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SD8000-089-88 (sd8000-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: SD8000-089-88 (sd8000-il)
Reynolds number: 50,000
Max Cl/Cd: 33.57 at α=5.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-sd8000-il-50000.txt
Download as CSV file: xf-sd8000-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: SD8000-089-88                                   
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.4577   0.09509   0.08820  -0.0044   1.0000   0.3126
  -7.750  -0.4564   0.09224   0.08540  -0.0038   1.0000   0.3279
  -7.500  -0.4580   0.08952   0.08274  -0.0031   1.0000   0.3434
  -7.250  -0.4544   0.08636   0.07964  -0.0021   1.0000   0.3582
  -7.000  -0.4590   0.08388   0.07725  -0.0008   1.0000   0.3737
  -6.750  -0.4300   0.07917   0.07248   0.0011   1.0000   0.3998
  -6.500  -0.5206   0.05653   0.04937  -0.0392   1.0000   0.1511
  -6.250  -0.5117   0.05195   0.04461  -0.0393   1.0000   0.1498
  -6.000  -0.5012   0.04730   0.03967  -0.0394   1.0000   0.1478
  -5.750  -0.4888   0.04277   0.03470  -0.0395   1.0000   0.1468
  -5.500  -0.4741   0.03879   0.02998  -0.0394   1.0000   0.1509
  -5.250  -0.4561   0.03590   0.02697  -0.0384   1.0000   0.1572
  -5.000  -0.4362   0.03302   0.02342  -0.0378   1.0000   0.1657
  -4.750  -0.4158   0.03083   0.02112  -0.0367   1.0000   0.1772
  -4.500  -0.3943   0.02879   0.01884  -0.0357   1.0000   0.1911
  -4.250  -0.3718   0.02695   0.01673  -0.0348   1.0000   0.2075
  -4.000  -0.3496   0.02539   0.01509  -0.0337   1.0000   0.2285
  -3.750  -0.3266   0.02396   0.01357  -0.0327   1.0000   0.2529
  -3.500  -0.3043   0.02271   0.01236  -0.0315   1.0000   0.2860
  -3.250  -0.2817   0.02150   0.01128  -0.0303   1.0000   0.3287
  -3.000  -0.2603   0.02032   0.01045  -0.0288   1.0000   0.3903
  -2.750  -0.2407   0.01910   0.00987  -0.0267   1.0000   0.4900
  -2.500  -0.2288   0.01805   0.00968  -0.0220   1.0000   0.6333
  -2.250  -0.2255   0.01743   0.00966  -0.0144   1.0000   0.7801
  -2.000  -0.1278   0.01708   0.00899  -0.0243   1.0000   1.0000
  -1.750  -0.1254   0.01677   0.00839  -0.0221   1.0000   1.0000
  -1.500  -0.1099   0.01672   0.00801  -0.0212   1.0000   1.0000
  -1.250  -0.0913   0.01677   0.00778  -0.0205   1.0000   1.0000
  -1.000  -0.0718   0.01689   0.00765  -0.0200   1.0000   1.0000
  -0.750  -0.0519   0.01705   0.00760  -0.0194   1.0000   1.0000
  -0.500  -0.0319   0.01726   0.00761  -0.0189   1.0000   1.0000
  -0.250  -0.0119   0.01751   0.00771  -0.0184   1.0000   1.0000
   0.000   0.0080   0.01781   0.00787  -0.0179   1.0000   1.0000
   0.250   0.0276   0.01815   0.00809  -0.0175   1.0000   1.0000
   0.500   0.0470   0.01855   0.00838  -0.0171   1.0000   1.0000
   0.750   0.0660   0.01900   0.00875  -0.0168   1.0000   1.0000
   1.000   0.0846   0.01950   0.00919  -0.0165   1.0000   1.0000
   1.250   0.1028   0.02007   0.00972  -0.0163   1.0000   1.0000
   1.500   0.1204   0.02071   0.01032  -0.0162   1.0000   1.0000
   1.750   0.1375   0.02143   0.01102  -0.0162   1.0000   1.0000
   2.000   0.1818   0.02268   0.01229  -0.0213   0.9866   1.0000
   2.250   0.2476   0.02407   0.01377  -0.0298   0.9605   1.0000
   2.500   0.3097   0.02509   0.01491  -0.0370   0.9326   1.0000
   2.750   0.3700   0.02576   0.01575  -0.0431   0.9034   1.0000
   3.000   0.4300   0.02603   0.01621  -0.0484   0.8733   1.0000
   3.250   0.4937   0.02581   0.01626  -0.0533   0.8426   1.0000
   3.500   0.5523   0.02510   0.01579  -0.0561   0.8115   1.0000
   3.750   0.5999   0.02422   0.01511  -0.0564   0.7784   1.0000
   4.000   0.6376   0.02342   0.01449  -0.0550   0.7414   1.0000
   4.250   0.6718   0.02265   0.01379  -0.0527   0.7014   1.0000
   4.500   0.7007   0.02220   0.01331  -0.0498   0.6562   1.0000
   4.750   0.7264   0.02210   0.01311  -0.0469   0.6069   1.0000
   5.000   0.7497   0.02239   0.01319  -0.0441   0.5553   1.0000
   5.250   0.7718   0.02299   0.01357  -0.0417   0.5039   1.0000
   5.500   0.7940   0.02381   0.01414  -0.0396   0.4562   1.0000
   5.750   0.8157   0.02484   0.01494  -0.0377   0.4118   1.0000
   6.000   0.8370   0.02605   0.01605  -0.0361   0.3718   1.0000
   6.250   0.8601   0.02735   0.01712  -0.0348   0.3377   1.0000
   6.500   0.8817   0.02878   0.01855  -0.0335   0.3065   1.0000
   6.750   0.9043   0.03033   0.02001  -0.0323   0.2795   1.0000
   7.000   0.9246   0.03201   0.02186  -0.0310   0.2545   1.0000
   7.250   0.9468   0.03392   0.02374  -0.0299   0.2336   1.0000
   7.500   0.9658   0.03598   0.02606  -0.0286   0.2138   1.0000
   7.750   0.9855   0.03819   0.02844  -0.0273   0.1966   1.0000
   8.000   1.0041   0.04056   0.03096  -0.0260   0.1810   1.0000
   8.250   1.0193   0.04326   0.03394  -0.0245   0.1674   1.0000
   8.500   1.0303   0.04662   0.03771  -0.0229   0.1572   1.0000
   8.750   1.0442   0.04966   0.04091  -0.0215   0.1471   1.0000
   9.000   1.0472   0.05352   0.04528  -0.0197   0.1405   1.0000
   9.250   1.0593   0.05728   0.04913  -0.0186   0.1345   1.0000
   9.500   1.0480   0.06240   0.05481  -0.0168   0.1330   1.0000
   9.750   1.0321   0.06772   0.06053  -0.0156   0.1324   1.0000
  10.000   1.0128   0.07321   0.06628  -0.0149   0.1329   1.0000
  10.250   0.9909   0.07866   0.07187  -0.0146   0.1338   1.0000
  10.500   0.9715   0.08430   0.07757  -0.0150   0.1348   1.0000
  10.750   0.9551   0.09052   0.08382  -0.0167   0.1356   1.0000
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