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NREL's S802 Airfoil (s802-nr) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: NREL's S802 Airfoil (s802-nr)
Reynolds number: 200,000
Max Cl/Cd: 91.32 at α=6.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s802-nr-200000.txt
Download as CSV file: xf-s802-nr-200000.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 =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.250  -0.2814   0.12221   0.11901  -0.0403   1.0000   0.0420
 -11.000  -0.2859   0.12117   0.11803  -0.0374   1.0000   0.0427
 -10.750  -0.3522   0.11921   0.11562  -0.0462   1.0000   0.0416
 -10.500  -0.3446   0.11671   0.11314  -0.0446   1.0000   0.0424
 -10.250  -0.3416   0.11429   0.11076  -0.0436   1.0000   0.0436
 -10.000  -0.3423   0.11192   0.10843  -0.0429   1.0000   0.0447
  -9.750  -0.3460   0.10962   0.10619  -0.0421   1.0000   0.0457
  -9.500  -0.3542   0.10760   0.10425  -0.0406   1.0000   0.0468
  -9.250  -0.3686   0.10627   0.10300  -0.0382   1.0000   0.0478
  -9.000  -0.3717   0.10165   0.09844  -0.0473   0.9959   0.0501
  -8.750  -0.3634   0.09531   0.09211  -0.0594   0.9889   0.0505
  -8.500  -0.3429   0.09143   0.08822  -0.0548   0.9883   0.0527
  -8.250  -0.3208   0.08827   0.08504  -0.0577   0.9852   0.0554
  -8.000  -0.3078   0.08369   0.08046  -0.0636   0.9781   0.0583
  -7.750  -0.1941   0.06062   0.05751  -0.0820   0.9537   0.0663
  -7.500  -0.1834   0.05579   0.05267  -0.0865   0.9494   0.0689
  -7.250  -0.2777   0.06150   0.05811  -0.0982   0.9488   0.0648
  -7.000  -0.2603   0.05878   0.05537  -0.0995   0.9411   0.0670
  -6.750  -0.2359   0.05264   0.04889  -0.1093   0.9354   0.0739
  -6.500  -0.2232   0.04690   0.04286  -0.1138   0.9265   0.0778
  -6.250  -0.1940   0.04409   0.04004  -0.1162   0.9235   0.0810
  -6.000  -0.1611   0.03949   0.03497  -0.1224   0.9207   0.0920
  -5.750  -0.1359   0.02900   0.02324  -0.1245   0.9129   0.0536
  -5.500  -0.1003   0.02479   0.01837  -0.1264   0.9095   0.0460
  -5.250  -0.0624   0.02191   0.01496  -0.1286   0.9071   0.0443
  -5.000  -0.0232   0.02012   0.01289  -0.1310   0.9051   0.0450
  -4.750   0.0016   0.01933   0.01196  -0.1305   0.8976   0.0472
  -4.500   0.0361   0.01811   0.01057  -0.1317   0.8939   0.0484
  -4.250   0.0726   0.01706   0.00939  -0.1333   0.8912   0.0499
  -4.000   0.0986   0.01612   0.00843  -0.1331   0.8853   0.0519
  -3.750   0.1280   0.01538   0.00774  -0.1337   0.8802   0.0565
  -3.500   0.1624   0.01468   0.00700  -0.1351   0.8768   0.0649
  -3.250   0.1919   0.01392   0.00635  -0.1358   0.8718   0.0920
  -3.000   0.2192   0.01272   0.00599  -0.1369   0.8663   0.2787
  -2.750   0.2499   0.01181   0.00587  -0.1383   0.8627   0.4917
  -2.500   0.2760   0.01169   0.00633  -0.1372   0.8596   0.6780
  -2.250   0.2942   0.01211   0.00679  -0.1347   0.8531   0.7313
  -2.000   0.3181   0.01242   0.00706  -0.1331   0.8487   0.7639
  -1.750   0.3444   0.01265   0.00721  -0.1320   0.8455   0.7875
  -1.500   0.3616   0.01297   0.00753  -0.1293   0.8406   0.8060
  -1.250   0.3811   0.01319   0.00772  -0.1271   0.8357   0.8223
  -1.000   0.4046   0.01328   0.00775  -0.1257   0.8321   0.8369
  -0.750   0.4296   0.01335   0.00776  -0.1246   0.8294   0.8509
  -0.500   0.4437   0.01358   0.00799  -0.1217   0.8236   0.8638
  -0.250   0.4647   0.01365   0.00803  -0.1201   0.8195   0.8765
   0.000   0.4889   0.01365   0.00799  -0.1190   0.8163   0.8888
   0.250   0.5083   0.01367   0.00799  -0.1170   0.8127   0.9003
   0.500   0.5216   0.01378   0.00813  -0.1141   0.8071   0.9119
   0.750   0.5433   0.01374   0.00807  -0.1127   0.8031   0.9229
   1.000   0.5700   0.01366   0.00795  -0.1122   0.8001   0.9332
   1.250   0.5873   0.01377   0.00809  -0.1102   0.7949   0.9444
   1.500   0.6111   0.01379   0.00812  -0.1095   0.7899   0.9539
   1.750   0.6447   0.01373   0.00803  -0.1107   0.7863   0.9613
   2.000   0.6812   0.01371   0.00798  -0.1124   0.7830   0.9675
   2.250   0.7098   0.01388   0.00822  -0.1131   0.7763   0.9756
   2.500   0.7493   0.01377   0.00810  -0.1155   0.7714   0.9811
   2.750   0.7870   0.01375   0.00807  -0.1176   0.7657   0.9882
   3.000   0.8184   0.01372   0.00808  -0.1185   0.7580   1.0000
   3.250   0.8510   0.01361   0.00795  -0.1194   0.7516   1.0000
   3.500   0.8764   0.01364   0.00800  -0.1191   0.7426   1.0000
   3.750   0.9078   0.01355   0.00793  -0.1198   0.7347   1.0000
   4.000   0.9386   0.01344   0.00782  -0.1203   0.7254   1.0000
   4.250   0.9667   0.01342   0.00785  -0.1204   0.7154   1.0000
   4.500   1.0002   0.01327   0.00768  -0.1214   0.7064   1.0000
   4.750   1.0280   0.01322   0.00770  -0.1214   0.6950   1.0000
   5.000   1.0555   0.01317   0.00770  -0.1213   0.6827   1.0000
   5.250   1.0834   0.01310   0.00766  -0.1212   0.6693   1.0000
   5.500   1.1103   0.01303   0.00765  -0.1209   0.6542   1.0000
   5.750   1.1358   0.01297   0.00764  -0.1204   0.6364   1.0000
   6.000   1.1602   0.01294   0.00763  -0.1196   0.6144   1.0000
   6.250   1.1814   0.01298   0.00769  -0.1183   0.5846   1.0000
   6.500   1.1999   0.01314   0.00776  -0.1163   0.5365   1.0000
   6.750   1.2102   0.01377   0.00794  -0.1130   0.4630   1.0000
   7.000   1.2134   0.01489   0.00859  -0.1087   0.3899   1.0000
   7.250   1.2146   0.01608   0.00940  -0.1043   0.3273   1.0000
   7.500   1.2156   0.01732   0.01031  -0.1001   0.2746   1.0000
   7.750   1.2182   0.01859   0.01131  -0.0963   0.2293   1.0000
   8.000   1.2230   0.01985   0.01235  -0.0931   0.1923   1.0000
   8.250   1.2289   0.02111   0.01343  -0.0902   0.1647   1.0000
   8.500   1.2354   0.02240   0.01458  -0.0874   0.1442   1.0000
   8.750   1.2425   0.02373   0.01581  -0.0849   0.1286   1.0000
   9.000   1.2517   0.02499   0.01702  -0.0828   0.1159   1.0000
   9.250   1.2624   0.02620   0.01826  -0.0808   0.1056   1.0000
   9.500   1.2712   0.02763   0.01967  -0.0788   0.0979   1.0000
   9.750   1.2825   0.02888   0.02093  -0.0771   0.0908   1.0000
  10.000   1.2933   0.03033   0.02240  -0.0754   0.0848   1.0000
  10.250   1.3062   0.03155   0.02367  -0.0740   0.0795   1.0000
  10.500   1.3185   0.03325   0.02529  -0.0726   0.0747   1.0000
  10.750   1.3329   0.03441   0.02664  -0.0714   0.0708   1.0000
  11.000   1.3462   0.03572   0.02799  -0.0702   0.0670   1.0000
  11.250   1.3658   0.03746   0.02965  -0.0695   0.0630   1.0000
  11.500   1.3793   0.03875   0.03115  -0.0683   0.0604   1.0000
  11.750   1.3926   0.04015   0.03267  -0.0671   0.0574   1.0000
  12.000   1.4064   0.04162   0.03418  -0.0662   0.0547   1.0000
  12.250   1.4293   0.04369   0.03631  -0.0659   0.0516   1.0000
  12.500   1.4381   0.04532   0.03817  -0.0644   0.0496   1.0000
  12.750   1.4467   0.04706   0.04009  -0.0632   0.0473   1.0000
  13.000   1.4557   0.04881   0.04191  -0.0621   0.0453   1.0000
  13.250   1.4736   0.05150   0.04463  -0.0618   0.0424   1.0000
  13.500   1.4721   0.05361   0.04701  -0.0600   0.0411   1.0000
  13.750   1.4731   0.05599   0.04963  -0.0587   0.0395   1.0000
  14.000   1.4742   0.05835   0.05217  -0.0577   0.0378   1.0000
  14.250   1.4768   0.06053   0.05442  -0.0569   0.0362   1.0000
  14.500   1.4836   0.06416   0.05810  -0.0564   0.0342   1.0000
  14.750   1.4740   0.06748   0.06173  -0.0554   0.0334   1.0000
  15.000   1.4644   0.07126   0.06581  -0.0549   0.0325   1.0000
  15.250   1.4552   0.07523   0.07003  -0.0547   0.0314   1.0000
  15.500   1.4479   0.07908   0.07408  -0.0549   0.0303   1.0000
  15.750   1.4412   0.08291   0.07804  -0.0554   0.0293   1.0000
  16.000   1.4395   0.08622   0.08140  -0.0559   0.0283   1.0000
  16.250   1.4334   0.09085   0.08612  -0.0567   0.0275   1.0000
  16.500   1.4126   0.09786   0.09340  -0.0585   0.0271   1.0000
  16.750   1.3924   0.10457   0.10039  -0.0612   0.0269   1.0000
  17.000   1.3712   0.11199   0.10808  -0.0647   0.0268   1.0000
  17.250   1.3486   0.12021   0.11655  -0.0692   0.0267   1.0000
  17.500   1.3249   0.12927   0.12585  -0.0747   0.0268   1.0000
  17.750   1.2999   0.13928   0.13607  -0.0812   0.0269   1.0000
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