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NREL's S802 Airfoil (s802-nr) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: NREL's S802 Airfoil (s802-nr)
Reynolds number: 500,000
Max Cl/Cd: 113.64 at α=3.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s802-nr-500000-n5.txt
Download as CSV file: xf-s802-nr-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NREL's S802 Airfoil                             
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.3110   0.08199   0.07960  -0.0735   0.9804   0.0101
  -9.500  -0.3160   0.07562   0.07326  -0.0778   0.9707   0.0102
  -9.250  -0.4282   0.03295   0.02977  -0.1187   0.9264   0.0102
  -9.000  -0.4041   0.02667   0.02279  -0.1259   0.9168   0.0109
  -8.750  -0.3741   0.02324   0.01877  -0.1300   0.9060   0.0116
  -8.500  -0.3439   0.02144   0.01655  -0.1322   0.8937   0.0119
  -8.250  -0.3185   0.01943   0.01421  -0.1335   0.8806   0.0123
  -8.000  -0.2924   0.01837   0.01297  -0.1341   0.8683   0.0126
  -7.750  -0.2668   0.01754   0.01197  -0.1344   0.8564   0.0129
  -7.250  -0.2169   0.01606   0.01015  -0.1344   0.8347   0.0136
  -7.000  -0.1917   0.01546   0.00938  -0.1342   0.8256   0.0141
  -6.750  -0.1662   0.01491   0.00869  -0.1341   0.8170   0.0147
  -6.500  -0.1405   0.01437   0.00800  -0.1340   0.8094   0.0152
  -6.250  -0.1148   0.01384   0.00734  -0.1338   0.8020   0.0155
  -6.000  -0.0887   0.01338   0.00678  -0.1337   0.7955   0.0158
  -5.750  -0.0635   0.01260   0.00591  -0.1336   0.7887   0.0163
  -5.500  -0.0373   0.01214   0.00537  -0.1336   0.7828   0.0168
  -5.250  -0.0107   0.01175   0.00494  -0.1336   0.7766   0.0173
  -5.000   0.0162   0.01142   0.00454  -0.1336   0.7709   0.0179
  -4.750   0.0435   0.01115   0.00422  -0.1337   0.7660   0.0188
  -4.500   0.0709   0.01087   0.00388  -0.1337   0.7610   0.0197
  -4.250   0.0985   0.01063   0.00357  -0.1338   0.7564   0.0202
  -4.000   0.1262   0.01035   0.00323  -0.1340   0.7524   0.0212
  -3.750   0.1541   0.01011   0.00297  -0.1341   0.7480   0.0225
  -3.500   0.1820   0.00994   0.00275  -0.1342   0.7436   0.0241
  -3.250   0.2101   0.00979   0.00256  -0.1344   0.7397   0.0266
  -3.000   0.2383   0.00959   0.00240  -0.1346   0.7360   0.0366
  -2.750   0.2665   0.00934   0.00225  -0.1349   0.7324   0.0656
  -2.500   0.2948   0.00912   0.00214  -0.1352   0.7289   0.1017
  -2.250   0.3232   0.00889   0.00205  -0.1356   0.7257   0.1508
  -2.000   0.3518   0.00867   0.00197  -0.1360   0.7227   0.2077
  -1.750   0.3806   0.00829   0.00192  -0.1367   0.7193   0.3072
  -1.500   0.4097   0.00793   0.00188  -0.1374   0.7160   0.4141
  -1.250   0.4388   0.00750   0.00187  -0.1381   0.7130   0.5516
  -1.000   0.4664   0.00735   0.00204  -0.1381   0.7103   0.6654
  -0.500   0.5230   0.00746   0.00214  -0.1381   0.7046   0.7094
  -0.250   0.5512   0.00751   0.00220  -0.1382   0.7016   0.7225
   0.000   0.5792   0.00757   0.00225  -0.1382   0.6985   0.7323
   0.250   0.6074   0.00764   0.00230  -0.1382   0.6954   0.7414
   0.500   0.6354   0.00772   0.00236  -0.1382   0.6922   0.7495
   0.750   0.6631   0.00776   0.00242  -0.1382   0.6877   0.7569
   1.000   0.6905   0.00781   0.00248  -0.1380   0.6828   0.7637
   1.250   0.7183   0.00790   0.00252  -0.1380   0.6778   0.7704
   1.500   0.7450   0.00794   0.00260  -0.1377   0.6715   0.7760
   1.750   0.7719   0.00801   0.00265  -0.1375   0.6643   0.7823
   2.000   0.7989   0.00806   0.00271  -0.1373   0.6569   0.7868
   2.250   0.8253   0.00812   0.00276  -0.1370   0.6489   0.7901
   2.500   0.8521   0.00817   0.00284  -0.1368   0.6407   0.7931
   2.750   0.8785   0.00826   0.00289  -0.1365   0.6310   0.7960
   3.000   0.9050   0.00832   0.00296  -0.1362   0.6199   0.7989
   3.250   0.9311   0.00840   0.00304  -0.1359   0.6077   0.8013
   3.500   0.9565   0.00849   0.00313  -0.1354   0.5931   0.8037
   3.750   0.9807   0.00863   0.00322  -0.1346   0.5723   0.8063
   4.000   1.0024   0.00887   0.00334  -0.1334   0.5341   0.8089
   4.250   1.0197   0.00939   0.00359  -0.1314   0.4785   0.8120
   4.500   1.0356   0.01007   0.00398  -0.1293   0.4192   0.8152
   4.750   1.0510   0.01078   0.00442  -0.1271   0.3617   0.8179
   5.000   1.0677   0.01143   0.00484  -0.1252   0.3122   0.8207
   5.250   1.0851   0.01203   0.00525  -0.1235   0.2712   0.8237
   5.500   1.1031   0.01260   0.00566  -0.1219   0.2350   0.8273
   5.750   1.1208   0.01317   0.00608  -0.1202   0.2025   0.8309
   6.000   1.1386   0.01367   0.00648  -0.1186   0.1768   0.8340
   6.250   1.1558   0.01418   0.00690  -0.1168   0.1539   0.8376
   6.500   1.1724   0.01466   0.00731  -0.1149   0.1344   0.8417
   6.750   1.1888   0.01513   0.00773  -0.1130   0.1187   0.8458
   7.000   1.2049   0.01560   0.00816  -0.1110   0.1055   0.8502
   7.250   1.2213   0.01607   0.00861  -0.1091   0.0943   0.8556
   7.500   1.2375   0.01655   0.00909  -0.1073   0.0852   0.8614
   7.750   1.2534   0.01703   0.00958  -0.1053   0.0772   0.8678
   8.250   1.2841   0.01804   0.01063  -0.1015   0.0640   0.8839
   8.500   1.2992   0.01851   0.01116  -0.0995   0.0593   0.8955
   8.750   1.3120   0.01902   0.01173  -0.0971   0.0549   0.9160
   9.000   1.3254   0.01952   0.01231  -0.0950   0.0513   1.0000
   9.250   1.3415   0.02015   0.01297  -0.0935   0.0479   1.0000
   9.500   1.3562   0.02090   0.01372  -0.0919   0.0443   1.0000
   9.750   1.3708   0.02165   0.01450  -0.0903   0.0417   1.0000
  10.000   1.3859   0.02238   0.01530  -0.0889   0.0396   1.0000
  10.250   1.3999   0.02320   0.01615  -0.0873   0.0372   1.0000
  10.500   1.4122   0.02417   0.01713  -0.0857   0.0348   1.0000
  10.750   1.4257   0.02507   0.01809  -0.0842   0.0333   1.0000
  11.000   1.4393   0.02598   0.01907  -0.0828   0.0319   1.0000
  11.250   1.4521   0.02696   0.02011  -0.0814   0.0302   1.0000
  11.500   1.4637   0.02808   0.02126  -0.0799   0.0284   1.0000
  11.750   1.4744   0.02928   0.02251  -0.0785   0.0268   1.0000
  12.000   1.4873   0.03033   0.02363  -0.0773   0.0254   1.0000
  12.250   1.4992   0.03148   0.02483  -0.0761   0.0238   1.0000
  12.500   1.5096   0.03278   0.02618  -0.0748   0.0224   1.0000
  12.750   1.5185   0.03426   0.02770  -0.0735   0.0211   1.0000
  13.000   1.5291   0.03559   0.02913  -0.0724   0.0203   1.0000
  13.250   1.5391   0.03701   0.03065  -0.0714   0.0194   1.0000
  13.500   1.5482   0.03854   0.03225  -0.0703   0.0184   1.0000
  13.750   1.5564   0.04020   0.03397  -0.0693   0.0174   1.0000
  14.000   1.5628   0.04206   0.03588  -0.0683   0.0165   1.0000
  14.250   1.5712   0.04376   0.03769  -0.0674   0.0157   1.0000
  14.500   1.5787   0.04559   0.03962  -0.0666   0.0148   1.0000
  14.750   1.5851   0.04758   0.04168  -0.0659   0.0139   1.0000
  15.000   1.5900   0.04976   0.04394  -0.0652   0.0130   1.0000
  15.250   1.5948   0.05201   0.04629  -0.0646   0.0123   1.0000
  15.500   1.5996   0.05434   0.04873  -0.0641   0.0116   1.0000
  15.750   1.6030   0.05686   0.05135  -0.0638   0.0109   1.0000
  16.000   1.6052   0.05961   0.05418  -0.0635   0.0103   1.0000
  16.250   1.6058   0.06262   0.05729  -0.0633   0.0097   1.0000
  16.500   1.6069   0.06567   0.06046  -0.0633   0.0092   1.0000
  16.750   1.6068   0.06896   0.06388  -0.0635   0.0087   1.0000
  17.000   1.6053   0.07252   0.06756  -0.0638   0.0083   1.0000
  17.250   1.6023   0.07642   0.07157  -0.0644   0.0079   1.0000
  17.500   1.5972   0.08075   0.07603  -0.0653   0.0075   1.0000
  17.750   1.5911   0.08539   0.08081  -0.0665   0.0073   1.0000
  18.000   1.5852   0.09015   0.08572  -0.0679   0.0070   1.0000
  18.250   1.5777   0.09532   0.09105  -0.0697   0.0068   1.0000
  18.500   1.5689   0.10085   0.09672  -0.0718   0.0066   1.0000
  18.750   1.5587   0.10683   0.10286  -0.0744   0.0064   1.0000
  19.000   1.5471   0.11322   0.10941  -0.0774   0.0062   1.0000
  19.250   1.5341   0.12006   0.11640  -0.0808   0.0061   1.0000
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