366   0.01887   0.01280  -0.0499   0.1291   1.0000
  11.750   1.5305   0.02082   0.01462  -0.0467   0.1075   1.0000
  12.000   1.5202   0.02328   0.01694  -0.0438   0.0836   1.0000
  12.250   1.4913   0.02753   0.02101  -0.0405   0.0474   1.0000
  12.500   1.4689   0.03176   0.02519  -0.0385   0.0219   1.0000
  12.750   1.4690   0.03416   0.02763  -0.0377   0.0186   1.0000
  13.000   1.4686   0.03670   0.03023  -0.0371   0.0168   1.0000
  13.250   1.4697   0.03916   0.03276  -0.0366   0.0160   1.0000
  13.500   1.4715   0.04160   0.03528  -0.0363   0.0156   1.0000
  13.750   1.4726   0.04421   0.03797  -0.0361   0.0151   1.0000
  14.000   1.4717   0.04706   0.04090  -0.0360   0.0146   1.0000
  14.250   1.4700   0.05007   0.04398  -0.0359   0.0143   1.0000
  14.500   1.4667   0.05332   0.04732  -0.0360   0.0140   1.0000
  14.750   1.4601   0.05701   0.05109  -0.0361   0.0135   1.0000
  15.000   1.4521   0.06090   0.05508  -0.0363   0.0132   1.0000
  15.250   1.4436   0.06492   0.05920  -0.0366   0.0131   1.0000
  15.500   1.4377   0.06867   0.06304  -0.0370   0.0129   1.0000
  15.750   1.4329   0.07228   0.06673  -0.0373   0.0127   1.0000
  16.000   1.4280   0.07597   0.07050  -0.0378   0.0124   1.0000
  16.250   1.4184   0.08036   0.07499  -0.0384   0.0123   1.0000
  16.500   1.4102   0.08459   0.07930  -0.0390   0.0121   1.0000
  16.750   1.4012   0.08899   0.08379  -0.0398   0.0119   1.0000
  17.000   1.3915   0.09357   0.08846  -0.0407   0.0118   1.0000
  17.250   1.3823   0.09813   0.09311  -0.0416   0.0117   1.0000
  17.500   1.3721   0.10288   0.09794  -0.0427   0.0115   1.0000
  17.750   1.3619   0.10769   0.10284  -0.0439   0.0114   1.0000
  18.000   1.3516   0.11260   0.10784  -0.0452   0.0113   1.0000
  18.250   1.3406   0.11769   0.11302  -0.0468   0.0111   1.0000
  18.500   1.3289   0.12296   0.11837  -0.0485   0.0110   1.0000
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