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GOE 178 AIRFOIL (goe178-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: GOE 178 AIRFOIL (goe178-il)
Reynolds number: 200,000
Max Cl/Cd: 76.49 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe178-il-200000-n5.txt
Download as CSV file: xf-goe178-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 178 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.3644   0.09043   0.08710  -0.0195   1.0000   0.0208
  -7.750  -0.3607   0.08719   0.08390  -0.0211   1.0000   0.0212
  -7.500  -0.3577   0.08421   0.08097  -0.0227   1.0000   0.0221
  -7.250  -0.3534   0.08060   0.07741  -0.0256   1.0000   0.0231
  -7.000  -0.3491   0.07659   0.07344  -0.0291   1.0000   0.0236
  -6.750  -0.3454   0.07254   0.06942  -0.0322   1.0000   0.0237
  -6.500  -0.3213   0.06586   0.06269  -0.0420   0.9925   0.0241
  -6.250  -0.2837   0.05494   0.05160  -0.0586   0.9819   0.0261
  -6.000  -0.2562   0.05365   0.05027  -0.0611   0.9740   0.0277
  -5.750  -0.2220   0.04782   0.04424  -0.0691   0.9639   0.0286
  -5.500  -0.1875   0.04147   0.03763  -0.0764   0.9523   0.0299
  -5.250  -0.1522   0.03356   0.02921  -0.0833   0.9401   0.0322
  -5.000  -0.1195   0.02569   0.02047  -0.0879   0.9271   0.0333
  -4.750  -0.0893   0.02226   0.01635  -0.0896   0.9107   0.0348
  -4.500  -0.0603   0.01973   0.01335  -0.0904   0.8914   0.0355
  -4.250  -0.0317   0.01816   0.01143  -0.0907   0.8686   0.0361
  -4.000  -0.0040   0.01701   0.00995  -0.0905   0.8439   0.0367
  -3.750   0.0227   0.01621   0.00887  -0.0900   0.8184   0.0377
  -3.500   0.0492   0.01561   0.00803  -0.0895   0.7923   0.0390
  -3.250   0.0760   0.01494   0.00710  -0.0891   0.7654   0.0397
  -3.000   0.1029   0.01434   0.00624  -0.0886   0.7369   0.0401
  -2.750   0.1298   0.01386   0.00554  -0.0882   0.7064   0.0406
  -2.500   0.1566   0.01349   0.00495  -0.0878   0.6747   0.0413
  -2.250   0.1836   0.01322   0.00444  -0.0875   0.6448   0.0421
  -2.000   0.2109   0.01301   0.00403  -0.0873   0.6182   0.0431
  -1.750   0.2382   0.01287   0.00369  -0.0871   0.5951   0.0441
  -1.500   0.2659   0.01273   0.00341  -0.0870   0.5751   0.0458
  -1.250   0.2937   0.01264   0.00322  -0.0869   0.5586   0.0484
  -1.000   0.3215   0.01258   0.00311  -0.0868   0.5451   0.0538
  -0.750   0.3494   0.01256   0.00305  -0.0868   0.5339   0.0673
  -0.500   0.3774   0.01256   0.00297  -0.0868   0.5238   0.0815
  -0.250   0.4054   0.01255   0.00291  -0.0868   0.5151   0.0936
   0.000   0.4332   0.01256   0.00286  -0.0867   0.5070   0.1040
   0.250   0.4613   0.01258   0.00285  -0.0868   0.4996   0.1131
   0.500   0.4891   0.01260   0.00285  -0.0868   0.4929   0.1268
   0.750   0.5171   0.01251   0.00291  -0.0869   0.4860   0.1780
   1.000   0.5448   0.01241   0.00296  -0.0870   0.4786   0.2518
   1.250   0.5717   0.01197   0.00309  -0.0871   0.4717   0.4667
   1.750   0.6212   0.01109   0.00317  -0.0853   0.4588   1.0000
   2.000   0.6491   0.01124   0.00325  -0.0852   0.4522   1.0000
   2.250   0.6768   0.01142   0.00335  -0.0852   0.4470   1.0000
   2.500   0.7047   0.01159   0.00347  -0.0852   0.4422   1.0000
   2.750   0.7326   0.01175   0.00360  -0.0852   0.4372   1.0000
   3.000   0.7602   0.01194   0.00376  -0.0851   0.4329   1.0000
   3.250   0.7878   0.01213   0.00392  -0.0851   0.4284   1.0000
   3.500   0.8154   0.01228   0.00409  -0.0850   0.4217   1.0000
   3.750   0.8426   0.01248   0.00424  -0.0849   0.4136   1.0000
   4.000   0.8698   0.01262   0.00440  -0.0848   0.4041   1.0000
   4.250   0.8970   0.01280   0.00458  -0.0847   0.3962   1.0000
   4.500   0.9243   0.01297   0.00480  -0.0846   0.3893   1.0000
   4.750   0.9514   0.01317   0.00502  -0.0845   0.3829   1.0000
   5.000   0.9786   0.01334   0.00526  -0.0844   0.3756   1.0000
   5.250   1.0054   0.01355   0.00552  -0.0843   0.3690   1.0000
   5.500   1.0322   0.01373   0.00575  -0.0841   0.3581   1.0000
   5.750   1.0584   0.01390   0.00594  -0.0839   0.3373   1.0000
   6.000   1.0839   0.01417   0.00615  -0.0836   0.3083   1.0000
   6.250   1.1083   0.01458   0.00647  -0.0832   0.2765   1.0000
   6.500   1.1310   0.01527   0.00694  -0.0827   0.2393   1.0000
   6.750   1.1535   0.01600   0.00754  -0.0821   0.2071   1.0000
   7.250   1.1845   0.01936   0.01001  -0.0797   0.0494   1.0000
   7.500   1.2058   0.02019   0.01087  -0.0789   0.0280   1.0000
   7.750   1.2257   0.02115   0.01178  -0.0779   0.0211   1.0000
   8.000   1.2458   0.02202   0.01277  -0.0770   0.0186   1.0000
   8.250   1.2647   0.02297   0.01388  -0.0759   0.0166   1.0000
   8.500   1.2816   0.02406   0.01513  -0.0746   0.0154   1.0000
   8.750   1.2956   0.02535   0.01661  -0.0729   0.0145   1.0000
   9.000   1.3051   0.02692   0.01835  -0.0708   0.0138   1.0000
   9.250   1.3089   0.02881   0.02041  -0.0681   0.0133   1.0000
   9.500   1.3146   0.03026   0.02198  -0.0656   0.0129   1.0000
   9.750   1.3193   0.03173   0.02358  -0.0631   0.0125   1.0000
  10.000   1.3230   0.03341   0.02539  -0.0610   0.0119   1.0000
  10.250   1.3251   0.03539   0.02749  -0.0591   0.0115   1.0000
  10.500   1.3261   0.03764   0.02987  -0.0575   0.0111   1.0000
  10.750   1.3267   0.04013   0.03248  -0.0564   0.0109   1.0000
  11.000   1.3276   0.04276   0.03523  -0.0555   0.0107   1.0000
  11.250   1.3287   0.04547   0.03805  -0.0547   0.0104   1.0000
  11.500   1.3299   0.04824   0.04097  -0.0540   0.0102   1.0000
  11.750   1.3315   0.05103   0.04387  -0.0534   0.0100   1.0000
  12.000   1.3332   0.05385   0.04680  -0.0528   0.0098   1.0000
  12.250   1.3349   0.05670   0.04976  -0.0522   0.0097   1.0000
  12.500   1.3366   0.05959   0.05276  -0.0516   0.0095   1.0000
  12.750   1.3381   0.06254   0.05582  -0.0510   0.0094   1.0000
  13.000   1.3390   0.06562   0.05900  -0.0504   0.0091   1.0000
  13.250   1.3395   0.06894   0.06242  -0.0491   0.0089   1.0000
  13.500   1.3361   0.07275   0.06643  -0.0494   0.0087   1.0000
  13.750   1.3312   0.07682   0.07073  -0.0506   0.0086   1.0000
  14.000   1.3257   0.08111   0.07523  -0.0517   0.0084   1.0000
  14.250   1.3187   0.08571   0.08005  -0.0530   0.0083   1.0000
  14.500   1.3108   0.09060   0.08515  -0.0545   0.0082   1.0000
  14.750   1.3017   0.09584   0.09059  -0.0564   0.0081   1.0000
  15.000   1.2914   0.10144   0.09640  -0.0585   0.0080   1.0000
  15.250   1.2802   0.10736   0.10253  -0.0610   0.0080   1.0000
  15.500   1.2681   0.11371   0.10907  -0.0640   0.0080   1.0000
  15.750   1.2556   0.12036   0.11591  -0.0674   0.0080   1.0000
  16.000   1.2423   0.12743   0.12317  -0.0712   0.0080   1.0000
  16.250   1.2286   0.13494   0.13085  -0.0755   0.0080   1.0000
  16.500   1.2149   0.14284   0.13893  -0.0803   0.0080   1.0000
  16.750   1.2011   0.15124   0.14749  -0.0855   0.0081   1.0000
  17.000   1.1868   0.16030   0.15671  -0.0913   0.0081   1.0000
  17.250   1.1725   0.16997   0.16651  -0.0976   0.0082   1.0000
  17.500   1.1576   0.18063   0.17729  -0.1044   0.0083   1.0000
  17.750   1.1437   0.19196   0.18870  -0.1115   0.0085   1.0000
  18.000   1.1328   0.20340   0.20018  -0.1181   0.0086   1.0000
  18.250   1.1278   0.21326   0.21003  -0.1234   0.0087   1.0000
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