Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

GOE 775 AIRFOIL (goe775-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: GOE 775 AIRFOIL (goe775-il)
Reynolds number: 1,000,000
Max Cl/Cd: 69.78 at α=8.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe775-il-1000000-n5.txt
Download as CSV file: xf-goe775-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 775 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -19.750  -1.3278   0.08126   0.07646  -0.0368   1.0000   0.0440
 -19.500  -1.3365   0.07705   0.07218  -0.0381   1.0000   0.0447
 -19.250  -1.3433   0.07314   0.06821  -0.0392   1.0000   0.0454
 -19.000  -1.3490   0.06940   0.06439  -0.0402   1.0000   0.0460
 -18.750  -1.3535   0.06581   0.06073  -0.0412   1.0000   0.0467
 -18.500  -1.3567   0.06243   0.05727  -0.0420   1.0000   0.0473
 -18.250  -1.3593   0.05918   0.05395  -0.0427   1.0000   0.0479
 -18.000  -1.3631   0.05586   0.05057  -0.0433   1.0000   0.0487
 -17.750  -1.3651   0.05276   0.04742  -0.0438   1.0000   0.0495
 -17.500  -1.3655   0.04990   0.04450  -0.0442   1.0000   0.0504
 -17.250  -1.3643   0.04727   0.04181  -0.0444   1.0000   0.0513
 -17.000  -1.3615   0.04484   0.03932  -0.0446   1.0000   0.0522
 -16.750  -1.3578   0.04254   0.03697  -0.0447   1.0000   0.0530
 -16.500  -1.3552   0.04019   0.03458  -0.0447   1.0000   0.0541
 -16.250  -1.3510   0.03805   0.03239  -0.0446   1.0000   0.0553
 -16.000  -1.3450   0.03611   0.03041  -0.0444   1.0000   0.0566
 -15.750  -1.3375   0.03435   0.02860  -0.0441   1.0000   0.0578
 -15.500  -1.3308   0.03257   0.02680  -0.0437   1.0000   0.0592
 -15.250  -1.3235   0.03090   0.02511  -0.0432   1.0000   0.0609
 -15.000  -1.3144   0.02944   0.02361  -0.0427   1.0000   0.0625
 -14.750  -1.3039   0.02813   0.02226  -0.0421   1.0000   0.0640
 -14.500  -1.2950   0.02674   0.02087  -0.0413   1.0000   0.0658
 -14.250  -1.2843   0.02555   0.01965  -0.0405   1.0000   0.0677
 -14.000  -1.2721   0.02452   0.01859  -0.0396   1.0000   0.0696
 -13.750  -1.2605   0.02349   0.01755  -0.0385   1.0000   0.0714
 -13.500  -1.2489   0.02252   0.01657  -0.0374   1.0000   0.0736
 -13.250  -1.2358   0.02170   0.01574  -0.0362   1.0000   0.0757
 -13.000  -1.2231   0.02094   0.01496  -0.0348   1.0000   0.0777
 -12.750  -1.2120   0.02017   0.01420  -0.0331   1.0000   0.0801
 -12.500  -1.2012   0.01954   0.01356  -0.0311   1.0000   0.0826
 -12.250  -1.1892   0.01899   0.01299  -0.0292   0.9995   0.0845
 -12.000  -1.1659   0.01828   0.01230  -0.0296   0.9963   0.0874
 -11.750  -1.1401   0.01769   0.01170  -0.0303   0.9931   0.0902
 -11.500  -1.1147   0.01718   0.01117  -0.0307   0.9882   0.0923
 -11.250  -1.0912   0.01660   0.01061  -0.0308   0.9816   0.0951
 -11.000  -1.0675   0.01609   0.01010  -0.0308   0.9755   0.0980
 -10.750  -1.0448   0.01567   0.00966  -0.0304   0.9673   0.1005
 -10.500  -1.0240   0.01520   0.00920  -0.0297   0.9591   0.1034
 -10.250  -1.0045   0.01478   0.00877  -0.0286   0.9494   0.1064
 -10.000  -0.9844   0.01443   0.00839  -0.0275   0.9407   0.1093
  -9.750  -0.9654   0.01405   0.00801  -0.0261   0.9315   0.1127
  -9.500  -0.9460   0.01369   0.00764  -0.0248   0.9234   0.1168
  -9.250  -0.9257   0.01339   0.00731  -0.0236   0.9147   0.1205
  -9.000  -0.9061   0.01304   0.00697  -0.0223   0.9069   0.1253
  -8.750  -0.8850   0.01274   0.00667  -0.0212   0.8984   0.1300
  -8.500  -0.8651   0.01243   0.00635  -0.0199   0.8893   0.1357
  -8.250  -0.8438   0.01216   0.00609  -0.0187   0.8801   0.1418
  -8.000  -0.8247   0.01188   0.00581  -0.0171   0.8688   0.1489
  -7.750  -0.8042   0.01165   0.00559  -0.0158   0.8574   0.1557
  -7.500  -0.7829   0.01141   0.00535  -0.0146   0.8447   0.1637
  -7.250  -0.7602   0.01119   0.00512  -0.0136   0.8291   0.1711
  -7.000  -0.7371   0.01100   0.00491  -0.0127   0.8101   0.1792
  -6.750  -0.7145   0.01082   0.00469  -0.0117   0.7865   0.1870
  -6.500  -0.6908   0.01071   0.00450  -0.0109   0.7630   0.1940
  -6.250  -0.6673   0.01057   0.00432  -0.0101   0.7415   0.2010
  -6.000  -0.6427   0.01046   0.00417  -0.0094   0.7240   0.2075
  -5.750  -0.6176   0.01034   0.00402  -0.0089   0.7098   0.2135
  -5.500  -0.5931   0.01022   0.00388  -0.0082   0.6961   0.2210
  -5.250  -0.5670   0.01012   0.00376  -0.0078   0.6839   0.2269
  -5.000  -0.5420   0.00999   0.00362  -0.0073   0.6727   0.2343
  -4.750  -0.5160   0.00988   0.00351  -0.0069   0.6610   0.2419
  -4.500  -0.4905   0.00976   0.00339  -0.0064   0.6501   0.2500
  -4.250  -0.4642   0.00965   0.00328  -0.0060   0.6395   0.2581
  -4.000  -0.4382   0.00957   0.00318  -0.0056   0.6283   0.2654
  -3.750  -0.4120   0.00946   0.00308  -0.0052   0.6175   0.2748
  -3.500  -0.3860   0.00938   0.00299  -0.0048   0.6066   0.2839
  -3.250  -0.3595   0.00928   0.00291  -0.0045   0.5956   0.2940
  -3.000  -0.3332   0.00922   0.00283  -0.0041   0.5840   0.3023
  -2.750  -0.3066   0.00913   0.00276  -0.0038   0.5727   0.3131
  -2.500  -0.2808   0.00904   0.00269  -0.0033   0.5607   0.3265
  -2.250  -0.2546   0.00896   0.00262  -0.0030   0.5479   0.3405
  -2.000  -0.2282   0.00891   0.00257  -0.0026   0.5344   0.3530
  -1.750  -0.2022   0.00888   0.00253  -0.0022   0.5192   0.3634
  -1.500  -0.1753   0.00887   0.00249  -0.0019   0.5044   0.3728
  -1.250  -0.1486   0.00883   0.00246  -0.0016   0.4919   0.3819
  -0.750  -0.0942   0.00882   0.00241  -0.0011   0.4695   0.3979
  -0.250  -0.0403   0.00882   0.00239  -0.0006   0.4467   0.4168
   0.000  -0.0138   0.00881   0.00238  -0.0002   0.4362   0.4271
   0.250   0.0140   0.00881   0.00238  -0.0001   0.4280   0.4355
   0.500   0.0406   0.00881   0.00239   0.0002   0.4179   0.4458
   0.750   0.0680   0.00882   0.00240   0.0004   0.4089   0.4566
   1.000   0.0945   0.00882   0.00241   0.0007   0.3989   0.4685
   1.500   0.1488   0.00883   0.00245   0.0012   0.3828   0.4911
   1.750   0.1755   0.00887   0.00249   0.0015   0.3736   0.5035
   2.000   0.2024   0.00887   0.00252   0.0018   0.3644   0.5185
   2.250   0.2284   0.00891   0.00257   0.0022   0.3537   0.5335
   2.500   0.2549   0.00895   0.00262   0.0026   0.3418   0.5472
   2.750   0.2811   0.00903   0.00268   0.0030   0.3279   0.5601
   3.000   0.3068   0.00913   0.00276   0.0034   0.3142   0.5721
   3.250   0.3334   0.00921   0.00283   0.0037   0.3034   0.5836
   3.500   0.3597   0.00927   0.00291   0.0041   0.2949   0.5950
   3.750   0.3863   0.00937   0.00299   0.0044   0.2852   0.6062
   4.000   0.4122   0.00945   0.00308   0.0048   0.2759   0.6171
   4.250   0.4386   0.00956   0.00318   0.0052   0.2665   0.6280
   4.500   0.4645   0.00965   0.00328   0.0056   0.2589   0.6391
   4.750   0.4908   0.00975   0.00338   0.0060   0.2509   0.6498
   5.000   0.5163   0.00987   0.00350   0.0064   0.2427   0.6607
   5.250   0.5423   0.00998   0.00362   0.0068   0.2352   0.6724
   5.500   0.5673   0.01011   0.00375   0.0074   0.2276   0.6837
   5.750   0.5934   0.01021   0.00387   0.0078   0.2219   0.6959
   6.000   0.6180   0.01033   0.00402   0.0084   0.2144   0.7097
   6.250   0.6431   0.01045   0.00417   0.0090   0.2083   0.7238
   6.500   0.6677   0.01056   0.00432   0.0096   0.2018   0.7413
   6.750   0.6912   0.01070   0.00450   0.0104   0.1947   0.7628
   7.000   0.7150   0.01081   0.00468   0.0112   0.1881   0.7865
   7.250   0.7375   0.01099   0.00490   0.0122   0.1801   0.8101
   7.500   0.7609   0.01117   0.00511   0.0131   0.1724   0.8292
   7.750   0.7835   0.01140   0.00534   0.0140   0.1648   0.8447
   8.000   0.8051   0.01164   0.00557   0.0152   0.1568   0.8573
   8.250   0.8256   0.01187   0.00580   0.0165   0.1499   0.8688
   8.750   0.8660   0.01241   0.00634   0.0192   0.1367   0.8893
   9.000   0.8858   0.01273   0.00666   0.0206   0.1308   0.8984
   9.250   0.9070   0.01302   0.00695   0.0217   0.1260   0.9069
   9.500   0.9267   0.01337   0.00730   0.0230   0.1212   0.9148
   9.750   0.9469   0.01368   0.00763   0.0242   0.1174   0.9235
  10.000   0.9665   0.01403   0.00799   0.0255   0.1133   0.9316
  10.250   0.9853   0.01442   0.00838   0.0268   0.1097   0.9408
  10.500   1.0055   0.01477   0.00875   0.0279   0.1069   0.9495
  10.750   1.0252   0.01518   0.00918   0.0290   0.1039   0.9592
  11.000   1.0458   0.01566   0.00965   0.0297   0.1009   0.9675
  11.250   1.0687   0.01607   0.01008   0.0301   0.0984   0.9757
  11.500   1.0927   0.01657   0.01058   0.0300   0.0956   0.9818
  11.750   1.1162   0.01714   0.01114   0.0299   0.0928   0.9884
  12.000   1.1417   0.01766   0.01168   0.0294   0.0906   0.9932
  12.250   1.1676   0.01825   0.01227   0.0288   0.0879   0.9965
  12.500   1.1911   0.01894   0.01295   0.0283   0.0850   0.9997
  12.750   1.2018   0.01950   0.01352   0.0305   0.0831   1.0000
  13.000   1.2133   0.02012   0.01415   0.0324   0.0807   1.0000
  13.250   1.2249   0.02087   0.01490   0.0340   0.0782   1.0000
  13.500   1.2374   0.02166   0.01569   0.0354   0.0762   1.0000
  13.750   1.2509   0.02245   0.01650   0.0365   0.0742   1.0000
  14.000   1.2629   0.02340   0.01747   0.0377   0.0720   1.0000
  14.250   1.2742   0.02445   0.01853   0.0387   0.0700   1.0000
  14.500   1.2867   0.02547   0.01957   0.0395   0.0682   1.0000
  14.750   1.2978   0.02663   0.02075   0.0404   0.0663   1.0000
  15.000   1.3070   0.02800   0.02213   0.0411   0.0645   1.0000
  15.250   1.3173   0.02933   0.02350   0.0417   0.0629   1.0000
  15.500   1.3268   0.03077   0.02497   0.0422   0.0612   1.0000
  15.750   1.3343   0.03241   0.02663   0.0427   0.0595   1.0000
  16.000   1.3408   0.03421   0.02846   0.0431   0.0581   1.0000
  16.250   1.3485   0.03596   0.03025   0.0434   0.0568   1.0000
  16.500   1.3548   0.03787   0.03221   0.0435   0.0556   1.0000
  16.750   1.3595   0.03997   0.03435   0.0436   0.0544   1.0000
  17.000   1.3623   0.04229   0.03671   0.0437   0.0532   1.0000
  17.250   1.3657   0.04463   0.03910   0.0436   0.0523   1.0000
  17.500   1.3687   0.04705   0.04158   0.0434   0.0514   1.0000
  17.750   1.3701   0.04966   0.04425   0.0431   0.0505   1.0000
  18.000   1.3701   0.05248   0.04712   0.0427   0.0496   1.0000
  18.250   1.3684   0.05553   0.05024   0.0422   0.0487   1.0000
  18.500   1.3648   0.05885   0.05361   0.0416   0.0480   1.0000
  18.750   1.3620   0.06211   0.05694   0.0409   0.0473   1.0000
  19.000   1.3590   0.06548   0.06039   0.0401   0.0467   1.0000
  19.250   1.3547   0.06904   0.06402   0.0392   0.0460   1.0000
<< Back to GOE 775 AIRFOIL (goe775-il)

Polar data table (+)

Polar graphs


<< Back to GOE 775 AIRFOIL (goe775-il)