Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

S3025 9.38% (s3025-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: S3025 9.38% (s3025-il)
Reynolds number: 200,000
Max Cl/Cd: 79.99 at α=6°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s3025-il-200000.txt
Download as CSV file: xf-s3025-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S3025 9.38%                                     
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.3341   0.09136   0.08795  -0.0334   1.0000   0.0394
  -8.000  -0.3401   0.08874   0.08541  -0.0351   1.0000   0.0418
  -7.750  -0.3450   0.08616   0.08291  -0.0352   1.0000   0.0420
  -7.500  -0.2902   0.07064   0.06778  -0.0342   1.0000   0.0454
  -7.250  -0.3033   0.06911   0.06633  -0.0312   1.0000   0.0457
  -7.000  -0.3242   0.06826   0.06559  -0.0277   0.9994   0.0458
  -6.750  -0.3075   0.06351   0.06083  -0.0321   0.9942   0.0476
  -6.500  -0.2900   0.05785   0.05515  -0.0398   0.9869   0.0498
  -6.250  -0.3697   0.06831   0.06539  -0.0397   0.9941   0.0463
  -6.000  -0.3386   0.06353   0.06055  -0.0468   0.9876   0.0491
  -5.750  -0.2869   0.05593   0.05227  -0.0648   0.9768   0.0553
  -5.500  -0.2642   0.04913   0.04561  -0.0684   0.9730   0.0574
  -5.250  -0.2365   0.04625   0.04270  -0.0708   0.9651   0.0601
  -5.000  -0.1952   0.04057   0.03637  -0.0786   0.9592   0.0698
  -4.750  -0.1678   0.03759   0.03347  -0.0802   0.9511   0.0725
  -4.500  -0.1289   0.03395   0.02935  -0.0846   0.9461   0.0842
  -4.250  -0.0918   0.02568   0.02002  -0.0850   0.9387   0.0412
  -4.000  -0.0541   0.02186   0.01537  -0.0858   0.9330   0.0326
  -3.750  -0.0204   0.01923   0.01237  -0.0867   0.9261   0.0318
  -3.500   0.0138   0.01755   0.01036  -0.0876   0.9188   0.0340
  -3.250   0.0455   0.01597   0.00868  -0.0880   0.9104   0.0353
  -3.000   0.0785   0.01476   0.00741  -0.0885   0.9027   0.0371
  -2.750   0.1069   0.01391   0.00650  -0.0882   0.8919   0.0400
  -2.500   0.1356   0.01304   0.00556  -0.0880   0.8819   0.0465
  -2.250   0.1633   0.01171   0.00465  -0.0877   0.8726   0.1428
  -2.000   0.1868   0.01086   0.00446  -0.0872   0.8606   0.3291
  -1.750   0.2050   0.00979   0.00446  -0.0852   0.8492   0.6123
  -1.500   0.2418   0.00900   0.00439  -0.0851   0.8415   0.9258
  -1.250   0.3081   0.00885   0.00400  -0.0928   0.8325   1.0000
  -1.000   0.3320   0.00892   0.00386  -0.0919   0.8207   1.0000
  -0.750   0.3563   0.00899   0.00375  -0.0910   0.8094   1.0000
  -0.500   0.3812   0.00908   0.00364  -0.0902   0.7990   1.0000
  -0.250   0.4051   0.00917   0.00360  -0.0893   0.7872   1.0000
   0.000   0.4295   0.00928   0.00358  -0.0885   0.7759   1.0000
   0.250   0.4544   0.00939   0.00355  -0.0877   0.7653   1.0000
   0.500   0.4798   0.00950   0.00352  -0.0870   0.7553   1.0000
   0.750   0.5044   0.00961   0.00354  -0.0863   0.7438   1.0000
   1.000   0.5294   0.00973   0.00358  -0.0856   0.7329   1.0000
   1.250   0.5549   0.00986   0.00360  -0.0849   0.7226   1.0000
   1.500   0.5806   0.00998   0.00363  -0.0843   0.7122   1.0000
   1.750   0.6057   0.01010   0.00370  -0.0837   0.7008   1.0000
   2.000   0.6311   0.01023   0.00377  -0.0831   0.6899   1.0000
   2.250   0.6570   0.01037   0.00383  -0.0826   0.6797   1.0000
   2.500   0.6826   0.01049   0.00392  -0.0820   0.6686   1.0000
   2.750   0.7079   0.01062   0.00403  -0.0814   0.6569   1.0000
   3.000   0.7334   0.01076   0.00413  -0.0808   0.6454   1.0000
   3.250   0.7590   0.01090   0.00423  -0.0802   0.6339   1.0000
   3.500   0.7846   0.01104   0.00435  -0.0797   0.6221   1.0000
   3.750   0.8099   0.01118   0.00446  -0.0791   0.6094   1.0000
   4.000   0.8349   0.01131   0.00459  -0.0784   0.5957   1.0000
   4.250   0.8598   0.01146   0.00473  -0.0778   0.5817   1.0000
   4.500   0.8846   0.01161   0.00489  -0.0771   0.5670   1.0000
   4.750   0.9093   0.01178   0.00505  -0.0764   0.5518   1.0000
   5.000   0.9337   0.01196   0.00521  -0.0756   0.5359   1.0000
   5.250   0.9577   0.01214   0.00542  -0.0749   0.5181   1.0000
   5.500   0.9815   0.01234   0.00565  -0.0740   0.4995   1.0000
   5.750   1.0049   0.01259   0.00587  -0.0731   0.4800   1.0000
   6.000   1.0279   0.01285   0.00613  -0.0722   0.4586   1.0000
   6.250   1.0503   0.01316   0.00643  -0.0712   0.4368   1.0000
   6.500   1.0724   0.01350   0.00676  -0.0702   0.4133   1.0000
   6.750   1.0937   0.01391   0.00712  -0.0691   0.3897   1.0000
   7.000   1.1144   0.01436   0.00753  -0.0679   0.3645   1.0000
   7.250   1.1342   0.01485   0.00798  -0.0666   0.3368   1.0000
   7.500   1.1529   0.01542   0.00847  -0.0652   0.3076   1.0000
   7.750   1.1707   0.01604   0.00900  -0.0637   0.2781   1.0000
   8.000   1.1881   0.01671   0.00958  -0.0622   0.2491   1.0000
   8.250   1.2053   0.01740   0.01021  -0.0607   0.2219   1.0000
   8.500   1.2222   0.01812   0.01090  -0.0592   0.1960   1.0000
   8.750   1.2378   0.01891   0.01162  -0.0576   0.1697   1.0000
   9.000   1.2523   0.01977   0.01241  -0.0558   0.1437   1.0000
   9.250   1.2645   0.02077   0.01330  -0.0538   0.1155   1.0000
   9.500   1.2694   0.02226   0.01451  -0.0509   0.0752   1.0000
   9.750   1.2657   0.02420   0.01621  -0.0466   0.0458   1.0000
  10.000   1.2660   0.02587   0.01790  -0.0430   0.0375   1.0000
  10.250   1.2655   0.02762   0.01970  -0.0398   0.0337   1.0000
  10.500   1.2660   0.02941   0.02161  -0.0369   0.0316   1.0000
  10.750   1.2693   0.03110   0.02344  -0.0346   0.0300   1.0000
  11.000   1.2728   0.03288   0.02532  -0.0327   0.0283   1.0000
  11.250   1.2747   0.03490   0.02742  -0.0310   0.0269   1.0000
  11.500   1.2745   0.03728   0.02985  -0.0293   0.0258   1.0000
  11.750   1.2753   0.03991   0.03255  -0.0276   0.0248   1.0000
  12.000   1.2824   0.04194   0.03472  -0.0264   0.0243   1.0000
  12.250   1.2899   0.04410   0.03703  -0.0252   0.0237   1.0000
  12.500   1.2979   0.04637   0.03946  -0.0240   0.0232   1.0000
  12.750   1.3056   0.04879   0.04207  -0.0230   0.0227   1.0000
  13.000   1.3121   0.05147   0.04495  -0.0220   0.0224   1.0000
  13.250   1.3161   0.05442   0.04812  -0.0211   0.0220   1.0000
  13.500   1.3169   0.05761   0.05152  -0.0205   0.0217   1.0000
  13.750   1.3154   0.06076   0.05484  -0.0203   0.0211   1.0000
  14.000   1.3119   0.06422   0.05848  -0.0204   0.0206   1.0000
  14.250   1.3058   0.06835   0.06285  -0.0207   0.0206   1.0000
  14.500   1.2988   0.07242   0.06710  -0.0214   0.0202   1.0000
  14.750   1.2896   0.07704   0.07190  -0.0224   0.0199   1.0000
  15.000   1.2758   0.08251   0.07763  -0.0241   0.0200   1.0000
  15.250   1.2588   0.08877   0.08416  -0.0265   0.0202   1.0000
  15.500   1.2406   0.09559   0.09123  -0.0296   0.0204   1.0000
  15.750   1.2194   0.10331   0.09920  -0.0337   0.0205   1.0000
  16.000   1.1921   0.11289   0.10906  -0.0395   0.0209   1.0000
  16.250   1.1643   0.12341   0.11981  -0.0463   0.0213   1.0000
<< Back to S3025 9.38% (s3025-il)

Polar data table (+)

Polar graphs


<< Back to S3025 9.38% (s3025-il)