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

WB-135/35 13.5% smoothed (wb13535sm-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: WB-135/35 13.5% smoothed (wb13535sm-il)
Reynolds number: 100,000
Max Cl/Cd: 51.77 at α=6°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-wb13535sm-il-100000.txt
Download as CSV file: xf-wb13535sm-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: WB-135/35  13.5%  smoothed                      
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.3966   0.09613   0.09142  -0.0544   1.0000   0.0789
 -10.250  -0.4296   0.08380   0.07922  -0.0590   1.0000   0.0677
 -10.000  -0.4391   0.07880   0.07427  -0.0597   1.0000   0.0657
  -9.750  -0.4585   0.07336   0.06894  -0.0607   1.0000   0.0642
  -9.500  -0.5050   0.06586   0.06160  -0.0634   1.0000   0.0619
  -9.250  -0.6355   0.05884   0.05416  -0.0625   1.0000   0.0552
  -9.000  -0.6555   0.05599   0.05122  -0.0595   1.0000   0.0549
  -8.750  -0.6711   0.05303   0.04814  -0.0568   1.0000   0.0545
  -8.500  -0.6834   0.05002   0.04490  -0.0544   1.0000   0.0543
  -8.250  -0.6909   0.04702   0.04158  -0.0523   1.0000   0.0543
  -8.000  -0.6819   0.04346   0.03742  -0.0530   0.9966   0.0549
  -7.750  -0.6565   0.03996   0.03327  -0.0554   0.9899   0.0554
  -7.500  -0.6296   0.03597   0.02884  -0.0574   0.9844   0.0562
  -7.250  -0.6023   0.03319   0.02583  -0.0585   0.9787   0.0575
  -7.000  -0.5713   0.03123   0.02368  -0.0599   0.9732   0.0593
  -6.750  -0.5398   0.02977   0.02201  -0.0612   0.9675   0.0636
  -6.500  -0.5106   0.02832   0.02034  -0.0618   0.9610   0.0678
  -6.250  -0.4761   0.02684   0.01893  -0.0636   0.9564   0.0741
  -6.000  -0.4552   0.02577   0.01781  -0.0628   0.9491   0.0820
  -5.750  -0.4242   0.02462   0.01672  -0.0639   0.9437   0.1028
  -5.500  -0.4010   0.02386   0.01641  -0.0637   0.9368   0.1918
  -5.250  -0.3712   0.02459   0.01699  -0.0644   0.9299   0.2358
  -5.000  -0.3409   0.02519   0.01750  -0.0651   0.9244   0.2595
  -4.750  -0.3187   0.02568   0.01789  -0.0644   0.9170   0.2795
  -4.500  -0.2824   0.02643   0.01875  -0.0660   0.9124   0.3044
  -4.250  -0.2645   0.02663   0.01892  -0.0645   0.9052   0.3176
  -4.000  -0.2341   0.02638   0.01852  -0.0653   0.9000   0.3284
  -3.750  -0.1948   0.02608   0.01800  -0.0676   0.8965   0.3410
  -3.500  -0.1818   0.02609   0.01800  -0.0653   0.8886   0.3483
  -3.250  -0.1492   0.02588   0.01768  -0.0664   0.8841   0.3599
  -3.000  -0.1147   0.02570   0.01737  -0.0678   0.8800   0.3731
  -2.750  -0.1006   0.02581   0.01744  -0.0658   0.8724   0.3831
  -2.500  -0.0661   0.02566   0.01725  -0.0671   0.8682   0.3976
  -2.250  -0.0423   0.02572   0.01729  -0.0666   0.8625   0.4114
  -2.000  -0.0204   0.02579   0.01736  -0.0659   0.8561   0.4257
  -1.750   0.0177   0.02564   0.01718  -0.0677   0.8522   0.4459
  -1.500   0.0320   0.02590   0.01745  -0.0656   0.8442   0.4613
  -1.250   0.0760   0.02545   0.01706  -0.0680   0.8378   0.4847
  -1.000   0.1042   0.02522   0.01684  -0.0677   0.8271   0.5065
  -0.750   0.1688   0.02414   0.01579  -0.0729   0.8217   0.5402
  -0.500   0.1891   0.02403   0.01578  -0.0713   0.8110   0.5618
  -0.250   0.2366   0.02333   0.01516  -0.0740   0.8071   0.5951
   0.000   0.2532   0.02344   0.01538  -0.0720   0.7975   0.6220
   0.250   0.2980   0.02270   0.01481  -0.0743   0.7930   0.6656
   0.750   0.4684   0.02061   0.01362  -0.0951   0.7834   1.0000
   1.000   0.5066   0.02027   0.01308  -0.0966   0.7773   1.0000
   1.250   0.5258   0.02051   0.01321  -0.0950   0.7671   1.0000
   1.500   0.5663   0.02002   0.01260  -0.0964   0.7611   1.0000
   1.750   0.5849   0.02022   0.01274  -0.0945   0.7499   1.0000
   2.000   0.6143   0.02008   0.01253  -0.0942   0.7411   1.0000
   2.250   0.6458   0.01981   0.01220  -0.0941   0.7321   1.0000
   2.500   0.6686   0.01982   0.01218  -0.0927   0.7203   1.0000
   2.750   0.6968   0.01964   0.01195  -0.0920   0.7093   1.0000
   3.000   0.7331   0.01916   0.01140  -0.0925   0.6998   1.0000
   3.250   0.7566   0.01909   0.01132  -0.0911   0.6860   1.0000
   3.500   0.7821   0.01894   0.01114  -0.0900   0.6716   1.0000
   3.750   0.8087   0.01873   0.01090  -0.0890   0.6562   1.0000
   4.000   0.8361   0.01849   0.01060  -0.0881   0.6397   1.0000
   4.250   0.8565   0.01847   0.01057  -0.0862   0.6192   1.0000
   4.500   0.8805   0.01836   0.01040  -0.0848   0.5985   1.0000
   4.750   0.9052   0.01830   0.01025  -0.0836   0.5774   1.0000
   5.000   0.9258   0.01842   0.01031  -0.0818   0.5544   1.0000
   5.250   0.9504   0.01853   0.01029  -0.0808   0.5347   1.0000
   5.500   0.9702   0.01886   0.01058  -0.0791   0.5145   1.0000
   5.750   0.9921   0.01919   0.01085  -0.0779   0.4969   1.0000
   6.000   1.0147   0.01960   0.01118  -0.0768   0.4814   1.0000
   6.250   1.0373   0.02006   0.01159  -0.0758   0.4674   1.0000
   6.500   1.0606   0.02058   0.01208  -0.0750   0.4551   1.0000
   6.750   1.0856   0.02112   0.01257  -0.0745   0.4441   1.0000
   7.000   1.1087   0.02172   0.01318  -0.0737   0.4333   1.0000
   7.250   1.1290   0.02229   0.01378  -0.0724   0.4208   1.0000
   7.500   1.1479   0.02278   0.01426  -0.0708   0.4062   1.0000
   7.750   1.1658   0.02328   0.01474  -0.0691   0.3914   1.0000
   8.000   1.1851   0.02387   0.01535  -0.0677   0.3795   1.0000
   8.250   1.2023   0.02440   0.01589  -0.0659   0.3660   1.0000
   8.500   1.2221   0.02497   0.01646  -0.0646   0.3543   1.0000
   8.750   1.2389   0.02550   0.01705  -0.0628   0.3425   1.0000
   9.000   1.2492   0.02596   0.01760  -0.0600   0.3288   1.0000
   9.250   1.2581   0.02642   0.01817  -0.0569   0.3158   1.0000
   9.500   1.2661   0.02688   0.01874  -0.0537   0.3035   1.0000
   9.750   1.2700   0.02731   0.01926  -0.0499   0.2906   1.0000
  10.000   1.2630   0.02774   0.01977  -0.0444   0.2753   1.0000
  10.250   1.2562   0.02839   0.02053  -0.0395   0.2586   1.0000
  10.500   1.2486   0.02933   0.02151  -0.0352   0.2381   1.0000
  10.750   1.2401   0.03070   0.02292  -0.0314   0.2054   1.0000
  11.000   1.2274   0.03293   0.02485  -0.0280   0.1531   1.0000
  11.250   1.2060   0.03648   0.02783  -0.0248   0.0893   1.0000
  11.500   1.1912   0.03994   0.03105  -0.0224   0.0694   1.0000
  11.750   1.1824   0.04303   0.03416  -0.0207   0.0617   1.0000
  12.000   1.1737   0.04625   0.03745  -0.0194   0.0578   1.0000
  12.250   1.1637   0.04977   0.04108  -0.0184   0.0547   1.0000
  12.500   1.1566   0.05315   0.04462  -0.0177   0.0526   1.0000
  12.750   1.1487   0.05675   0.04836  -0.0173   0.0512   1.0000
  13.000   1.1399   0.06062   0.05237  -0.0173   0.0499   1.0000
  13.250   1.1306   0.06471   0.05657  -0.0174   0.0486   1.0000
  13.500   1.1203   0.06902   0.06096  -0.0177   0.0473   1.0000
  13.750   1.1144   0.07273   0.06470  -0.0178   0.0457   1.0000
  14.000   1.1161   0.07555   0.06765  -0.0175   0.0444   1.0000
  14.250   1.1209   0.07788   0.07006  -0.0171   0.0431   1.0000
  14.500   1.1298   0.07960   0.07184  -0.0160   0.0416   1.0000
  14.750   1.1454   0.08038   0.07263  -0.0143   0.0405   1.0000
  15.000   1.1666   0.08066   0.07290  -0.0122   0.0395   1.0000
  15.250   1.1917   0.08098   0.07322  -0.0099   0.0387   1.0000
  15.500   1.2242   0.08155   0.07380  -0.0074   0.0378   1.0000
  15.750   1.2416   0.08439   0.07677  -0.0063   0.0371   1.0000
  16.000   1.2380   0.08828   0.08091  -0.0066   0.0369   1.0000
  16.250   1.2312   0.09249   0.08538  -0.0073   0.0368   1.0000
  16.500   1.2214   0.09713   0.09027  -0.0085   0.0368   1.0000
  16.750   1.2113   0.10210   0.09546  -0.0099   0.0368   1.0000
  17.000   1.1969   0.10764   0.10123  -0.0121   0.0368   1.0000
  17.250   1.1826   0.11353   0.10733  -0.0145   0.0369   1.0000
  17.500   1.1705   0.11949   0.11348  -0.0170   0.0371   1.0000
  17.750   1.1540   0.12589   0.12011  -0.0206   0.0374   1.0000
  18.000   1.1304   0.13375   0.12822  -0.0260   0.0377   1.0000
  18.250   1.0157   0.16534   0.16043  -0.0492   0.0430   1.0000
  18.500   0.9879   0.17872   0.17382  -0.0569   0.0451   1.0000
  18.750   0.9832   0.18568   0.18075  -0.0601   0.0460   1.0000
<< Back to WB-135/35 13.5% smoothed (wb13535sm-il)

Polar data table (+)

Polar graphs


<< Back to WB-135/35 13.5% smoothed (wb13535sm-il)