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S3021-095-84 (s3021-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: S3021-095-84 (s3021-il)
Reynolds number: 200,000
Max Cl/Cd: 71.57 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s3021-il-200000-n5.txt
Download as CSV file: xf-s3021-il-200000-n5.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 =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.3968   0.07954   0.07620  -0.0325   1.0000   0.0316
  -7.500  -0.4282   0.06412   0.06086  -0.0425   1.0000   0.0191
  -7.250  -0.4317   0.06002   0.05676  -0.0435   1.0000   0.0187
  -7.000  -0.4351   0.05581   0.05251  -0.0439   1.0000   0.0183
  -6.750  -0.4173   0.04921   0.04567  -0.0496   0.9918   0.0176
  -6.500  -0.3946   0.04143   0.03747  -0.0555   0.9818   0.0170
  -6.250  -0.3714   0.03486   0.03036  -0.0589   0.9716   0.0165
  -6.000  -0.3482   0.02993   0.02485  -0.0604   0.9598   0.0163
  -5.750  -0.3227   0.02631   0.02068  -0.0612   0.9483   0.0163
  -5.500  -0.2945   0.02377   0.01767  -0.0619   0.9375   0.0167
  -5.250  -0.2645   0.02199   0.01549  -0.0626   0.9267   0.0179
  -5.000  -0.2347   0.02030   0.01343  -0.0630   0.9150   0.0184
  -4.750  -0.2057   0.01875   0.01157  -0.0632   0.9023   0.0184
  -4.500  -0.1768   0.01748   0.01004  -0.0632   0.8891   0.0185
  -4.250  -0.1487   0.01640   0.00878  -0.0631   0.8755   0.0187
  -4.000  -0.1215   0.01551   0.00774  -0.0627   0.8616   0.0190
  -3.750  -0.0951   0.01476   0.00686  -0.0622   0.8478   0.0193
  -3.500  -0.0694   0.01407   0.00606  -0.0616   0.8340   0.0198
  -3.250  -0.0441   0.01344   0.00529  -0.0610   0.8208   0.0208
  -3.000  -0.0182   0.01301   0.00474  -0.0605   0.8080   0.0221
  -2.750   0.0081   0.01271   0.00433  -0.0600   0.7957   0.0252
  -2.500   0.0343   0.01241   0.00391  -0.0595   0.7839   0.0283
  -2.250   0.0606   0.01211   0.00354  -0.0590   0.7723   0.0348
  -2.000   0.0861   0.01165   0.00323  -0.0585   0.7611   0.0818
  -1.750   0.1109   0.01115   0.00305  -0.0581   0.7504   0.1777
  -1.500   0.1356   0.01070   0.00292  -0.0576   0.7402   0.2850
  -1.250   0.1578   0.01003   0.00286  -0.0568   0.7299   0.4590
  -1.000   0.1733   0.00901   0.00293  -0.0537   0.7202   0.7481
  -0.750   0.2221   0.00878   0.00294  -0.0570   0.7108   0.9194
  -0.500   0.2658   0.00883   0.00283  -0.0600   0.7005   0.9678
  -0.250   0.3116   0.00885   0.00271  -0.0638   0.6899   0.9914
   0.000   0.3472   0.00890   0.00261  -0.0655   0.6795   1.0000
   0.250   0.3715   0.00898   0.00256  -0.0647   0.6695   1.0000
   0.500   0.3960   0.00905   0.00254  -0.0640   0.6585   1.0000
   0.750   0.4205   0.00914   0.00253  -0.0633   0.6477   1.0000
   1.000   0.4451   0.00923   0.00253  -0.0625   0.6372   1.0000
   1.250   0.4697   0.00934   0.00254  -0.0618   0.6269   1.0000
   1.500   0.4944   0.00943   0.00258  -0.0612   0.6157   1.0000
   1.750   0.5192   0.00954   0.00263  -0.0605   0.6047   1.0000
   2.000   0.5439   0.00965   0.00269  -0.0598   0.5939   1.0000
   2.250   0.5686   0.00978   0.00275  -0.0591   0.5827   1.0000
   2.500   0.5933   0.00990   0.00283  -0.0584   0.5710   1.0000
   2.750   0.6181   0.01003   0.00293  -0.0578   0.5587   1.0000
   3.000   0.6429   0.01017   0.00304  -0.0571   0.5460   1.0000
   3.250   0.6676   0.01032   0.00315  -0.0565   0.5327   1.0000
   3.500   0.6922   0.01047   0.00328  -0.0558   0.5186   1.0000
   3.750   0.7168   0.01064   0.00343  -0.0551   0.5039   1.0000
   4.000   0.7412   0.01083   0.00359  -0.0544   0.4882   1.0000
   4.250   0.7655   0.01103   0.00375  -0.0537   0.4717   1.0000
   4.500   0.7897   0.01124   0.00394  -0.0530   0.4541   1.0000
   4.750   0.8137   0.01148   0.00417  -0.0523   0.4351   1.0000
   5.000   0.8373   0.01174   0.00439  -0.0515   0.4157   1.0000
   5.250   0.8608   0.01203   0.00464  -0.0508   0.3948   1.0000
   5.500   0.8839   0.01235   0.00492  -0.0500   0.3732   1.0000
   5.750   0.9069   0.01269   0.00525  -0.0492   0.3510   1.0000
   6.000   0.9291   0.01309   0.00559  -0.0483   0.3278   1.0000
   6.250   0.9515   0.01349   0.00596  -0.0474   0.3054   1.0000
   6.500   0.9734   0.01394   0.00636  -0.0465   0.2834   1.0000
   6.750   0.9940   0.01448   0.00681  -0.0455   0.2551   1.0000
   7.000   1.0136   0.01510   0.00733  -0.0444   0.2219   1.0000
   7.250   1.0331   0.01575   0.00786  -0.0432   0.1919   1.0000
   7.750   1.0693   0.01728   0.00908  -0.0408   0.1278   1.0000
   8.000   1.0877   0.01802   0.00974  -0.0396   0.1059   1.0000
   8.250   1.1048   0.01884   0.01047  -0.0382   0.0837   1.0000
   8.500   1.1198   0.01984   0.01136  -0.0366   0.0568   1.0000
   8.750   1.1330   0.02095   0.01234  -0.0348   0.0336   1.0000
   9.000   1.1444   0.02218   0.01349  -0.0327   0.0187   1.0000
   9.250   1.1570   0.02323   0.01457  -0.0308   0.0145   1.0000
   9.500   1.1689   0.02425   0.01567  -0.0288   0.0123   1.0000
   9.750   1.1769   0.02537   0.01689  -0.0262   0.0111   1.0000
  10.000   1.1862   0.02639   0.01804  -0.0239   0.0108   1.0000
  10.250   1.1942   0.02753   0.01932  -0.0217   0.0104   1.0000
  10.500   1.2005   0.02882   0.02080  -0.0195   0.0101   1.0000
  10.750   1.2056   0.03026   0.02238  -0.0174   0.0098   1.0000
  11.000   1.2089   0.03191   0.02418  -0.0156   0.0095   1.0000
  11.250   1.2115   0.03373   0.02614  -0.0140   0.0093   1.0000
  11.500   1.2129   0.03576   0.02831  -0.0127   0.0091   1.0000
  11.750   1.2129   0.03806   0.03076  -0.0116   0.0089   1.0000
  12.000   1.2139   0.04039   0.03323  -0.0109   0.0088   1.0000
  12.250   1.2123   0.04313   0.03609  -0.0103   0.0086   1.0000
  12.500   1.2109   0.04598   0.03908  -0.0100   0.0085   1.0000
  12.750   1.2100   0.04886   0.04209  -0.0100   0.0085   1.0000
  13.000   1.2073   0.05209   0.04545  -0.0101   0.0084   1.0000
  13.250   1.2039   0.05551   0.04901  -0.0104   0.0083   1.0000
  13.500   1.2015   0.05890   0.05253  -0.0109   0.0082   1.0000
  13.750   1.1981   0.06253   0.05632  -0.0115   0.0081   1.0000
  14.000   1.1944   0.06632   0.06026  -0.0123   0.0081   1.0000
  14.250   1.1893   0.07043   0.06450  -0.0135   0.0079   1.0000
  14.500   1.1817   0.07502   0.06923  -0.0148   0.0077   1.0000
  14.750   1.1773   0.07935   0.07372  -0.0163   0.0077   1.0000
  15.000   1.1675   0.08467   0.07920  -0.0181   0.0075   1.0000
  15.250   1.1593   0.09001   0.08469  -0.0204   0.0075   1.0000
  15.500   1.1515   0.09553   0.09039  -0.0231   0.0074   1.0000
  15.750   1.1422   0.10156   0.09661  -0.0262   0.0073   1.0000
  16.000   1.1330   0.10769   0.10290  -0.0294   0.0074   1.0000
  16.250   1.1232   0.11419   0.10957  -0.0330   0.0073   1.0000
  16.500   1.1115   0.12147   0.11703  -0.0373   0.0072   1.0000
  16.750   1.1006   0.12863   0.12434  -0.0414   0.0073   1.0000
  17.000   1.0893   0.13610   0.13195  -0.0457   0.0073   1.0000
  17.250   1.0766   0.14429   0.14030  -0.0507   0.0073   1.0000
  17.500   1.0640   0.15280   0.14895  -0.0559   0.0074   1.0000
  17.750   1.0512   0.16170   0.15797  -0.0613   0.0074   1.0000
  18.000   1.0369   0.17157   0.16795  -0.0672   0.0074   1.0000
  18.250   1.0224   0.18261   0.17914  -0.0736   0.0077   1.0000
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