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S3021-095-84 (s3021-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: S3021-095-84 (s3021-il)
Reynolds number: 1,000,000
Max Cl/Cd: 119.73 at α=4.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s3021-il-1000000.txt
Download as CSV file: xf-s3021-il-1000000.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 =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.4055   0.08954   0.08794  -0.0275   1.0000   0.0117
  -9.000  -0.4054   0.08534   0.08375  -0.0293   1.0000   0.0117
  -7.500  -0.4458   0.04497   0.04323  -0.0554   0.9948   0.0121
  -7.250  -0.4263   0.03983   0.03790  -0.0604   0.9887   0.0125
  -7.000  -0.3990   0.03663   0.03454  -0.0643   0.9849   0.0128
  -6.750  -0.3755   0.03307   0.03077  -0.0667   0.9766   0.0132
  -6.500  -0.3516   0.02961   0.02705  -0.0684   0.9662   0.0138
  -6.250  -0.3301   0.02643   0.02357  -0.0687   0.9505   0.0146
  -6.000  -0.3058   0.02502   0.02188  -0.0680   0.9310   0.0160
  -5.750  -0.2832   0.02450   0.02103  -0.0668   0.9071   0.0164
  -5.500  -0.2747   0.01874   0.01466  -0.0651   0.8828   0.0177
  -5.250  -0.2520   0.01762   0.01338  -0.0643   0.8622   0.0182
  -5.000  -0.2285   0.01665   0.01221  -0.0635   0.8435   0.0190
  -4.750  -0.2042   0.01566   0.01099  -0.0628   0.8266   0.0200
  -4.500  -0.1813   0.01171   0.00641  -0.0605   0.8119   0.0137
  -4.250  -0.1558   0.01106   0.00563  -0.0599   0.7973   0.0140
  -3.750  -0.1043   0.00993   0.00426  -0.0589   0.7707   0.0141
  -3.500  -0.0782   0.00950   0.00374  -0.0584   0.7585   0.0144
  -3.250  -0.0517   0.00915   0.00331  -0.0580   0.7469   0.0149
  -3.000  -0.0253   0.00881   0.00287  -0.0576   0.7360   0.0151
  -2.750   0.0014   0.00852   0.00248  -0.0572   0.7254   0.0154
  -2.500   0.0285   0.00827   0.00216  -0.0570   0.7150   0.0160
  -2.250   0.0557   0.00807   0.00189  -0.0567   0.7050   0.0166
  -2.000   0.0828   0.00787   0.00158  -0.0564   0.6953   0.0184
  -1.750   0.1103   0.00773   0.00141  -0.0562   0.6855   0.0208
  -1.500   0.1373   0.00750   0.00125  -0.0560   0.6761   0.0515
  -1.250   0.1626   0.00698   0.00113  -0.0557   0.6667   0.1804
  -1.000   0.1889   0.00665   0.00107  -0.0555   0.6568   0.2755
  -0.750   0.2150   0.00634   0.00104  -0.0553   0.6477   0.3784
  -0.500   0.2407   0.00605   0.00101  -0.0550   0.6384   0.4828
  -0.250   0.2656   0.00564   0.00101  -0.0545   0.6292   0.6233
   0.000   0.2829   0.00493   0.00108  -0.0520   0.6208   0.8719
   0.250   0.3177   0.00491   0.00117  -0.0529   0.6113   0.9715
   0.500   0.3549   0.00497   0.00118  -0.0549   0.6016   0.9839
   0.750   0.3995   0.00504   0.00117  -0.0585   0.5912   0.9897
   1.000   0.4409   0.00512   0.00117  -0.0615   0.5804   0.9955
   1.250   0.4832   0.00516   0.00115  -0.0647   0.5691   0.9995
   1.500   0.5107   0.00522   0.00116  -0.0646   0.5585   1.0000
   1.750   0.5357   0.00529   0.00119  -0.0640   0.5475   1.0000
   2.000   0.5607   0.00538   0.00122  -0.0634   0.5364   1.0000
   2.250   0.5857   0.00546   0.00125  -0.0628   0.5246   1.0000
   2.500   0.6108   0.00555   0.00130  -0.0622   0.5116   1.0000
   2.750   0.6358   0.00566   0.00136  -0.0616   0.4986   1.0000
   3.000   0.6608   0.00577   0.00142  -0.0610   0.4849   1.0000
   3.250   0.6856   0.00590   0.00150  -0.0604   0.4699   1.0000
   3.500   0.7104   0.00604   0.00159  -0.0597   0.4542   1.0000
   4.000   0.7597   0.00636   0.00179  -0.0585   0.4201   1.0000
   4.250   0.7842   0.00655   0.00191  -0.0578   0.4003   1.0000
   4.500   0.8084   0.00676   0.00206  -0.0572   0.3805   1.0000
   4.750   0.8327   0.00697   0.00220  -0.0565   0.3594   1.0000
   5.000   0.8567   0.00723   0.00237  -0.0558   0.3379   1.0000
   5.250   0.8798   0.00756   0.00257  -0.0550   0.3064   1.0000
   5.500   0.9026   0.00796   0.00281  -0.0542   0.2711   1.0000
   5.750   0.9257   0.00833   0.00306  -0.0534   0.2421   1.0000
   6.000   0.9494   0.00866   0.00330  -0.0528   0.2203   1.0000
   6.250   0.9726   0.00905   0.00357  -0.0521   0.1951   1.0000
   6.500   0.9951   0.00950   0.00388  -0.0513   0.1657   1.0000
   6.750   1.0169   0.01002   0.00424  -0.0504   0.1339   1.0000
   7.000   1.0388   0.01053   0.00461  -0.0496   0.1073   1.0000
   7.250   1.0586   0.01124   0.00511  -0.0485   0.0721   1.0000
   7.500   1.0771   0.01208   0.00572  -0.0471   0.0378   1.0000
   7.750   1.0935   0.01312   0.00656  -0.0454   0.0097   1.0000
   8.000   1.1163   0.01353   0.00701  -0.0447   0.0088   1.0000
   8.250   1.1382   0.01400   0.00753  -0.0438   0.0080   1.0000
   8.500   1.1591   0.01455   0.00814  -0.0427   0.0074   1.0000
   8.750   1.1777   0.01530   0.00899  -0.0413   0.0068   1.0000
   9.000   1.1979   0.01587   0.00963  -0.0402   0.0066   1.0000
   9.250   1.2177   0.01644   0.01025  -0.0391   0.0063   1.0000
   9.500   1.2359   0.01710   0.01098  -0.0377   0.0062   1.0000
   9.750   1.2523   0.01786   0.01182  -0.0361   0.0060   1.0000
  10.000   1.2688   0.01855   0.01258  -0.0346   0.0058   1.0000
  10.250   1.2823   0.01940   0.01351  -0.0326   0.0057   1.0000
  10.500   1.2928   0.02023   0.01444  -0.0301   0.0057   1.0000
  10.750   1.2993   0.02116   0.01545  -0.0270   0.0056   1.0000
  11.000   1.3063   0.02211   0.01648  -0.0243   0.0054   1.0000
  11.250   1.3112   0.02325   0.01771  -0.0215   0.0054   1.0000
  11.500   1.3163   0.02445   0.01899  -0.0191   0.0053   1.0000
  11.750   1.3201   0.02582   0.02044  -0.0169   0.0051   1.0000
  12.000   1.3223   0.02743   0.02215  -0.0148   0.0051   1.0000
  12.250   1.3239   0.02923   0.02403  -0.0131   0.0051   1.0000
  12.500   1.3216   0.03149   0.02638  -0.0115   0.0049   1.0000
  12.750   1.3169   0.03417   0.02916  -0.0102   0.0048   1.0000
  13.000   1.3193   0.03633   0.03142  -0.0094   0.0048   1.0000
  13.250   1.3102   0.03980   0.03501  -0.0084   0.0047   1.0000
  13.500   1.3024   0.04334   0.03869  -0.0077   0.0046   1.0000
  13.750   1.2931   0.04731   0.04282  -0.0070   0.0045   1.0000
  14.000   1.2993   0.04932   0.04490  -0.0075   0.0046   1.0000
  14.250   1.2900   0.05347   0.04924  -0.0079   0.0045   1.0000
  14.750   1.2770   0.06149   0.05752  -0.0091   0.0045   1.0000
  15.000   1.2704   0.06575   0.06191  -0.0097   0.0045   1.0000
  15.250   1.2604   0.07069   0.06699  -0.0112   0.0045   1.0000
  15.500   1.2563   0.07489   0.07130  -0.0130   0.0046   1.0000
  15.750   1.2435   0.08073   0.07730  -0.0154   0.0046   1.0000
  16.000   1.2387   0.08545   0.08212  -0.0178   0.0046   1.0000
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