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S4096 (designed for the E-flite UMX ASK-21 scale RC sailplane) (s4096-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: S4096 (designed for the E-flite UMX ASK-21 scale RC sailplane) (s4096-il)
Reynolds number: 100,000
Max Cl/Cd: 40.47 at α=7.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s4096-il-100000-n5.txt
Download as CSV file: xf-s4096-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S4096 (designed for the E-flite UMX ASK-21 scale
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -11.250  -0.5004   0.13270   0.12790  -0.0001   1.0011   0.0354
 -11.000  -0.4968   0.12970   0.12490  -0.0002   1.0011   0.0347
 -10.750  -0.6614   0.13565   0.13061   0.0151   1.0011   0.0354
 -10.500  -0.6543   0.13228   0.12725   0.0154   1.0011   0.0345
 -10.250  -0.6523   0.12764   0.12263   0.0140   1.0011   0.0336
 -10.000  -0.6534   0.12233   0.11735   0.0119   1.0011   0.0328
  -9.750  -0.6576   0.11637   0.11143   0.0092   1.0011   0.0319
  -9.250  -0.7139   0.08777   0.08284  -0.0109   1.0011   0.0279
  -9.000  -0.7187   0.08078   0.07572  -0.0146   1.0011   0.0277
  -8.750  -0.7198   0.07352   0.06821  -0.0182   1.0011   0.0275
  -8.500  -0.7147   0.06621   0.06054  -0.0216   1.0011   0.0273
  -8.250  -0.7026   0.05931   0.05314  -0.0246   1.0011   0.0271
  -8.000  -0.6840   0.05285   0.04597  -0.0273   1.0011   0.0275
  -7.750  -0.6607   0.04779   0.04022  -0.0293   1.0011   0.0284
  -7.500  -0.6354   0.04474   0.03688  -0.0307   1.0011   0.0292
  -7.250  -0.6080   0.04146   0.03316  -0.0319   1.0011   0.0296
  -7.000  -0.5795   0.03858   0.02984  -0.0329   1.0011   0.0299
  -6.750  -0.5504   0.03612   0.02703  -0.0338   1.0011   0.0304
  -6.500  -0.5211   0.03398   0.02458  -0.0345   1.0011   0.0311
  -6.250  -0.4917   0.03212   0.02245  -0.0351   1.0011   0.0318
  -6.000  -0.4623   0.03056   0.02067  -0.0357   1.0011   0.0331
  -5.750  -0.4327   0.02932   0.01920  -0.0362   1.0011   0.0351
  -5.500  -0.4038   0.02793   0.01777  -0.0367   1.0011   0.0368
  -5.250  -0.3747   0.02680   0.01660  -0.0373   1.0011   0.0384
  -5.000  -0.3454   0.02583   0.01558  -0.0379   1.0011   0.0403
  -4.750  -0.3158   0.02496   0.01462  -0.0384   1.0011   0.0429
  -4.500  -0.2860   0.02415   0.01373  -0.0391   1.0011   0.0464
  -4.250  -0.2563   0.02345   0.01300  -0.0398   1.0011   0.0545
  -4.000  -0.2264   0.02262   0.01229  -0.0406   1.0011   0.0724
  -3.750  -0.1967   0.02174   0.01172  -0.0414   1.0011   0.1282
  -3.500  -0.1678   0.02095   0.01142  -0.0424   1.0011   0.2283
  -3.250  -0.1398   0.02021   0.01135  -0.0431   1.0011   0.3690
  -3.000  -0.1123   0.01966   0.01131  -0.0434   1.0011   0.4847
  -2.750  -0.0853   0.01925   0.01130  -0.0433   1.0011   0.5866
  -2.500  -0.0611   0.01887   0.01135  -0.0422   1.0011   0.7029
  -2.250  -0.0413   0.01847   0.01133  -0.0394   1.0011   0.8419
  -2.000  -0.0122   0.01770   0.01065  -0.0396   1.0011   0.9989
  -1.750   0.0160   0.01802   0.01081  -0.0403   1.0011   0.9989
  -1.500   0.0549   0.01816   0.01075  -0.0432   0.9865   0.9989
  -1.250   0.0949   0.01809   0.01050  -0.0463   0.9638   0.9989
  -1.000   0.1338   0.01807   0.01030  -0.0490   0.9402   0.9989
  -0.750   0.1700   0.01809   0.01016  -0.0509   0.9150   0.9989
  -0.500   0.2024   0.01816   0.01007  -0.0518   0.8885   0.9989
  -0.250   0.2322   0.01827   0.01002  -0.0520   0.8631   0.9989
   0.000   0.2607   0.01840   0.00999  -0.0520   0.8392   0.9989
   0.250   0.2890   0.01853   0.00998  -0.0519   0.8165   0.9989
   0.500   0.3171   0.01868   0.00999  -0.0519   0.7954   0.9989
   0.750   0.3455   0.01883   0.01001  -0.0519   0.7757   0.9989
   1.000   0.3741   0.01898   0.01005  -0.0520   0.7561   0.9989
   1.250   0.4027   0.01914   0.01010  -0.0521   0.7375   0.9989
   1.500   0.4313   0.01932   0.01018  -0.0523   0.7196   0.9989
   1.750   0.4599   0.01950   0.01026  -0.0524   0.7022   0.9989
   2.000   0.4888   0.01969   0.01036  -0.0527   0.6849   0.9989
   2.250   0.5178   0.01988   0.01049  -0.0530   0.6674   0.9989
   2.500   0.5468   0.02008   0.01062  -0.0534   0.6501   0.9989
   2.750   0.5757   0.02028   0.01076  -0.0537   0.6327   0.9989
   3.000   0.6046   0.02050   0.01093  -0.0540   0.6153   0.9989
   3.250   0.6335   0.02072   0.01109  -0.0543   0.5978   0.9989
   3.500   0.6623   0.02095   0.01127  -0.0546   0.5800   0.9989
   3.750   0.6913   0.02118   0.01149  -0.0550   0.5613   0.9989
   4.000   0.7201   0.02142   0.01172  -0.0554   0.5421   0.9989
   4.250   0.7488   0.02168   0.01194  -0.0558   0.5227   0.9989
   4.500   0.7776   0.02195   0.01219  -0.0561   0.5024   0.9989
   4.750   0.8062   0.02224   0.01248  -0.0565   0.4812   0.9989
   5.000   0.8347   0.02255   0.01275  -0.0569   0.4600   0.9989
   5.250   0.8631   0.02289   0.01307  -0.0572   0.4376   0.9989
   5.500   0.8912   0.02326   0.01342  -0.0576   0.4158   0.9989
   5.750   0.9194   0.02366   0.01381  -0.0580   0.3933   0.9989
   6.000   0.9472   0.02411   0.01421  -0.0583   0.3718   0.9989
   6.250   0.9751   0.02458   0.01467  -0.0587   0.3495   0.9989
   6.500   1.0026   0.02510   0.01518  -0.0591   0.3284   0.9989
   6.750   1.0301   0.02562   0.01572  -0.0594   0.3069   0.9989
   7.000   1.0572   0.02620   0.01628  -0.0598   0.2864   0.9989
   7.250   1.0842   0.02681   0.01692  -0.0601   0.2664   0.9989
   7.500   1.1109   0.02745   0.01758  -0.0604   0.2470   0.9989
   7.750   1.1372   0.02815   0.01828  -0.0607   0.2285   0.9989
   8.000   1.1632   0.02889   0.01902  -0.0609   0.2110   0.9989
   8.250   1.1890   0.02964   0.01985  -0.0611   0.1937   0.9989
   8.500   1.2143   0.03045   0.02071  -0.0613   0.1775   0.9989
   8.750   1.2390   0.03132   0.02163  -0.0614   0.1621   0.9989
   9.000   1.2633   0.03225   0.02261  -0.0614   0.1479   0.9989
   9.250   1.2869   0.03323   0.02365  -0.0614   0.1348   0.9989
   9.500   1.3098   0.03428   0.02480  -0.0612   0.1231   0.9989
   9.750   1.3316   0.03543   0.02600  -0.0609   0.1128   0.9989
  10.000   1.3527   0.03663   0.02730  -0.0606   0.1035   0.9989
  10.250   1.3733   0.03787   0.02870  -0.0601   0.0947   0.9989
  10.500   1.3915   0.03930   0.03018  -0.0593   0.0875   0.9989
  10.750   1.4096   0.04070   0.03179  -0.0585   0.0804   0.9989
  11.000   1.4250   0.04232   0.03352  -0.0574   0.0744   0.9989
  11.250   1.4395   0.04385   0.03520  -0.0563   0.0674   0.9989
  11.500   1.4521   0.04550   0.03701  -0.0550   0.0602   0.9989
  11.750   1.4599   0.04740   0.03895  -0.0534   0.0540   0.9989
  12.000   1.4686   0.04921   0.04102  -0.0517   0.0478   0.9989
  12.250   1.4658   0.05178   0.04366  -0.0488   0.0444   0.9989
  12.500   1.4606   0.05445   0.04659  -0.0455   0.0412   0.9989
  12.750   1.4534   0.05766   0.04999  -0.0430   0.0384   0.9989
  13.000   1.4432   0.06157   0.05406  -0.0414   0.0363   0.9989
  13.250   1.4341   0.06582   0.05852  -0.0406   0.0341   0.9989
  13.500   1.4250   0.07041   0.06334  -0.0404   0.0319   0.9989
  13.750   1.4139   0.07554   0.06866  -0.0410   0.0302   0.9989
  14.000   1.4007   0.08122   0.07451  -0.0422   0.0291   0.9989
  14.250   1.3852   0.08746   0.08089  -0.0439   0.0283   0.9989
  14.500   1.3709   0.09371   0.08733  -0.0457   0.0273   0.9989
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