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GOE 257 AIRFOIL (goe257-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 257 AIRFOIL (goe257-il)
Reynolds number: 100,000
Max Cl/Cd: 57.52 at α=6.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe257-il-100000-n5.txt
Download as CSV file: xf-goe257-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 257 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.3806   0.09753   0.09287  -0.0193   1.0000   0.0387
  -7.750  -0.3786   0.09441   0.08980  -0.0207   1.0000   0.0398
  -7.500  -0.3754   0.09115   0.08659  -0.0231   1.0000   0.0411
  -7.250  -0.3689   0.08761   0.08309  -0.0280   1.0000   0.0430
  -7.000  -0.3546   0.08388   0.07931  -0.0391   1.0000   0.0445
  -6.750  -0.3445   0.07906   0.07448  -0.0429   1.0000   0.0452
  -6.500  -0.3435   0.07587   0.07143  -0.0368   1.0000   0.0475
  -6.250  -0.3342   0.07289   0.06845  -0.0373   1.0000   0.0504
  -6.000  -0.3217   0.06944   0.06496  -0.0402   1.0000   0.0537
  -5.500  -0.2905   0.06139   0.05672  -0.0473   0.9997   0.0592
  -5.250  -0.2625   0.05771   0.05302  -0.0503   0.9918   0.0639
  -5.000  -0.2213   0.05284   0.04786  -0.0582   0.9831   0.0742
  -4.750  -0.1739   0.04936   0.04379  -0.0659   0.9735   0.0863
  -4.500  -0.1457   0.04487   0.03940  -0.0683   0.9620   0.0894
  -4.000  -0.0576   0.03504   0.02832  -0.0761   0.9350   0.0556
  -3.750  -0.0240   0.03188   0.02485  -0.0780   0.9172   0.0528
  -3.500   0.0097   0.02951   0.02202  -0.0794   0.8993   0.0535
  -3.250   0.0417   0.02745   0.01952  -0.0802   0.8819   0.0535
  -3.000   0.0725   0.02556   0.01724  -0.0806   0.8645   0.0520
  -2.750   0.1024   0.02398   0.01526  -0.0806   0.8471   0.0511
  -2.500   0.1316   0.02266   0.01358  -0.0805   0.8299   0.0506
  -2.250   0.1603   0.02156   0.01214  -0.0803   0.8140   0.0504
  -2.000   0.1884   0.02077   0.01110  -0.0801   0.7993   0.0526
  -1.750   0.2165   0.02003   0.01012  -0.0798   0.7860   0.0541
  -1.500   0.2445   0.01927   0.00916  -0.0794   0.7738   0.0539
  -1.250   0.2722   0.01863   0.00837  -0.0791   0.7622   0.0538
  -1.000   0.2999   0.01808   0.00772  -0.0789   0.7508   0.0539
  -0.750   0.3274   0.01762   0.00718  -0.0787   0.7404   0.0541
  -0.500   0.3548   0.01726   0.00672  -0.0784   0.7310   0.0546
  -0.250   0.3825   0.01699   0.00637  -0.0783   0.7209   0.0553
   0.000   0.4103   0.01682   0.00608  -0.0782   0.7114   0.0563
   0.500   0.4660   0.01659   0.00567  -0.0780   0.6922   0.0618
   0.750   0.4943   0.01658   0.00558  -0.0780   0.6831   0.0700
   1.000   0.5227   0.01654   0.00553  -0.0781   0.6742   0.0819
   1.250   0.5479   0.01426   0.00548  -0.0777   0.6650   1.0000
   1.500   0.5757   0.01445   0.00547  -0.0775   0.6553   1.0000
   1.750   0.6033   0.01463   0.00551  -0.0774   0.6441   1.0000
   2.000   0.6308   0.01480   0.00557  -0.0773   0.6319   1.0000
   2.250   0.6583   0.01498   0.00565  -0.0772   0.6200   1.0000
   2.500   0.6857   0.01515   0.00575  -0.0771   0.6084   1.0000
   2.750   0.7130   0.01532   0.00584  -0.0770   0.5970   1.0000
   3.000   0.7403   0.01549   0.00597  -0.0769   0.5846   1.0000
   3.250   0.7675   0.01566   0.00614  -0.0768   0.5718   1.0000
   3.500   0.7946   0.01583   0.00630  -0.0767   0.5583   1.0000
   3.750   0.8217   0.01601   0.00647  -0.0766   0.5454   1.0000
   4.000   0.8488   0.01621   0.00671  -0.0765   0.5339   1.0000
   4.250   0.8757   0.01643   0.00693  -0.0764   0.5231   1.0000
   4.500   0.9026   0.01665   0.00719  -0.0763   0.5113   1.0000
   4.750   0.9293   0.01689   0.00747  -0.0762   0.4989   1.0000
   5.000   0.9559   0.01715   0.00780  -0.0760   0.4863   1.0000
   5.250   0.9821   0.01742   0.00812  -0.0758   0.4731   1.0000
   5.500   1.0080   0.01772   0.00845  -0.0755   0.4582   1.0000
   5.750   1.0333   0.01805   0.00883  -0.0751   0.4410   1.0000
   6.000   1.0582   0.01843   0.00921  -0.0747   0.4225   1.0000
   6.250   1.0826   0.01882   0.00967  -0.0742   0.3992   1.0000
   6.500   1.1055   0.01928   0.01009  -0.0736   0.3638   1.0000
   6.750   1.1278   0.01982   0.01058  -0.0729   0.3187   1.0000
   7.000   1.1491   0.02052   0.01115  -0.0722   0.2790   1.0000
   7.250   1.1690   0.02142   0.01191  -0.0713   0.2470   1.0000
   7.500   1.1855   0.02272   0.01294  -0.0701   0.2019   1.0000
   7.750   1.2026   0.02398   0.01403  -0.0689   0.1366   1.0000
   8.000   1.2056   0.02680   0.01615  -0.0663   0.0517   1.0000
   8.250   1.2188   0.02838   0.01777  -0.0644   0.0351   1.0000
   8.500   1.2328   0.02975   0.01924  -0.0627   0.0290   1.0000
   8.750   1.2449   0.03121   0.02084  -0.0608   0.0265   1.0000
   9.000   1.2549   0.03271   0.02253  -0.0586   0.0247   1.0000
   9.250   1.2617   0.03431   0.02430  -0.0562   0.0229   1.0000
   9.500   1.2619   0.03618   0.02630  -0.0531   0.0215   1.0000
   9.750   1.2576   0.03832   0.02858  -0.0497   0.0207   1.0000
  10.000   1.2566   0.04046   0.03096  -0.0472   0.0201   1.0000
  10.250   1.2547   0.04289   0.03358  -0.0451   0.0197   1.0000
  10.500   1.2533   0.04550   0.03636  -0.0435   0.0194   1.0000
  10.750   1.2528   0.04819   0.03920  -0.0421   0.0190   1.0000
  11.000   1.2541   0.05085   0.04200  -0.0408   0.0187   1.0000
  11.250   1.2577   0.05339   0.04468  -0.0394   0.0183   1.0000
  11.500   1.2635   0.05584   0.04725  -0.0380   0.0179   1.0000
  11.750   1.2695   0.05835   0.04992  -0.0368   0.0172   1.0000
  12.000   1.2744   0.06104   0.05277  -0.0359   0.0165   1.0000
  12.250   1.2775   0.06396   0.05587  -0.0351   0.0159   1.0000
  12.500   1.2792   0.06711   0.05919  -0.0345   0.0154   1.0000
  12.750   1.2801   0.07048   0.06279  -0.0340   0.0151   1.0000
  13.000   1.2793   0.07417   0.06671  -0.0336   0.0149   1.0000
  13.250   1.2757   0.07824   0.07101  -0.0336   0.0148   1.0000
  13.500   1.2692   0.08268   0.07569  -0.0340   0.0147   1.0000
  13.750   1.2603   0.08750   0.08076  -0.0349   0.0146   1.0000
  14.000   1.2494   0.09272   0.08622  -0.0363   0.0146   1.0000
  14.250   1.2366   0.09832   0.09207  -0.0382   0.0146   1.0000
  14.500   1.2227   0.10439   0.09837  -0.0408   0.0147   1.0000
  14.750   1.2080   0.11098   0.10519  -0.0440   0.0147   1.0000
  15.000   1.1925   0.11813   0.11257  -0.0479   0.0148   1.0000
  15.250   1.1762   0.12598   0.12064  -0.0525   0.0149   1.0000
  15.500   1.1587   0.13471   0.12958  -0.0580   0.0150   1.0000
  15.750   1.1398   0.14466   0.13973  -0.0646   0.0153   1.0000
  16.000   1.1185   0.15646   0.15169  -0.0725   0.0156   1.0000
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