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

NREL's S822 Airfoil (s822-nr) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: NREL's S822 Airfoil (s822-nr)
Reynolds number: 1,000,000
Max Cl/Cd: 117.05 at α=4.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s822-nr-1000000.txt
Download as CSV file: xf-s822-nr-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NREL's S822 Airfoil                             
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -18.500  -0.8604   0.09772   0.09457  -0.0661   1.0000   0.0046
 -18.250  -0.8835   0.09041   0.08715  -0.0696   1.0000   0.0047
 -18.000  -0.9171   0.08157   0.07817  -0.0738   1.0000   0.0048
 -17.750  -0.9280   0.07652   0.07301  -0.0761   1.0000   0.0048
 -17.500  -0.9483   0.07010   0.06648  -0.0791   1.0000   0.0048
 -17.250  -0.9473   0.06698   0.06329  -0.0804   1.0000   0.0046
 -17.000  -0.9762   0.05973   0.05589  -0.0836   1.0000   0.0048
 -16.750  -0.9802   0.05612   0.05219  -0.0850   1.0000   0.0047
 -16.500  -0.9987   0.05083   0.04678  -0.0869   1.0000   0.0049
 -16.250  -1.0072   0.04706   0.04291  -0.0880   1.0000   0.0049
 -16.000  -1.0148   0.04363   0.03939  -0.0887   1.0000   0.0051
 -15.750  -1.0200   0.04073   0.03640  -0.0889   1.0000   0.0051
 -15.500  -1.0260   0.03798   0.03356  -0.0886   1.0000   0.0052
 -15.250  -1.0298   0.03566   0.03116  -0.0880   1.0000   0.0052
 -15.000  -1.0323   0.03366   0.02910  -0.0869   1.0000   0.0054
 -14.750  -1.0368   0.03179   0.02716  -0.0853   1.0000   0.0054
 -14.500  -1.0217   0.03007   0.02536  -0.0868   0.9987   0.0059
 -14.250  -1.0020   0.02819   0.02340  -0.0894   0.9950   0.0061
 -14.000  -0.9840   0.02654   0.02167  -0.0911   0.9880   0.0064
 -13.750  -0.9701   0.02430   0.01932  -0.0932   0.9804   0.0071
 -13.500  -0.9461   0.02290   0.01786  -0.0956   0.9723   0.0078
 -13.250  -0.9166   0.02167   0.01656  -0.0987   0.9656   0.0083
 -13.000  -0.8872   0.02032   0.01513  -0.1020   0.9563   0.0097
 -12.750  -0.8595   0.01925   0.01398  -0.1044   0.9434   0.0108
 -12.500  -0.8394   0.01849   0.01311  -0.1047   0.9288   0.0116
 -12.250  -0.8274   0.01778   0.01229  -0.1033   0.9159   0.0129
 -12.000  -0.8161   0.01714   0.01160  -0.1016   0.9065   0.0143
 -11.750  -0.8024   0.01665   0.01103  -0.1001   0.8990   0.0156
 -11.500  -0.7909   0.01605   0.01038  -0.0983   0.8924   0.0173
 -11.250  -0.7786   0.01552   0.00981  -0.0964   0.8863   0.0190
 -11.000  -0.7641   0.01509   0.00932  -0.0948   0.8810   0.0204
 -10.750  -0.7504   0.01463   0.00881  -0.0930   0.8760   0.0222
 -10.500  -0.7378   0.01416   0.00832  -0.0909   0.8710   0.0248
 -10.250  -0.7227   0.01382   0.00792  -0.0892   0.8666   0.0269
 -10.000  -0.7097   0.01342   0.00752  -0.0870   0.8627   0.0303
  -9.750  -0.6952   0.01309   0.00718  -0.0849   0.8588   0.0337
  -9.500  -0.6770   0.01277   0.00684  -0.0836   0.8554   0.0378
  -9.250  -0.6584   0.01242   0.00650  -0.0824   0.8520   0.0442
  -9.000  -0.6395   0.01204   0.00615  -0.0812   0.8493   0.0519
  -8.750  -0.6188   0.01172   0.00585  -0.0803   0.8463   0.0595
  -8.500  -0.5976   0.01141   0.00555  -0.0794   0.8434   0.0678
  -8.250  -0.5765   0.01107   0.00525  -0.0786   0.8407   0.0787
  -8.000  -0.5545   0.01078   0.00498  -0.0779   0.8379   0.0901
  -7.750  -0.5321   0.01048   0.00473  -0.0773   0.8355   0.1027
  -7.500  -0.5092   0.01018   0.00449  -0.0767   0.8329   0.1163
  -7.250  -0.4858   0.00991   0.00425  -0.0762   0.8302   0.1301
  -7.000  -0.4621   0.00964   0.00403  -0.0757   0.8276   0.1455
  -6.750  -0.4379   0.00939   0.00383  -0.0754   0.8252   0.1617
  -6.500  -0.4130   0.00919   0.00364  -0.0751   0.8226   0.1778
  -6.250  -0.3887   0.00893   0.00346  -0.0747   0.8204   0.1969
  -6.000  -0.3642   0.00867   0.00329  -0.0744   0.8179   0.2187
  -5.750  -0.3389   0.00845   0.00312  -0.0742   0.8152   0.2383
  -5.500  -0.3136   0.00822   0.00296  -0.0740   0.8126   0.2597
  -5.250  -0.2877   0.00803   0.00281  -0.0739   0.8102   0.2810
  -5.000  -0.2616   0.00786   0.00269  -0.0738   0.8076   0.3028
  -4.750  -0.2357   0.00766   0.00258  -0.0737   0.8054   0.3262
  -4.500  -0.2095   0.00747   0.00246  -0.0736   0.8028   0.3474
  -4.250  -0.1829   0.00730   0.00235  -0.0736   0.8000   0.3712
  -4.000  -0.1563   0.00712   0.00224  -0.0736   0.7973   0.3941
  -3.750  -0.1292   0.00698   0.00214  -0.0737   0.7947   0.4180
  -3.500  -0.1021   0.00685   0.00207  -0.0737   0.7921   0.4414
  -3.250  -0.0752   0.00670   0.00200  -0.0738   0.7895   0.4653
  -3.000  -0.0481   0.00656   0.00193  -0.0738   0.7866   0.4895
  -2.750  -0.0207   0.00642   0.00186  -0.0739   0.7837   0.5126
  -2.500   0.0070   0.00632   0.00181  -0.0740   0.7809   0.5365
  -2.250   0.0349   0.00624   0.00178  -0.0742   0.7779   0.5597
  -2.000   0.0626   0.00616   0.00176  -0.0743   0.7751   0.5803
  -1.750   0.0907   0.00610   0.00174  -0.0745   0.7720   0.5980
  -1.500   0.1191   0.00604   0.00172  -0.0747   0.7689   0.6137
  -1.250   0.1477   0.00602   0.00170  -0.0750   0.7658   0.6273
  -1.000   0.1764   0.00601   0.00170  -0.0753   0.7627   0.6393
  -0.750   0.2045   0.00597   0.00171  -0.0754   0.7594   0.6500
  -0.500   0.2331   0.00595   0.00170  -0.0757   0.7559   0.6600
  -0.250   0.2616   0.00593   0.00170  -0.0759   0.7525   0.6696
   0.000   0.2906   0.00594   0.00170  -0.0762   0.7488   0.6781
   0.250   0.3183   0.00590   0.00170  -0.0763   0.7437   0.6869
   0.500   0.3461   0.00586   0.00168  -0.0763   0.7376   0.6948
   0.750   0.3742   0.00586   0.00167  -0.0765   0.7316   0.7029
   1.000   0.4018   0.00583   0.00168  -0.0765   0.7253   0.7104
   1.250   0.4300   0.00586   0.00168  -0.0766   0.7197   0.7182
   1.500   0.4575   0.00583   0.00172  -0.0766   0.7132   0.7254
   1.750   0.4853   0.00586   0.00173  -0.0767   0.7068   0.7329
   2.000   0.5128   0.00586   0.00178  -0.0767   0.7000   0.7399
   2.250   0.5402   0.00590   0.00181  -0.0767   0.6929   0.7474
   2.500   0.5674   0.00592   0.00187  -0.0766   0.6855   0.7542
   2.750   0.5943   0.00598   0.00192  -0.0765   0.6773   0.7616
   3.000   0.6211   0.00602   0.00199  -0.0764   0.6686   0.7681
   3.250   0.6474   0.00610   0.00206  -0.0761   0.6598   0.7753
   3.500   0.6735   0.00616   0.00214  -0.0758   0.6497   0.7817
   3.750   0.6990   0.00625   0.00223  -0.0754   0.6376   0.7884
   4.000   0.7241   0.00635   0.00233  -0.0749   0.6245   0.7950
   4.250   0.7484   0.00647   0.00244  -0.0743   0.6103   0.8011
   4.500   0.7725   0.00661   0.00255  -0.0736   0.5947   0.8077
   4.750   0.7936   0.00678   0.00270  -0.0723   0.5731   0.8134
   5.000   0.8128   0.00703   0.00286  -0.0707   0.5421   0.8199
   5.250   0.8250   0.00745   0.00310  -0.0677   0.4926   0.8263
   5.500   0.8321   0.00802   0.00344  -0.0638   0.4400   0.8334
   5.750   0.8380   0.00850   0.00374  -0.0596   0.3962   0.8405
   6.000   0.8446   0.00902   0.00411  -0.0556   0.3537   0.8473
   6.250   0.8538   0.00956   0.00448  -0.0523   0.3161   0.8540
   6.500   0.8637   0.01005   0.00486  -0.0491   0.2827   0.8601
   6.750   0.8747   0.01058   0.00526  -0.0463   0.2513   0.8667
   7.000   0.8859   0.01107   0.00566  -0.0436   0.2235   0.8728
   7.250   0.8961   0.01165   0.00611  -0.0407   0.1941   0.8794
   7.500   0.9078   0.01218   0.00655  -0.0382   0.1704   0.8857
   7.750   0.9192   0.01273   0.00701  -0.0357   0.1478   0.8927
   8.000   0.9324   0.01325   0.00747  -0.0336   0.1306   0.8996
   8.250   0.9453   0.01374   0.00794  -0.0314   0.1156   0.9069
   8.500   0.9589   0.01426   0.00842  -0.0294   0.1019   0.9146
   8.750   0.9710   0.01479   0.00892  -0.0271   0.0889   0.9241
   9.000   0.9834   0.01528   0.00942  -0.0249   0.0792   0.9357
   9.250   0.9973   0.01575   0.00991  -0.0230   0.0707   0.9532
   9.500   1.0236   0.01633   0.01049  -0.0239   0.0615   0.9799
   9.750   1.0403   0.01699   0.01111  -0.0229   0.0531   1.0000
  10.000   1.0580   0.01757   0.01168  -0.0220   0.0482   1.0000
  10.250   1.0733   0.01827   0.01235  -0.0208   0.0417   1.0000
  10.500   1.0887   0.01896   0.01300  -0.0196   0.0366   1.0000
  10.750   1.1037   0.01968   0.01372  -0.0184   0.0326   1.0000
  11.000   1.1194   0.02037   0.01441  -0.0173   0.0297   1.0000
  11.250   1.1313   0.02129   0.01531  -0.0158   0.0255   1.0000
  11.500   1.1482   0.02191   0.01595  -0.0149   0.0234   1.0000
  11.750   1.1616   0.02275   0.01680  -0.0136   0.0215   1.0000
  12.000   1.1741   0.02368   0.01773  -0.0123   0.0191   1.0000
  12.250   1.1894   0.02442   0.01851  -0.0113   0.0182   1.0000
  12.500   1.2032   0.02528   0.01939  -0.0102   0.0171   1.0000
  12.750   1.2152   0.02627   0.02038  -0.0090   0.0157   1.0000
  13.000   1.2244   0.02749   0.02165  -0.0076   0.0146   1.0000
  13.250   1.2391   0.02833   0.02254  -0.0067   0.0141   1.0000
  13.500   1.2517   0.02933   0.02359  -0.0057   0.0135   1.0000
  13.750   1.2644   0.03034   0.02463  -0.0048   0.0128   1.0000
  14.000   1.2749   0.03154   0.02585  -0.0038   0.0121   1.0000
  14.250   1.2818   0.03306   0.02741  -0.0025   0.0111   1.0000
  14.500   1.2910   0.03443   0.02885  -0.0015   0.0107   1.0000
  14.750   1.3024   0.03565   0.03013  -0.0007   0.0104   1.0000
  15.000   1.3140   0.03687   0.03139   0.0000   0.0099   1.0000
  15.250   1.3227   0.03837   0.03294   0.0007   0.0095   1.0000
  15.500   1.3308   0.03996   0.03459   0.0015   0.0090   1.0000
  15.750   1.3371   0.04176   0.03643   0.0022   0.0085   1.0000
  16.000   1.3371   0.04420   0.03896   0.0031   0.0080   1.0000
  16.250   1.3465   0.04579   0.04061   0.0035   0.0077   1.0000
  16.500   1.3536   0.04766   0.04255   0.0039   0.0074   1.0000
  16.750   1.3596   0.04968   0.04464   0.0042   0.0070   1.0000
  17.000   1.3651   0.05180   0.04683   0.0044   0.0067   1.0000
  17.250   1.3687   0.05418   0.04926   0.0045   0.0063   1.0000
  17.500   1.3699   0.05688   0.05203   0.0045   0.0060   1.0000
  17.750   1.3625   0.06071   0.05597   0.0044   0.0056   1.0000
  18.000   1.3619   0.06384   0.05919   0.0040   0.0055   1.0000
  18.250   1.3642   0.06669   0.06213   0.0036   0.0054   1.0000
  18.500   1.3633   0.07002   0.06557   0.0029   0.0052   1.0000
  18.750   1.3633   0.07332   0.06896   0.0021   0.0050   1.0000
  19.000   1.3593   0.07729   0.07302   0.0009   0.0047   1.0000
  19.250   1.3539   0.08159   0.07744  -0.0005   0.0047   1.0000
<< Back to NREL's S822 Airfoil (s822-nr)

Polar data table (+)

Polar graphs


<< Back to NREL's S822 Airfoil (s822-nr)