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

S2055 (s2055-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: S2055 (s2055-il)
Reynolds number: 100,000
Max Cl/Cd: 51.88 at α=4.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s2055-il-100000.txt
Download as CSV file: xf-s2055-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S2055                                           
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.4803   0.10745   0.10238  -0.0214   1.0000   0.0815
  -9.250  -0.4929   0.10496   0.09999  -0.0263   1.0000   0.0827
  -9.000  -0.5083   0.10206   0.09721  -0.0315   1.0000   0.0831
  -8.750  -0.4755   0.09614   0.09122  -0.0241   1.0000   0.0868
  -8.500  -0.4720   0.09289   0.08801  -0.0244   1.0000   0.0898
  -8.250  -0.4758   0.08965   0.08483  -0.0261   1.0000   0.0932
  -8.000  -0.4912   0.08661   0.08192  -0.0296   1.0000   0.0953
  -7.750  -0.5167   0.08341   0.07872  -0.0361   1.0000   0.0965
  -7.500  -0.5111   0.07857   0.07396  -0.0346   1.0000   0.0982
  -7.250  -0.4982   0.07566   0.07111  -0.0309   1.0000   0.1019
  -7.000  -0.5003   0.07239   0.06784  -0.0316   1.0000   0.1065
  -6.750  -0.5191   0.06885   0.06405  -0.0360   1.0000   0.1113
  -6.500  -0.5032   0.06532   0.06075  -0.0319   1.0000   0.1159
  -6.250  -0.5125   0.06258   0.05764  -0.0341   1.0000   0.1251
  -6.000  -0.4984   0.05926   0.05462  -0.0303   1.0000   0.1323
  -5.750  -0.4617   0.04410   0.03986  -0.0268   1.0000   0.1466
  -4.750  -0.4414   0.03738   0.03059  -0.0277   1.0000   0.0821
  -4.500  -0.4218   0.03220   0.02493  -0.0262   1.0000   0.0659
  -4.250  -0.4010   0.02853   0.02066  -0.0246   1.0000   0.0604
  -4.000  -0.3783   0.02583   0.01733  -0.0231   1.0000   0.0591
  -3.750  -0.3570   0.02437   0.01572  -0.0220   1.0000   0.0646
  -3.500  -0.3332   0.02261   0.01357  -0.0207   1.0000   0.0668
  -3.250  -0.3085   0.02098   0.01162  -0.0195   1.0000   0.0703
  -3.000  -0.2858   0.01975   0.01040  -0.0186   1.0000   0.0808
  -2.750  -0.2626   0.01837   0.00904  -0.0175   1.0000   0.0912
  -2.500  -0.2408   0.01730   0.00807  -0.0164   1.0000   0.1143
  -2.250  -0.2195   0.01576   0.00703  -0.0153   1.0000   0.1870
  -2.000  -0.1432   0.01315   0.00726  -0.0206   1.0000   1.0000
  -1.750  -0.1357   0.01312   0.00698  -0.0176   1.0000   1.0000
  -1.500  -0.1242   0.01315   0.00678  -0.0153   1.0000   1.0000
  -1.250  -0.1097   0.01323   0.00665  -0.0136   1.0000   1.0000
  -1.000  -0.0932   0.01335   0.00658  -0.0122   1.0000   1.0000
  -0.750  -0.0755   0.01351   0.00657  -0.0110   1.0000   1.0000
  -0.500  -0.0570   0.01371   0.00658  -0.0100   1.0000   1.0000
  -0.250  -0.0381   0.01393   0.00668  -0.0092   1.0000   1.0000
   0.000  -0.0188   0.01419   0.00681  -0.0084   1.0000   1.0000
   0.250   0.0006   0.01448   0.00700  -0.0077   1.0000   1.0000
   0.500   0.0377   0.01502   0.00742  -0.0105   0.9946   1.0000
   0.750   0.0871   0.01563   0.00795  -0.0155   0.9841   1.0000
   1.000   0.1355   0.01611   0.00839  -0.0202   0.9724   1.0000
   1.250   0.1851   0.01648   0.00873  -0.0249   0.9593   1.0000
   1.500   0.2355   0.01671   0.00897  -0.0295   0.9454   1.0000
   1.750   0.2847   0.01680   0.00910  -0.0336   0.9316   1.0000
   2.000   0.3324   0.01678   0.00916  -0.0373   0.9180   1.0000
   2.250   0.3796   0.01666   0.00913  -0.0407   0.9046   1.0000
   2.500   0.4289   0.01639   0.00898  -0.0443   0.8910   1.0000
   2.750   0.4769   0.01599   0.00875  -0.0474   0.8772   1.0000
   3.000   0.5216   0.01550   0.00841  -0.0495   0.8621   1.0000
   3.250   0.5649   0.01491   0.00798  -0.0510   0.8455   1.0000
   3.500   0.5950   0.01452   0.00776  -0.0501   0.8218   1.0000
   3.750   0.6260   0.01409   0.00744  -0.0492   0.7945   1.0000
   4.000   0.6547   0.01372   0.00714  -0.0477   0.7602   1.0000
   4.250   0.6782   0.01353   0.00696  -0.0454   0.7116   1.0000
   4.500   0.6998   0.01349   0.00682  -0.0427   0.6424   1.0000
   4.750   0.7184   0.01385   0.00676  -0.0398   0.5520   1.0000
   5.000   0.7352   0.01462   0.00705  -0.0373   0.4699   1.0000
   5.250   0.7527   0.01546   0.00755  -0.0352   0.4079   1.0000
   5.500   0.7712   0.01628   0.00814  -0.0335   0.3582   1.0000
   5.750   0.7896   0.01711   0.00880  -0.0319   0.3134   1.0000
   6.000   0.8071   0.01793   0.00950  -0.0302   0.2618   1.0000
   6.250   0.8219   0.01907   0.01033  -0.0281   0.1976   1.0000
   6.500   0.8366   0.02055   0.01144  -0.0260   0.1390   1.0000
   6.750   0.8530   0.02213   0.01271  -0.0243   0.1075   1.0000
   7.000   0.8732   0.02391   0.01448  -0.0228   0.0900   1.0000
   7.250   0.8950   0.02585   0.01644  -0.0218   0.0780   1.0000
   7.500   0.9186   0.02813   0.01864  -0.0212   0.0690   1.0000
   7.750   0.9435   0.03050   0.02140  -0.0201   0.0648   1.0000
   8.000   0.9652   0.03270   0.02384  -0.0190   0.0597   1.0000
   8.250   0.9843   0.03629   0.02761  -0.0182   0.0556   1.0000
   8.500   0.9991   0.03939   0.03132  -0.0160   0.0544   1.0000
   8.750   1.0097   0.04309   0.03559  -0.0136   0.0538   1.0000
   9.000   1.0150   0.04673   0.03979  -0.0110   0.0525   1.0000
   9.250   1.0160   0.05042   0.04398  -0.0084   0.0510   1.0000
   9.500   1.0121   0.05469   0.04869  -0.0058   0.0510   1.0000
   9.750   1.0031   0.05938   0.05376  -0.0034   0.0521   1.0000
  10.000   0.9915   0.06395   0.05859  -0.0013   0.0532   1.0000
  10.250   0.9766   0.06828   0.06310   0.0008   0.0542   1.0000
  10.500   0.9644   0.07299   0.06790   0.0020   0.0552   1.0000
  10.750   0.8103   0.07471   0.07034   0.0022   0.0628   1.0000
  11.000   0.7785   0.08367   0.07936  -0.0027   0.0652   1.0000
  11.250   0.7608   0.09162   0.08732  -0.0064   0.0669   1.0000
  11.500   0.7688   0.09615   0.09183  -0.0051   0.0684   1.0000
  12.250   0.6688   0.13716   0.13271  -0.0313   0.1328   1.0000
  12.500   0.6469   0.14050   0.13600  -0.0355   0.1287   1.0000
<< Back to S2055 (s2055-il)

Polar data table (+)

Polar graphs


<< Back to S2055 (s2055-il)