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GOE 285 AIRFOIL (goe285-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 285 AIRFOIL (goe285-il)
Reynolds number: 100,000
Max Cl/Cd: 47.2 at α=4.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe285-il-100000.txt
Download as CSV file: xf-goe285-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 285 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.3456   0.10685   0.10152  -0.0280   1.0000   0.1119
  -9.000  -0.3582   0.10484   0.09960  -0.0316   1.0000   0.1155
  -8.750  -0.3934   0.10387   0.09880  -0.0367   1.0000   0.1166
  -8.500  -0.3769   0.09849   0.09344  -0.0350   1.0000   0.1178
  -8.250  -0.3519   0.09469   0.08963  -0.0320   1.0000   0.1199
  -8.000  -0.3455   0.09204   0.08702  -0.0309   1.0000   0.1223
  -7.750  -0.3481   0.08967   0.08472  -0.0303   1.0000   0.1251
  -7.500  -0.3622   0.08769   0.08285  -0.0294   1.0000   0.1278
  -7.250  -0.3957   0.08607   0.08138  -0.0316   1.0000   0.1308
  -7.000  -0.4383   0.08435   0.07960  -0.0354   1.0000   0.1323
  -6.750  -0.4252   0.08024   0.07565  -0.0308   1.0000   0.1335
  -6.500  -0.4208   0.07797   0.07347  -0.0268   1.0000   0.1349
  -6.250  -0.4211   0.07616   0.07172  -0.0236   1.0000   0.1372
  -6.000  -0.4252   0.07426   0.06986  -0.0218   1.0000   0.1405
  -5.750  -0.4440   0.07134   0.06661  -0.0282   1.0000   0.1489
  -5.500  -0.4385   0.06827   0.06372  -0.0247   1.0000   0.1504
  -5.250  -0.4344   0.06630   0.06183  -0.0219   1.0000   0.1527
  -5.000  -0.3936   0.06145   0.05664  -0.0323   0.9916   0.1667
  -4.750  -0.3563   0.05789   0.05314  -0.0351   0.9843   0.1714
  -4.500  -0.3171   0.05381   0.04883  -0.0419   0.9747   0.1858
  -4.250  -0.2628   0.04235   0.03559  -0.0523   0.9668   0.1166
  -4.000  -0.2260   0.03831   0.03160  -0.0555   0.9600   0.1128
  -3.750  -0.1856   0.03332   0.02556  -0.0583   0.9530   0.1015
  -3.500  -0.1447   0.03070   0.02253  -0.0611   0.9455   0.1011
  -3.250  -0.1050   0.02883   0.02017  -0.0632   0.9374   0.1027
  -3.000  -0.0635   0.02717   0.01853  -0.0662   0.9300   0.1078
  -2.750  -0.0241   0.02586   0.01697  -0.0682   0.9214   0.1127
  -2.500   0.0205   0.02432   0.01523  -0.0709   0.9144   0.1200
  -2.250   0.0616   0.02330   0.01414  -0.0732   0.9061   0.1344
  -2.000   0.1043   0.02211   0.01304  -0.0756   0.8984   0.1558
  -1.750   0.1420   0.02131   0.01222  -0.0771   0.8892   0.1808
  -1.500   0.1814   0.02039   0.01152  -0.0790   0.8807   0.2090
  -1.250   0.2138   0.01973   0.01096  -0.0793   0.8689   0.2359
  -1.000   0.2533   0.01867   0.01009  -0.0805   0.8603   0.2686
  -0.750   0.3407   0.01540   0.00924  -0.0895   0.8503   1.0000
  -0.500   0.3698   0.01517   0.00871  -0.0886   0.8334   1.0000
  -0.250   0.3964   0.01502   0.00832  -0.0874   0.8162   1.0000
   0.000   0.4218   0.01496   0.00806  -0.0862   0.7996   1.0000
   0.250   0.4466   0.01495   0.00789  -0.0849   0.7834   1.0000
   0.500   0.4711   0.01497   0.00774  -0.0837   0.7670   1.0000
   0.750   0.4955   0.01500   0.00762  -0.0824   0.7502   1.0000
   1.000   0.5198   0.01504   0.00750  -0.0811   0.7329   1.0000
   1.250   0.5440   0.01508   0.00740  -0.0799   0.7152   1.0000
   1.500   0.5683   0.01514   0.00732  -0.0786   0.6971   1.0000
   1.750   0.5928   0.01523   0.00725  -0.0774   0.6789   1.0000
   2.000   0.6174   0.01536   0.00722  -0.0763   0.6606   1.0000
   2.250   0.6420   0.01553   0.00724  -0.0752   0.6424   1.0000
   2.500   0.6665   0.01574   0.00729  -0.0742   0.6243   1.0000
   2.750   0.6909   0.01599   0.00740  -0.0732   0.6064   1.0000
   3.250   0.7387   0.01654   0.00772  -0.0711   0.5702   1.0000
   3.500   0.7624   0.01684   0.00792  -0.0701   0.5520   1.0000
   3.750   0.7861   0.01714   0.00815  -0.0691   0.5343   1.0000
   4.000   0.8100   0.01748   0.00838  -0.0682   0.5171   1.0000
   4.250   0.8340   0.01785   0.00864  -0.0673   0.5007   1.0000
   4.500   0.8583   0.01826   0.00894  -0.0665   0.4854   1.0000
   4.750   0.8835   0.01872   0.00925  -0.0658   0.4718   1.0000
   5.000   0.9073   0.01924   0.00975  -0.0651   0.4583   1.0000
   5.250   0.9316   0.01983   0.01034  -0.0645   0.4470   1.0000
   5.500   0.9585   0.02044   0.01080  -0.0643   0.4384   1.0000
   5.750   0.9816   0.02108   0.01155  -0.0635   0.4290   1.0000
   6.000   1.0089   0.02174   0.01210  -0.0635   0.4224   1.0000
   6.250   1.0315   0.02246   0.01299  -0.0627   0.4150   1.0000
   6.500   1.0568   0.02311   0.01365  -0.0624   0.4086   1.0000
   6.750   1.0818   0.02383   0.01441  -0.0620   0.4025   1.0000
   7.000   1.1040   0.02445   0.01516  -0.0611   0.3948   1.0000
   7.250   1.1308   0.02499   0.01558  -0.0609   0.3877   1.0000
   7.500   1.1502   0.02556   0.01638  -0.0597   0.3791   1.0000
   7.750   1.1773   0.02596   0.01665  -0.0595   0.3714   1.0000
   8.000   1.1953   0.02652   0.01747  -0.0580   0.3629   1.0000
   8.250   1.2223   0.02682   0.01762  -0.0578   0.3550   1.0000
   8.500   1.2390   0.02729   0.01838  -0.0561   0.3458   1.0000
   8.750   1.2647   0.02757   0.01857  -0.0557   0.3381   1.0000
   9.000   1.2814   0.02804   0.01929  -0.0540   0.3292   1.0000
   9.250   1.3044   0.02827   0.01951  -0.0532   0.3206   1.0000
   9.500   1.3221   0.02852   0.01990  -0.0516   0.3106   1.0000
   9.750   1.3390   0.02878   0.02029  -0.0499   0.3002   1.0000
  10.000   1.3587   0.02890   0.02038  -0.0486   0.2898   1.0000
  10.250   1.3723   0.02916   0.02082  -0.0464   0.2782   1.0000
  10.500   1.3829   0.02946   0.02128  -0.0438   0.2652   1.0000
  10.750   1.3901   0.02975   0.02169  -0.0407   0.2500   1.0000
  11.000   1.3912   0.03018   0.02220  -0.0369   0.2315   1.0000
  11.250   1.3827   0.03095   0.02311  -0.0319   0.2075   1.0000
  11.500   1.3691   0.03249   0.02465  -0.0272   0.1633   1.0000
  11.750   1.3517   0.03520   0.02698  -0.0236   0.1346   1.0000
  12.000   1.3354   0.03851   0.03009  -0.0209   0.1217   1.0000
  12.250   1.3237   0.04180   0.03335  -0.0190   0.1127   1.0000
  12.500   1.3128   0.04517   0.03661  -0.0174   0.1067   1.0000
  12.750   1.3096   0.04805   0.03960  -0.0163   0.1008   1.0000
  13.000   1.3071   0.05084   0.04231  -0.0151   0.0963   1.0000
  13.250   1.3107   0.05318   0.04470  -0.0139   0.0924   1.0000
  13.500   1.3154   0.05546   0.04705  -0.0129   0.0887   1.0000
  13.750   1.3256   0.05718   0.04867  -0.0116   0.0851   1.0000
  14.000   1.3365   0.05906   0.05060  -0.0105   0.0821   1.0000
  14.250   1.3419   0.06146   0.05317  -0.0098   0.0796   1.0000
  14.500   1.3520   0.06349   0.05528  -0.0089   0.0773   1.0000
  14.750   1.3696   0.06493   0.05666  -0.0077   0.0748   1.0000
  15.000   1.3862   0.06693   0.05870  -0.0066   0.0726   1.0000
  15.250   1.3817   0.07036   0.06240  -0.0065   0.0714   1.0000
  15.500   1.3778   0.07390   0.06618  -0.0064   0.0703   1.0000
  15.750   1.3739   0.07760   0.07011  -0.0065   0.0694   1.0000
  16.000   1.3678   0.08163   0.07436  -0.0069   0.0686   1.0000
  16.250   1.3579   0.08612   0.07906  -0.0077   0.0680   1.0000
  16.500   1.3447   0.09113   0.08430  -0.0090   0.0675   1.0000
  16.750   1.3267   0.09696   0.09038  -0.0111   0.0672   1.0000
  17.000   1.2968   0.10487   0.09859  -0.0149   0.0675   1.0000
  17.250   1.2498   0.11650   0.11058  -0.0218   0.0687   1.0000
  17.500   1.1875   0.13277   0.12718  -0.0325   0.0706   1.0000
  17.750   1.1200   0.15304   0.14764  -0.0456   0.0727   1.0000
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