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GOE 402 AIRFOIL (goe402-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 402 AIRFOIL (goe402-il)
Reynolds number: 100,000
Max Cl/Cd: 55.07 at α=9.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe402-il-100000.txt
Download as CSV file: xf-goe402-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 402 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
  ------ -------- --------- --------- -------- -------- --------
  -7.500  -0.2794   0.09509   0.09051  -0.0218   1.0000   0.0420
  -7.250  -0.2794   0.09296   0.08847  -0.0215   1.0000   0.0428
  -7.000  -0.2796   0.09084   0.08644  -0.0214   1.0000   0.0437
  -6.750  -0.2767   0.08859   0.08427  -0.0222   1.0000   0.0446
  -6.500  -0.2732   0.08665   0.08241  -0.0240   1.0000   0.0460
  -6.250  -0.2675   0.08532   0.08115  -0.0275   1.0000   0.0469
  -6.000  -0.2577   0.08499   0.08084  -0.0333   1.0000   0.0475
  -5.750  -0.2536   0.08413   0.08000  -0.0351   1.0000   0.0477
  -5.500  -0.2664   0.08061   0.07665  -0.0307   1.0000   0.0482
  -5.250  -0.2798   0.07819   0.07435  -0.0258   1.0000   0.0487
  -5.000  -0.2673   0.07403   0.07024  -0.0257   0.9957   0.0506
  -4.750  -0.2274   0.06942   0.06556  -0.0334   0.9868   0.0539
  -4.500  -0.1476   0.06680   0.06248  -0.0526   0.9751   0.0598
  -4.250  -0.1246   0.06019   0.05597  -0.0552   0.9677   0.0617
  -4.000  -0.0911   0.05604   0.05179  -0.0593   0.9585   0.0662
  -3.750  -0.0332   0.05225   0.04767  -0.0697   0.9475   0.0748
  -3.500   0.0193   0.04924   0.04434  -0.0772   0.9378   0.0881
  -3.250   0.0531   0.04428   0.03949  -0.0804   0.9291   0.0967
  -3.000   0.0981   0.04089   0.03589  -0.0855   0.9170   0.1111
  -2.750   0.1422   0.03793   0.03265  -0.0901   0.9047   0.1328
  -1.500   0.2789   0.02595   0.02046  -0.0925   0.8418   0.3940
  -1.250   0.2990   0.02373   0.01827  -0.0905   0.8279   0.4548
  -1.000   0.3311   0.02237   0.01665  -0.0910   0.8137   0.4795
  -0.750   0.4191   0.02235   0.01446  -0.0979   0.8002   0.1438
  -0.500   0.4488   0.02102   0.01275  -0.0971   0.7861   0.1270
  -0.250   0.4780   0.02019   0.01148  -0.0960   0.7719   0.1147
   0.000   0.5049   0.01932   0.01042  -0.0951   0.7576   0.1106
   0.250   0.5316   0.01874   0.00967  -0.0941   0.7432   0.1100
   0.500   0.5577   0.01835   0.00912  -0.0931   0.7286   0.1133
   0.750   0.5835   0.01793   0.00860  -0.0920   0.7137   0.1134
   1.000   0.6086   0.01759   0.00818  -0.0908   0.6986   0.1147
   1.250   0.6338   0.01732   0.00781  -0.0897   0.6832   0.1178
   1.500   0.6594   0.01715   0.00755  -0.0887   0.6676   0.1249
   1.750   0.6852   0.01703   0.00737  -0.0878   0.6518   0.1446
   2.000   0.7191   0.01526   0.00723  -0.0886   0.6355   1.0000
   2.250   0.7440   0.01547   0.00714  -0.0875   0.6179   1.0000
   2.500   0.7687   0.01569   0.00714  -0.0865   0.6005   1.0000
   2.750   0.7937   0.01594   0.00720  -0.0856   0.5841   1.0000
   3.000   0.8189   0.01624   0.00734  -0.0849   0.5689   1.0000
   3.250   0.8440   0.01657   0.00753  -0.0842   0.5545   1.0000
   3.500   0.8692   0.01693   0.00777  -0.0835   0.5411   1.0000
   3.750   0.8946   0.01731   0.00804  -0.0830   0.5291   1.0000
   4.000   0.9207   0.01770   0.00832  -0.0825   0.5190   1.0000
   4.250   0.9452   0.01816   0.00880  -0.0819   0.5076   1.0000
   4.500   0.9701   0.01861   0.00924  -0.0814   0.4973   1.0000
   4.750   0.9957   0.01900   0.00955  -0.0809   0.4880   1.0000
   5.000   1.0203   0.01940   0.01001  -0.0803   0.4779   1.0000
   5.250   1.0447   0.01989   0.01055  -0.0798   0.4689   1.0000
   5.500   1.0707   0.02033   0.01095  -0.0794   0.4617   1.0000
   5.750   1.0943   0.02090   0.01167  -0.0788   0.4533   1.0000
   6.000   1.1207   0.02132   0.01207  -0.0785   0.4465   1.0000
   6.250   1.1433   0.02195   0.01291  -0.0778   0.4385   1.0000
   6.500   1.1698   0.02240   0.01334  -0.0775   0.4321   1.0000
   6.750   1.1917   0.02299   0.01416  -0.0767   0.4232   1.0000
   7.000   1.2175   0.02348   0.01467  -0.0763   0.4165   1.0000
   7.250   1.2394   0.02415   0.01562  -0.0755   0.4085   1.0000
   7.500   1.2647   0.02469   0.01623  -0.0750   0.4016   1.0000
   7.750   1.2867   0.02531   0.01708  -0.0742   0.3928   1.0000
   8.000   1.3094   0.02591   0.01786  -0.0734   0.3839   1.0000
   8.250   1.3319   0.02607   0.01813  -0.0723   0.3705   1.0000
   8.500   1.3517   0.02588   0.01799  -0.0707   0.3513   1.0000
   8.750   1.3712   0.02559   0.01761  -0.0690   0.3301   1.0000
   9.000   1.3850   0.02555   0.01778  -0.0667   0.3080   1.0000
   9.250   1.3993   0.02555   0.01794  -0.0645   0.2865   1.0000
   9.500   1.4086   0.02558   0.01829  -0.0616   0.2535   1.0000
   9.750   1.4030   0.02684   0.01907  -0.0572   0.1541   1.0000
  10.000   1.3844   0.03033   0.02193  -0.0523   0.0975   1.0000
  10.250   1.3738   0.03286   0.02426  -0.0481   0.0713   1.0000
  10.500   1.3616   0.03551   0.02679  -0.0445   0.0633   1.0000
  10.750   1.3530   0.03814   0.02958  -0.0419   0.0589   1.0000
  11.000   1.3429   0.04122   0.03278  -0.0401   0.0560   1.0000
  11.250   1.3315   0.04479   0.03642  -0.0391   0.0539   1.0000
  11.500   1.3219   0.04839   0.04007  -0.0383   0.0521   1.0000
  11.750   1.3210   0.05130   0.04313  -0.0374   0.0500   1.0000
  12.000   1.3223   0.05400   0.04593  -0.0363   0.0475   1.0000
  12.250   1.3250   0.05665   0.04859  -0.0353   0.0447   1.0000
  12.500   1.3458   0.05825   0.05005  -0.0321   0.0413   1.0000
  12.750   1.3604   0.06054   0.05257  -0.0307   0.0403   1.0000
  13.000   1.3739   0.06329   0.05557  -0.0295   0.0395   1.0000
  13.250   1.3815   0.06670   0.05926  -0.0286   0.0390   1.0000
  13.500   1.3823   0.07059   0.06344  -0.0282   0.0388   1.0000
  13.750   1.3763   0.07492   0.06806  -0.0284   0.0384   1.0000
  14.000   1.3668   0.07960   0.07302  -0.0291   0.0382   1.0000
  14.250   1.3545   0.08472   0.07841  -0.0304   0.0381   1.0000
  14.500   1.3390   0.09032   0.08427  -0.0324   0.0380   1.0000
  14.750   1.3220   0.09638   0.09059  -0.0349   0.0381   1.0000
  15.000   1.3034   0.10303   0.09747  -0.0381   0.0385   1.0000
  15.250   1.2836   0.11019   0.10486  -0.0420   0.0389   1.0000
  15.500   1.2629   0.11802   0.11289  -0.0466   0.0393   1.0000
  15.750   1.2421   0.12640   0.12144  -0.0518   0.0398   1.0000
  16.000   1.2221   0.13523   0.13042  -0.0573   0.0405   1.0000
  16.250   1.2034   0.14434   0.13964  -0.0629   0.0411   1.0000
  16.500   1.1882   0.15323   0.14864  -0.0683   0.0418   1.0000
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