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S3021-095-84 (s3021-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: S3021-095-84 (s3021-il)
Reynolds number: 200,000
Max Cl/Cd: 74.57 at α=6°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s3021-il-200000.txt
Download as CSV file: xf-s3021-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S3021-095-84                                    
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.3155   0.08651   0.08328  -0.0309   1.0000   0.0511
  -8.750  -0.3245   0.08283   0.07965  -0.0345   1.0000   0.0517
  -8.500  -0.3333   0.07889   0.07578  -0.0376   1.0000   0.0520
  -8.250  -0.3412   0.07494   0.07188  -0.0403   1.0000   0.0521
  -8.000  -0.3542   0.07102   0.06801  -0.0431   1.0000   0.0521
  -7.750  -0.4130   0.07822   0.07499  -0.0422   1.0000   0.0518
  -7.500  -0.4180   0.07412   0.07082  -0.0455   1.0000   0.0521
  -7.250  -0.4255   0.06819   0.06492  -0.0460   1.0000   0.0528
  -7.000  -0.4193   0.06565   0.06250  -0.0428   1.0000   0.0538
  -6.750  -0.4164   0.06362   0.06050  -0.0405   1.0000   0.0549
  -6.500  -0.4171   0.06133   0.05823  -0.0388   1.0000   0.0560
  -6.250  -0.4217   0.05909   0.05600  -0.0369   1.0000   0.0572
  -6.000  -0.4216   0.05639   0.05326  -0.0364   0.9989   0.0590
  -5.750  -0.3848   0.04781   0.04405  -0.0478   0.9897   0.0665
  -5.500  -0.3520   0.04457   0.04087  -0.0509   0.9848   0.0693
  -5.250  -0.2617   0.02284   0.01905  -0.0623   0.9625   0.0821
  -5.000  -0.2278   0.01882   0.01457  -0.0663   0.9571   0.0942
  -4.750  -0.1974   0.01712   0.01267  -0.0675   0.9467   0.1050
  -4.500  -0.2063   0.02323   0.01679  -0.0624   0.9575   0.0415
  -4.250  -0.1713   0.02143   0.01470  -0.0634   0.9485   0.0395
  -4.000  -0.1326   0.01884   0.01177  -0.0654   0.9435   0.0382
  -3.750  -0.0999   0.01722   0.00994  -0.0659   0.9333   0.0378
  -3.500  -0.0656   0.01589   0.00848  -0.0667   0.9246   0.0383
  -3.250  -0.0327   0.01484   0.00733  -0.0672   0.9153   0.0395
  -3.000  -0.0048   0.01387   0.00631  -0.0668   0.9031   0.0414
  -2.750   0.0223   0.01318   0.00561  -0.0664   0.8908   0.0481
  -2.500   0.0490   0.01255   0.00490  -0.0658   0.8786   0.0569
  -2.250   0.0713   0.01117   0.00429  -0.0648   0.8665   0.2342
  -2.000   0.0932   0.01035   0.00413  -0.0637   0.8547   0.4206
  -1.750   0.1094   0.00941   0.00411  -0.0609   0.8427   0.6659
  -1.500   0.1767   0.00890   0.00417  -0.0668   0.8347   0.9656
  -1.250   0.2466   0.00881   0.00380  -0.0753   0.8259   1.0000
  -1.000   0.2692   0.00885   0.00366  -0.0742   0.8131   1.0000
  -0.750   0.2919   0.00891   0.00356  -0.0731   0.8002   1.0000
  -0.500   0.3151   0.00899   0.00349  -0.0721   0.7878   1.0000
  -0.250   0.3386   0.00907   0.00344  -0.0711   0.7760   1.0000
   0.000   0.3623   0.00916   0.00339  -0.0702   0.7646   1.0000
   0.250   0.3864   0.00926   0.00335  -0.0692   0.7538   1.0000
   0.500   0.4103   0.00936   0.00335  -0.0683   0.7420   1.0000
   0.750   0.4343   0.00946   0.00337  -0.0675   0.7303   1.0000
   1.000   0.4586   0.00957   0.00339  -0.0666   0.7191   1.0000
   1.250   0.4831   0.00968   0.00340  -0.0658   0.7085   1.0000
   1.500   0.5077   0.00980   0.00343  -0.0650   0.6975   1.0000
   1.750   0.5320   0.00991   0.00351  -0.0642   0.6858   1.0000
   2.000   0.5565   0.01004   0.00358  -0.0634   0.6745   1.0000
   2.250   0.5812   0.01016   0.00365  -0.0627   0.6634   1.0000
   2.500   0.6061   0.01029   0.00370  -0.0619   0.6525   1.0000
   2.750   0.6306   0.01041   0.00381  -0.0611   0.6402   1.0000
   3.000   0.6552   0.01054   0.00392  -0.0604   0.6278   1.0000
   3.250   0.6798   0.01067   0.00402  -0.0596   0.6151   1.0000
   3.500   0.7045   0.01080   0.00413  -0.0589   0.6021   1.0000
   3.750   0.7291   0.01093   0.00426  -0.0581   0.5887   1.0000
   4.000   0.7537   0.01107   0.00439  -0.0573   0.5746   1.0000
   4.250   0.7782   0.01121   0.00452  -0.0566   0.5597   1.0000
   4.500   0.8025   0.01136   0.00466  -0.0558   0.5440   1.0000
   4.750   0.8268   0.01152   0.00484  -0.0550   0.5276   1.0000
   5.000   0.8508   0.01170   0.00499  -0.0542   0.5103   1.0000
   5.250   0.8746   0.01190   0.00519  -0.0533   0.4913   1.0000
   5.500   0.8981   0.01211   0.00540  -0.0525   0.4707   1.0000
   5.750   0.9212   0.01237   0.00565  -0.0515   0.4494   1.0000
   6.000   0.9440   0.01266   0.00592  -0.0506   0.4262   1.0000
   6.250   0.9664   0.01299   0.00623  -0.0496   0.4021   1.0000
   6.500   0.9882   0.01337   0.00657  -0.0486   0.3774   1.0000
   6.750   1.0094   0.01381   0.00697  -0.0475   0.3518   1.0000
   7.000   1.0298   0.01429   0.00739  -0.0463   0.3233   1.0000
   7.250   1.0495   0.01483   0.00784  -0.0451   0.2922   1.0000
   7.500   1.0686   0.01542   0.00834  -0.0438   0.2597   1.0000
   7.750   1.0869   0.01608   0.00891  -0.0425   0.2275   1.0000
   8.000   1.1056   0.01674   0.00951  -0.0413   0.2006   1.0000
   8.250   1.1232   0.01748   0.01016  -0.0399   0.1718   1.0000
   8.500   1.1400   0.01828   0.01086  -0.0385   0.1438   1.0000
   8.750   1.1556   0.01920   0.01166  -0.0370   0.1148   1.0000
   9.000   1.1640   0.02074   0.01286  -0.0346   0.0638   1.0000
   9.250   1.1641   0.02292   0.01476  -0.0310   0.0337   1.0000
   9.500   1.1732   0.02416   0.01609  -0.0285   0.0279   1.0000
   9.750   1.1724   0.02581   0.01780  -0.0248   0.0251   1.0000
  10.000   1.1780   0.02709   0.01922  -0.0220   0.0240   1.0000
  10.250   1.1820   0.02856   0.02082  -0.0194   0.0228   1.0000
  10.500   1.1857   0.03017   0.02254  -0.0171   0.0220   1.0000
  10.750   1.1890   0.03194   0.02440  -0.0150   0.0212   1.0000
  11.000   1.1921   0.03385   0.02641  -0.0132   0.0205   1.0000
  11.250   1.1959   0.03588   0.02852  -0.0117   0.0200   1.0000
  11.500   1.2008   0.03802   0.03075  -0.0102   0.0197   1.0000
  11.750   1.2067   0.04046   0.03329  -0.0088   0.0192   1.0000
  12.000   1.2163   0.04291   0.03586  -0.0075   0.0189   1.0000
  12.250   1.2266   0.04563   0.03874  -0.0064   0.0188   1.0000
  12.500   1.2339   0.04919   0.04254  -0.0052   0.0185   1.0000
  12.750   1.2328   0.05187   0.04544  -0.0044   0.0184   1.0000
  13.000   1.2312   0.05504   0.04883  -0.0038   0.0183   1.0000
  13.250   1.2251   0.05816   0.05219  -0.0037   0.0180   1.0000
  13.500   1.2179   0.06181   0.05609  -0.0039   0.0178   1.0000
  13.750   1.2084   0.06597   0.06048  -0.0046   0.0177   1.0000
  14.000   1.1977   0.07069   0.06542  -0.0056   0.0178   1.0000
  14.250   1.1839   0.07576   0.07072  -0.0073   0.0178   1.0000
  14.500   1.1690   0.08143   0.07660  -0.0094   0.0179   1.0000
  14.750   1.1524   0.08759   0.08297  -0.0122   0.0180   1.0000
  15.000   1.1349   0.09430   0.08987  -0.0156   0.0181   1.0000
  15.250   1.1170   0.10150   0.09724  -0.0195   0.0182   1.0000
  15.500   1.0977   0.10944   0.10535  -0.0241   0.0184   1.0000
  15.750   1.0780   0.11800   0.11407  -0.0292   0.0185   1.0000
  16.000   1.0656   0.12542   0.12165  -0.0341   0.0186   1.0000
  16.250   1.0499   0.13426   0.13063  -0.0403   0.0188   1.0000
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