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USA 26 AIRFOIL (usa26-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: USA 26 AIRFOIL (usa26-il)
Reynolds number: 100,000
Max Cl/Cd: 52.3 at α=8°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-usa26-il-100000-n5.txt
Download as CSV file: xf-usa26-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: USA 26 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
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.3659   0.09269   0.08814  -0.0261   1.0000   0.0615
  -7.500  -0.3796   0.09092   0.08646  -0.0244   1.0000   0.0630
  -7.250  -0.3925   0.08883   0.08445  -0.0231   1.0000   0.0638
  -6.750  -0.4186   0.08366   0.07929  -0.0276   1.0000   0.0675
  -6.500  -0.3963   0.07801   0.07346  -0.0349   0.9942   0.0678
  -6.250  -0.3729   0.07237   0.06765  -0.0402   0.9877   0.0678
  -5.750  -0.3298   0.06014   0.05521  -0.0455   0.9764   0.0534
  -5.500  -0.3073   0.05593   0.05087  -0.0480   0.9691   0.0521
  -5.250  -0.2789   0.05088   0.04557  -0.0520   0.9628   0.0511
  -5.000  -0.2566   0.04555   0.03983  -0.0543   0.9541   0.0523
  -4.750  -0.2282   0.04084   0.03466  -0.0568   0.9488   0.0524
  -4.500  -0.2086   0.03748   0.03092  -0.0566   0.9397   0.0521
  -4.250  -0.1774   0.03415   0.02707  -0.0582   0.9343   0.0521
  -4.000  -0.1548   0.03176   0.02424  -0.0575   0.9245   0.0524
  -3.750  -0.1182   0.02989   0.02173  -0.0591   0.9184   0.0542
  -3.500  -0.0934   0.02826   0.01975  -0.0585   0.9076   0.0547
  -3.250  -0.0637   0.02643   0.01759  -0.0587   0.8987   0.0549
  -3.000  -0.0304   0.02475   0.01565  -0.0596   0.8909   0.0553
  -2.750  -0.0027   0.02343   0.01415  -0.0593   0.8806   0.0559
  -2.500   0.0316   0.02216   0.01273  -0.0602   0.8728   0.0568
  -2.250   0.0623   0.02116   0.01161  -0.0604   0.8622   0.0577
  -2.000   0.0921   0.02033   0.01071  -0.0604   0.8501   0.0597
  -1.750   0.1242   0.01959   0.00988  -0.0609   0.8374   0.0629
  -1.500   0.1581   0.01885   0.00906  -0.0617   0.8239   0.0650
  -1.250   0.1924   0.01816   0.00830  -0.0625   0.8087   0.0663
  -1.000   0.2268   0.01756   0.00761  -0.0633   0.7911   0.0679
  -0.750   0.2620   0.01683   0.00683  -0.0643   0.7710   0.0711
  -0.500   0.2948   0.01638   0.00628  -0.0649   0.7454   0.0755
  -0.250   0.3290   0.01603   0.00577  -0.0656   0.7164   0.0821
   0.250   0.3930   0.01513   0.00535  -0.0669   0.6521   0.2757
   0.500   0.4210   0.01506   0.00522  -0.0667   0.6215   0.3423
   0.750   0.4444   0.01468   0.00505  -0.0659   0.5959   0.4504
   1.000   0.5813   0.01425   0.00529  -0.0882   0.5582   1.0000
   1.250   0.6041   0.01450   0.00531  -0.0871   0.5422   1.0000
   1.500   0.6269   0.01474   0.00538  -0.0860   0.5284   1.0000
   1.750   0.6497   0.01499   0.00547  -0.0850   0.5160   1.0000
   2.000   0.6725   0.01525   0.00559  -0.0839   0.5049   1.0000
   2.250   0.6952   0.01553   0.00572  -0.0829   0.4946   1.0000
   2.500   0.7177   0.01577   0.00589  -0.0818   0.4844   1.0000
   2.750   0.7406   0.01605   0.00607  -0.0808   0.4761   1.0000
   3.000   0.7632   0.01631   0.00628  -0.0798   0.4676   1.0000
   3.250   0.7863   0.01660   0.00648  -0.0788   0.4608   1.0000
   3.500   0.8090   0.01687   0.00675  -0.0779   0.4534   1.0000
   3.750   0.8322   0.01718   0.00699  -0.0770   0.4475   1.0000
   4.000   0.8546   0.01746   0.00729  -0.0759   0.4405   1.0000
   4.250   0.8773   0.01777   0.00758  -0.0749   0.4343   1.0000
   4.500   0.8997   0.01808   0.00789  -0.0739   0.4279   1.0000
   4.750   0.9215   0.01837   0.00820  -0.0728   0.4208   1.0000
   5.000   0.9432   0.01868   0.00849  -0.0716   0.4140   1.0000
   5.250   0.9639   0.01896   0.00883  -0.0703   0.4061   1.0000
   5.500   0.9852   0.01927   0.00913  -0.0690   0.3994   1.0000
   5.750   1.0057   0.01957   0.00951  -0.0677   0.3918   1.0000
   6.000   1.0269   0.01989   0.00983  -0.0664   0.3855   1.0000
   6.250   1.0466   0.02020   0.01026  -0.0649   0.3779   1.0000
   6.500   1.0676   0.02053   0.01061  -0.0637   0.3719   1.0000
   6.750   1.0880   0.02089   0.01110  -0.0624   0.3658   1.0000
   7.000   1.1084   0.02125   0.01158  -0.0610   0.3599   1.0000
   7.250   1.1291   0.02162   0.01200  -0.0598   0.3543   1.0000
   7.500   1.1462   0.02194   0.01246  -0.0578   0.3450   1.0000
   7.750   1.1619   0.02222   0.01282  -0.0556   0.3341   1.0000
   8.000   1.1752   0.02247   0.01311  -0.0530   0.3206   1.0000
   8.250   1.1878   0.02274   0.01348  -0.0503   0.3060   1.0000
   8.500   1.2010   0.02308   0.01388  -0.0477   0.2924   1.0000
   8.750   1.2143   0.02345   0.01435  -0.0452   0.2794   1.0000
   9.000   1.2272   0.02385   0.01488  -0.0427   0.2646   1.0000
   9.250   1.2388   0.02430   0.01544  -0.0400   0.2444   1.0000
   9.500   1.2441   0.02488   0.01595  -0.0364   0.2147   1.0000
   9.750   1.2479   0.02566   0.01666  -0.0326   0.1913   1.0000
  10.000   1.2504   0.02666   0.01756  -0.0289   0.1723   1.0000
  10.250   1.2492   0.02800   0.01878  -0.0251   0.1513   1.0000
  10.500   1.2479   0.02949   0.02019  -0.0215   0.1263   1.0000
  10.750   1.2403   0.03147   0.02195  -0.0177   0.0786   1.0000
  11.000   1.2212   0.03434   0.02447  -0.0133   0.0464   1.0000
  11.250   1.2115   0.03678   0.02690  -0.0103   0.0346   1.0000
  11.500   1.2067   0.03904   0.02924  -0.0080   0.0311   1.0000
  11.750   1.1998   0.04168   0.03198  -0.0062   0.0285   1.0000
  12.000   1.1925   0.04457   0.03500  -0.0048   0.0270   1.0000
  12.250   1.1850   0.04776   0.03832  -0.0040   0.0261   1.0000
  12.500   1.1777   0.05118   0.04192  -0.0037   0.0256   1.0000
  12.750   1.1680   0.05518   0.04609  -0.0040   0.0248   1.0000
  13.000   1.1593   0.05933   0.05042  -0.0047   0.0244   1.0000
  13.250   1.1484   0.06401   0.05525  -0.0057   0.0239   1.0000
  13.500   1.1374   0.06886   0.06027  -0.0070   0.0236   1.0000
  13.750   1.1262   0.07383   0.06541  -0.0084   0.0230   1.0000
  14.000   1.1148   0.07894   0.07067  -0.0099   0.0227   1.0000
  14.250   1.1038   0.08405   0.07591  -0.0115   0.0222   1.0000
  14.500   1.0920   0.08940   0.08139  -0.0132   0.0217   1.0000
  14.750   1.0823   0.09449   0.08659  -0.0148   0.0214   1.0000
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