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

S3021-095-84 (s3021-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: S3021-095-84 (s3021-il)
Reynolds number: 500,000
Max Cl/Cd: 101.36 at α=5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s3021-il-500000.txt
Download as CSV file: xf-s3021-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S3021-095-84                                    
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.4171   0.10141   0.09911  -0.0243   1.0000   0.0168
  -9.750  -0.4127   0.09836   0.09607  -0.0250   1.0000   0.0171
  -9.500  -0.4061   0.09604   0.09376  -0.0251   1.0000   0.0176
  -9.250  -0.4020   0.09305   0.09079  -0.0260   1.0000   0.0180
  -7.000  -0.4227   0.05558   0.05339  -0.0451   0.9993   0.0223
  -6.750  -0.4097   0.04328   0.04066  -0.0553   0.9912   0.0232
  -6.500  -0.3811   0.04110   0.03847  -0.0584   0.9867   0.0240
  -6.250  -0.3501   0.03892   0.03620  -0.0618   0.9827   0.0255
  -6.000  -0.3203   0.03477   0.03173  -0.0649   0.9754   0.0282
  -5.750  -0.2955   0.02915   0.02540  -0.0671   0.9654   0.0315
  -5.500  -0.2661   0.02696   0.02320  -0.0689   0.9575   0.0330
  -5.250  -0.2402   0.02525   0.02134  -0.0692   0.9439   0.0348
  -5.000  -0.2086   0.02626   0.02206  -0.0687   0.9291   0.0401
  -4.750  -0.1923   0.01704   0.01176  -0.0658   0.9110   0.0218
  -4.500  -0.1686   0.01492   0.00932  -0.0647   0.8937   0.0209
  -4.250  -0.1438   0.01367   0.00783  -0.0637   0.8765   0.0207
  -4.000  -0.1188   0.01278   0.00677  -0.0629   0.8599   0.0209
  -3.750  -0.0933   0.01220   0.00604  -0.0621   0.8441   0.0215
  -3.500  -0.0684   0.01144   0.00514  -0.0613   0.8293   0.0215
  -3.250  -0.0432   0.01083   0.00439  -0.0605   0.8152   0.0216
  -3.000  -0.0177   0.01035   0.00380  -0.0599   0.8019   0.0219
  -2.750   0.0083   0.00999   0.00333  -0.0593   0.7893   0.0224
  -2.500   0.0341   0.00952   0.00274  -0.0587   0.7774   0.0243
  -2.250   0.0607   0.00929   0.00242  -0.0583   0.7662   0.0269
  -2.000   0.0875   0.00909   0.00216  -0.0579   0.7553   0.0345
  -1.750   0.1120   0.00838   0.00193  -0.0574   0.7443   0.1651
  -1.500   0.1369   0.00788   0.00183  -0.0571   0.7340   0.2956
  -1.250   0.1620   0.00751   0.00176  -0.0566   0.7243   0.4091
  -1.000   0.1853   0.00698   0.00173  -0.0559   0.7140   0.5696
  -0.750   0.2036   0.00627   0.00176  -0.0536   0.7044   0.7888
  -0.500   0.2496   0.00611   0.00189  -0.0564   0.6947   0.9706
  -0.250   0.3039   0.00617   0.00183  -0.0620   0.6838   0.9888
   0.000   0.3540   0.00619   0.00174  -0.0668   0.6728   0.9991
   0.250   0.3815   0.00624   0.00170  -0.0667   0.6628   1.0000
   0.500   0.4060   0.00631   0.00167  -0.0660   0.6532   1.0000
   0.750   0.4308   0.00635   0.00166  -0.0654   0.6430   1.0000
   1.000   0.4556   0.00642   0.00166  -0.0647   0.6331   1.0000
   1.250   0.4803   0.00650   0.00166  -0.0640   0.6235   1.0000
   1.500   0.5053   0.00656   0.00168  -0.0634   0.6129   1.0000
   1.750   0.5304   0.00664   0.00172  -0.0628   0.6026   1.0000
   2.000   0.5553   0.00673   0.00175  -0.0621   0.5924   1.0000
   2.250   0.5802   0.00683   0.00179  -0.0615   0.5813   1.0000
   2.500   0.6053   0.00691   0.00185  -0.0609   0.5697   1.0000
   2.750   0.6303   0.00701   0.00192  -0.0603   0.5580   1.0000
   3.000   0.6553   0.00712   0.00199  -0.0596   0.5459   1.0000
   3.250   0.6802   0.00723   0.00207  -0.0590   0.5329   1.0000
   3.500   0.7050   0.00736   0.00216  -0.0584   0.5194   1.0000
   3.750   0.7298   0.00750   0.00227  -0.0577   0.5053   1.0000
   4.000   0.7546   0.00764   0.00238  -0.0571   0.4896   1.0000
   4.250   0.7792   0.00780   0.00250  -0.0565   0.4733   1.0000
   4.500   0.8037   0.00798   0.00264  -0.0558   0.4557   1.0000
   4.750   0.8280   0.00820   0.00281  -0.0551   0.4368   1.0000
   5.000   0.8524   0.00841   0.00298  -0.0545   0.4163   1.0000
   5.250   0.8764   0.00867   0.00317  -0.0538   0.3952   1.0000
   5.500   0.9005   0.00894   0.00340  -0.0532   0.3725   1.0000
   5.750   0.9240   0.00925   0.00364  -0.0525   0.3487   1.0000
   6.000   0.9466   0.00966   0.00391  -0.0516   0.3150   1.0000
   6.250   0.9684   0.01015   0.00423  -0.0507   0.2797   1.0000
   6.500   0.9907   0.01061   0.00457  -0.0499   0.2491   1.0000
   6.750   1.0129   0.01107   0.00492  -0.0491   0.2210   1.0000
   7.250   1.0566   0.01207   0.00571  -0.0474   0.1692   1.0000
   7.500   1.0773   0.01267   0.00617  -0.0465   0.1399   1.0000
   7.750   1.0957   0.01348   0.00676  -0.0452   0.1020   1.0000
   8.000   1.1143   0.01426   0.00736  -0.0440   0.0713   1.0000
   8.250   1.1269   0.01556   0.00834  -0.0419   0.0275   1.0000
   8.500   1.1430   0.01653   0.00923  -0.0402   0.0149   1.0000
   8.750   1.1615   0.01725   0.01002  -0.0388   0.0128   1.0000
   9.000   1.1797   0.01795   0.01082  -0.0374   0.0118   1.0000
   9.250   1.1968   0.01870   0.01167  -0.0359   0.0112   1.0000
   9.500   1.2116   0.01958   0.01263  -0.0341   0.0106   1.0000
   9.750   1.2221   0.02070   0.01386  -0.0317   0.0101   1.0000
  10.000   1.2273   0.02190   0.01516  -0.0285   0.0097   1.0000
  10.250   1.2307   0.02313   0.01650  -0.0252   0.0095   1.0000
  10.500   1.2380   0.02417   0.01764  -0.0227   0.0094   1.0000
  10.750   1.2430   0.02545   0.01902  -0.0201   0.0093   1.0000
  11.000   1.2487   0.02675   0.02044  -0.0180   0.0090   1.0000
  11.250   1.2516   0.02837   0.02217  -0.0158   0.0090   1.0000
  11.500   1.2548   0.03009   0.02399  -0.0140   0.0089   1.0000
  11.750   1.2575   0.03198   0.02600  -0.0125   0.0087   1.0000
  12.000   1.2597   0.03405   0.02819  -0.0111   0.0087   1.0000
  12.250   1.2618   0.03624   0.03049  -0.0100   0.0086   1.0000
  12.500   1.2638   0.03854   0.03291  -0.0091   0.0084   1.0000
  12.750   1.2656   0.04093   0.03543  -0.0084   0.0083   1.0000
  13.000   1.2667   0.04354   0.03818  -0.0077   0.0084   1.0000
  13.250   1.2667   0.04634   0.04111  -0.0073   0.0082   1.0000
  13.500   1.2659   0.04933   0.04424  -0.0071   0.0082   1.0000
  13.750   1.2637   0.05259   0.04765  -0.0070   0.0081   1.0000
  14.000   1.2605   0.05609   0.05132  -0.0072   0.0082   1.0000
  14.250   1.2555   0.05988   0.05527  -0.0077   0.0081   1.0000
  14.500   1.2481   0.06421   0.05982  -0.0085   0.0082   1.0000
  14.750   1.2392   0.06891   0.06470  -0.0098   0.0082   1.0000
  15.000   1.2283   0.07412   0.07009  -0.0115   0.0083   1.0000
  15.250   1.2163   0.07974   0.07591  -0.0138   0.0084   1.0000
  15.500   1.2015   0.08616   0.08252  -0.0167   0.0085   1.0000
  15.750   1.1861   0.09300   0.08954  -0.0202   0.0085   1.0000
  16.000   1.1701   0.10030   0.09702  -0.0241   0.0087   1.0000
  16.250   1.1523   0.10836   0.10525  -0.0287   0.0087   1.0000
  16.500   1.1354   0.11658   0.11364  -0.0335   0.0088   1.0000
  16.750   1.1175   0.12540   0.12259  -0.0389   0.0090   1.0000
  17.000   1.1007   0.13439   0.13173  -0.0444   0.0090   1.0000
  17.250   1.0812   0.14450   0.14197  -0.0507   0.0091   1.0000
<< Back to S3021-095-84 (s3021-il)

Polar data table (+)

Polar graphs


<< Back to S3021-095-84 (s3021-il)