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NREL's S821 Airfoil (s821-nr) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: NREL's S821 Airfoil (s821-nr)
Reynolds number: 200,000
Max Cl/Cd: 52.79 at α=8.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s821-nr-200000.txt
Download as CSV file: xf-s821-nr-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NREL's S821 Airfoil                             
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -5.000   0.1241   0.09980   0.09497  -0.0610   0.9452   0.2525
  -4.750   0.1529   0.09720   0.09239  -0.0650   0.9421   0.2563
  -3.250  -0.1418   0.03053   0.02424  -0.1096   0.8539   0.2630
  -3.000  -0.0985   0.02996   0.02375  -0.1122   0.8463   0.2642
  -2.750  -0.0592   0.02939   0.02321  -0.1143   0.8360   0.2655
  -2.500  -0.0135   0.02846   0.02224  -0.1185   0.8270   0.2672
  -2.250   0.0155   0.02734   0.02103  -0.1204   0.8130   0.2690
  -2.000   0.0429   0.02592   0.01945  -0.1229   0.7996   0.2713
  -1.750   0.0762   0.02444   0.01771  -0.1264   0.7873   0.2743
  -1.500   0.0988   0.02339   0.01642  -0.1274   0.7723   0.2766
  -1.250   0.1314   0.02244   0.01534  -0.1292   0.7603   0.2786
  -1.000   0.1563   0.02210   0.01504  -0.1287   0.7465   0.2801
  -0.750   0.1860   0.02191   0.01484  -0.1290   0.7347   0.2817
  -0.500   0.2129   0.02170   0.01462  -0.1288   0.7222   0.2834
  -0.250   0.2412   0.02144   0.01431  -0.1291   0.7104   0.2855
   0.000   0.2687   0.02110   0.01389  -0.1293   0.6983   0.2878
   0.250   0.2974   0.02076   0.01344  -0.1298   0.6870   0.2904
   0.500   0.3259   0.02044   0.01298  -0.1303   0.6756   0.2930
   0.750   0.3554   0.02005   0.01252  -0.1309   0.6656   0.2956
   1.000   0.3805   0.01991   0.01246  -0.1302   0.6545   0.2977
   1.250   0.4111   0.01991   0.01243  -0.1305   0.6449   0.3001
   1.500   0.4356   0.01981   0.01240  -0.1298   0.6340   0.3025
   1.750   0.4664   0.01971   0.01221  -0.1303   0.6250   0.3056
   2.000   0.4941   0.01958   0.01204  -0.1303   0.6153   0.3087
   2.250   0.5236   0.01947   0.01181  -0.1306   0.6056   0.3116
   2.500   0.5532   0.01927   0.01164  -0.1309   0.5972   0.3148
   2.750   0.5778   0.01928   0.01178  -0.1300   0.5878   0.3176
   3.000   0.6072   0.01935   0.01183  -0.1300   0.5790   0.3212
   3.250   0.6342   0.01938   0.01187  -0.1297   0.5696   0.3253
   3.500   0.6625   0.01934   0.01174  -0.1296   0.5598   0.3293
   3.750   0.6920   0.01924   0.01163  -0.1297   0.5510   0.3331
   4.000   0.7154   0.01924   0.01177  -0.1286   0.5410   0.3364
   4.250   0.7446   0.01933   0.01181  -0.1284   0.5320   0.3405
   4.500   0.7694   0.01936   0.01189  -0.1276   0.5224   0.3450
   4.750   0.7975   0.01939   0.01182  -0.1274   0.5129   0.3495
   5.000   0.8239   0.01936   0.01187  -0.1269   0.5040   0.3539
   5.250   0.8467   0.01942   0.01205  -0.1256   0.4940   0.3581
   5.500   0.8754   0.01958   0.01213  -0.1254   0.4849   0.3634
   5.750   0.8980   0.01962   0.01222  -0.1241   0.4748   0.3686
   6.000   0.9246   0.01961   0.01220  -0.1236   0.4655   0.3735
   6.250   0.9460   0.01971   0.01244  -0.1221   0.4557   0.3777
   6.500   0.9693   0.01981   0.01256  -0.1209   0.4456   0.3828
   6.750   0.9922   0.01995   0.01269  -0.1197   0.4352   0.3885
   7.000   1.0140   0.01998   0.01273  -0.1183   0.4242   0.3938
   7.250   1.0333   0.02011   0.01298  -0.1164   0.4132   0.3985
   7.500   1.0521   0.02029   0.01316  -0.1145   0.4015   0.4039
   7.750   1.0681   0.02043   0.01335  -0.1121   0.3889   0.4097
   8.000   1.0840   0.02060   0.01345  -0.1098   0.3763   0.4150
   8.250   1.0965   0.02077   0.01373  -0.1069   0.3619   0.4197
   8.500   1.1094   0.02111   0.01412  -0.1041   0.3464   0.4250
   8.750   1.1221   0.02153   0.01452  -0.1015   0.3293   0.4310
   9.000   1.1337   0.02206   0.01496  -0.0988   0.3098   0.4365
   9.250   1.1425   0.02260   0.01552  -0.0959   0.2884   0.4416
   9.500   1.1484   0.02341   0.01627  -0.0927   0.2662   0.4466
   9.750   1.1526   0.02442   0.01715  -0.0895   0.2451   0.4521
  10.000   1.1582   0.02552   0.01814  -0.0867   0.2249   0.4579
  10.250   1.1630   0.02667   0.01924  -0.0841   0.2074   0.4631
  10.500   1.1666   0.02797   0.02051  -0.0814   0.1925   0.4680
  10.750   1.1697   0.02942   0.02189  -0.0789   0.1797   0.4736
  11.000   1.1760   0.03081   0.02326  -0.0770   0.1676   0.4800
  11.250   1.1824   0.03225   0.02470  -0.0752   0.1572   0.4859
  11.500   1.1863   0.03388   0.02634  -0.0734   0.1484   0.4912
  11.750   1.1905   0.03560   0.02807  -0.0718   0.1405   0.4972
  12.000   1.1973   0.03728   0.02976  -0.0705   0.1328   0.5042
  12.250   1.1998   0.03932   0.03174  -0.0693   0.1267   0.5101
  12.500   1.2073   0.04101   0.03358  -0.0683   0.1200   0.5165
  12.750   1.2102   0.04319   0.03573  -0.0673   0.1148   0.5232
  13.000   1.2172   0.04517   0.03776  -0.0667   0.1091   0.5305
  13.250   1.2206   0.04741   0.04003  -0.0660   0.1046   0.5366
  13.500   1.2265   0.04955   0.04227  -0.0655   0.0996   0.5439
  13.750   1.2297   0.05203   0.04470  -0.0651   0.0956   0.5517
  14.000   1.2358   0.05432   0.04714  -0.0649   0.0911   0.5591
  14.250   1.2390   0.05689   0.04967  -0.0646   0.0876   0.5664
  14.500   1.2443   0.05944   0.05235  -0.0647   0.0835   0.5751
  14.750   1.2485   0.06206   0.05499  -0.0647   0.0803   0.5827
  15.000   1.2527   0.06480   0.05784  -0.0648   0.0767   0.5912
  15.250   1.2570   0.06762   0.06068  -0.0652   0.0736   0.6008
  15.500   1.2614   0.07039   0.06353  -0.0654   0.0707   0.6092
  15.750   1.2652   0.07341   0.06665  -0.0659   0.0677   0.6194
  16.000   1.2713   0.07602   0.06922  -0.0662   0.0653   0.6291
  16.250   1.2738   0.07937   0.07277  -0.0670   0.0626   0.6397
  16.500   1.2785   0.08237   0.07582  -0.0677   0.0603   0.6506
  16.750   1.2841   0.08524   0.07873  -0.0682   0.0582   0.6633
  17.000   1.2866   0.08869   0.08235  -0.0692   0.0560   0.6749
  17.250   1.2925   0.09161   0.08529  -0.0700   0.0542   0.6894
  17.500   1.2979   0.09456   0.08832  -0.0707   0.0524   0.7045
  17.750   1.2998   0.09818   0.09213  -0.0720   0.0507   0.7200
  18.000   1.3050   0.10121   0.09524  -0.0729   0.0492   0.7397
  18.250   1.3167   0.10288   0.09686  -0.0727   0.0478   0.7675
  18.500   1.3134   0.10694   0.10122  -0.0740   0.0466   0.7964
  18.750   1.3041   0.10914   0.10373  -0.0723   0.0457   0.9126
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