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

WASP (smoothed) (waspsm-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: WASP (smoothed) (waspsm-il)
Reynolds number: 50,000
Max Cl/Cd: 31.08 at α=6.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-waspsm-il-50000.txt
Download as CSV file: xf-waspsm-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: WASP (smoothed)                                 
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.4277   0.11372   0.10676  -0.0145   1.0000   0.2078
  -8.500  -0.4008   0.10746   0.10047  -0.0124   1.0000   0.2169
  -8.250  -0.4243   0.10763   0.10082  -0.0150   1.0000   0.2230
  -8.000  -0.3966   0.10161   0.09474  -0.0128   1.0000   0.2338
  -7.750  -0.4006   0.09897   0.09220  -0.0133   1.0000   0.2410
  -7.500  -0.4040   0.09692   0.09025  -0.0131   1.0000   0.2520
  -7.250  -0.3905   0.09282   0.08618  -0.0119   1.0000   0.2632
  -7.000  -0.3896   0.08997   0.08342  -0.0109   1.0000   0.2752
  -6.750  -0.3934   0.08752   0.08109  -0.0099   1.0000   0.2880
  -6.500  -0.3906   0.08471   0.07837  -0.0085   1.0000   0.3040
  -6.250  -0.3876   0.08191   0.07566  -0.0071   1.0000   0.3206
  -6.000  -0.3856   0.07922   0.07305  -0.0055   1.0000   0.3376
  -5.750  -0.3874   0.07686   0.07080  -0.0041   1.0000   0.3566
  -5.500  -0.3915   0.07450   0.06856  -0.0027   1.0000   0.3766
  -5.250  -0.3805   0.07126   0.06535   0.0006   1.0000   0.3970
  -5.000  -0.3808   0.06891   0.06310   0.0038   1.0000   0.4246
  -4.750  -0.3741   0.06634   0.06060   0.0084   1.0000   0.4590
  -4.500  -0.3386   0.04685   0.03954  -0.0402   1.0000   0.1610
  -4.250  -0.3213   0.04310   0.03554  -0.0403   1.0000   0.1570
  -4.000  -0.3004   0.03893   0.03077  -0.0411   1.0000   0.1515
  -3.750  -0.2769   0.03554   0.02656  -0.0412   1.0000   0.1473
  -3.500  -0.2540   0.03284   0.02335  -0.0408   1.0000   0.1486
  -3.250  -0.2330   0.03105   0.02155  -0.0401   1.0000   0.1574
  -3.000  -0.2075   0.02905   0.01893  -0.0396   1.0000   0.1634
  -2.750  -0.1839   0.02753   0.01731  -0.0391   1.0000   0.1752
  -2.500  -0.1589   0.02619   0.01577  -0.0386   1.0000   0.1912
  -2.250  -0.1329   0.02495   0.01449  -0.0384   1.0000   0.2129
  -2.000  -0.1078   0.02388   0.01344  -0.0379   1.0000   0.2446
  -1.750  -0.0789   0.02281   0.01256  -0.0382   1.0000   0.3053
  -1.500  -0.0491   0.02112   0.01186  -0.0383   1.0000   0.4688
  -1.250  -0.0170   0.01892   0.01099  -0.0377   1.0000   1.0000
  -1.000   0.0038   0.01936   0.01096  -0.0376   1.0000   1.0000
  -0.750   0.0234   0.01987   0.01112  -0.0373   1.0000   1.0000
  -0.500   0.0422   0.02045   0.01142  -0.0371   1.0000   1.0000
  -0.250   0.0603   0.02111   0.01183  -0.0370   1.0000   1.0000
   0.000   0.0779   0.02186   0.01238  -0.0370   1.0000   1.0000
   0.250   0.1210   0.02283   0.01311  -0.0418   0.9897   1.0000
   0.500   0.1821   0.02376   0.01379  -0.0494   0.9699   1.0000
   0.750   0.2416   0.02458   0.01442  -0.0564   0.9502   1.0000
   1.000   0.2946   0.02523   0.01495  -0.0619   0.9287   1.0000
   1.250   0.3510   0.02572   0.01535  -0.0676   0.9088   1.0000
   1.500   0.3939   0.02614   0.01573  -0.0707   0.8864   1.0000
   1.750   0.4476   0.02629   0.01586  -0.0751   0.8670   1.0000
   2.000   0.4909   0.02649   0.01605  -0.0776   0.8463   1.0000
   2.250   0.5321   0.02658   0.01616  -0.0793   0.8258   1.0000
   2.500   0.5764   0.02644   0.01604  -0.0811   0.8072   1.0000
   2.750   0.6086   0.02662   0.01625  -0.0810   0.7863   1.0000
   3.000   0.6423   0.02666   0.01631  -0.0809   0.7660   1.0000
   3.250   0.6783   0.02654   0.01620  -0.0808   0.7472   1.0000
   3.500   0.7045   0.02685   0.01654  -0.0796   0.7259   1.0000
   3.750   0.7334   0.02701   0.01674  -0.0786   0.7055   1.0000
   4.000   0.7650   0.02699   0.01672  -0.0776   0.6866   1.0000
   4.250   0.7871   0.02754   0.01732  -0.0760   0.6647   1.0000
   4.500   0.8142   0.02779   0.01761  -0.0747   0.6446   1.0000
   4.750   0.8421   0.02801   0.01783  -0.0734   0.6251   1.0000
   5.000   0.8630   0.02872   0.01861  -0.0718   0.6036   1.0000
   5.250   0.8893   0.02909   0.01899  -0.0704   0.5839   1.0000
   5.500   0.9139   0.02964   0.01960  -0.0690   0.5643   1.0000
   5.750   0.9347   0.03049   0.02055  -0.0675   0.5439   1.0000
   6.000   0.9591   0.03111   0.02120  -0.0661   0.5248   1.0000
   6.250   0.9852   0.03170   0.02179  -0.0649   0.5067   1.0000
   6.500   1.0031   0.03291   0.02319  -0.0633   0.4875   1.0000
   6.750   1.0234   0.03402   0.02443  -0.0618   0.4695   1.0000
   7.000   1.0449   0.03505   0.02556  -0.0604   0.4521   1.0000
   7.250   1.0664   0.03614   0.02676  -0.0590   0.4356   1.0000
   7.500   1.0879   0.03724   0.02797  -0.0576   0.4193   1.0000
   7.750   1.1090   0.03841   0.02930  -0.0562   0.4035   1.0000
   8.000   1.1311   0.03947   0.03046  -0.0548   0.3874   1.0000
   8.250   1.1470   0.04095   0.03214  -0.0530   0.3710   1.0000
   8.500   1.1604   0.04239   0.03382  -0.0509   0.3530   1.0000
   8.750   1.1904   0.04162   0.03296  -0.0492   0.3287   1.0000
   9.000   1.2037   0.04200   0.03349  -0.0465   0.3037   1.0000
   9.250   1.2224   0.04160   0.03302  -0.0439   0.2748   1.0000
   9.500   1.2419   0.04094   0.03201  -0.0413   0.2403   1.0000
   9.750   1.2448   0.04213   0.03324  -0.0375   0.2077   1.0000
  10.000   1.2492   0.04378   0.03476  -0.0340   0.1774   1.0000
  10.250   1.2577   0.04564   0.03640  -0.0313   0.1540   1.0000
  10.500   1.2631   0.04840   0.03930  -0.0287   0.1390   1.0000
  10.750   1.2712   0.05099   0.04191  -0.0265   0.1268   1.0000
  11.000   1.2715   0.05399   0.04523  -0.0238   0.1188   1.0000
  11.250   1.2759   0.05760   0.04900  -0.0219   0.1132   1.0000
  11.500   1.2629   0.06158   0.05343  -0.0189   0.1107   1.0000
  11.750   1.2471   0.06541   0.05756  -0.0160   0.1087   1.0000
  12.000   1.2284   0.06954   0.06195  -0.0139   0.1075   1.0000
  12.250   1.2160   0.07352   0.06609  -0.0128   0.1054   1.0000
  12.500   1.1998   0.07811   0.07083  -0.0124   0.1041   1.0000
  12.750   1.1843   0.08315   0.07598  -0.0127   0.1030   1.0000
<< Back to WASP (smoothed) (waspsm-il)

Polar data table (+)

Polar graphs


<< Back to WASP (smoothed) (waspsm-il)