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NREL's S803 Airfoil (s803-nr) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: NREL's S803 Airfoil (s803-nr)
Reynolds number: 100,000
Max Cl/Cd: 62.96 at α=6.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s803-nr-100000-n5.txt
Download as CSV file: xf-s803-nr-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NREL's S803 Airfoil                             
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.3768   0.09269   0.08778  -0.0475   1.0000   0.0326
  -8.750  -0.3795   0.09002   0.08518  -0.0466   1.0000   0.0323
  -8.500  -0.3862   0.08716   0.08240  -0.0460   1.0000   0.0320
  -8.250  -0.3957   0.08449   0.07983  -0.0449   1.0000   0.0317
  -8.000  -0.4111   0.08184   0.07729  -0.0435   1.0000   0.0314
  -7.750  -0.4134   0.07697   0.07247  -0.0478   0.9951   0.0310
  -7.250  -0.3898   0.05687   0.05201  -0.0761   0.9718   0.0308
  -7.000  -0.3744   0.04891   0.04356  -0.0849   0.9609   0.0312
  -6.750  -0.3546   0.04286   0.03694  -0.0902   0.9506   0.0315
  -6.500  -0.3289   0.03801   0.03152  -0.0941   0.9425   0.0315
  -6.250  -0.2972   0.03382   0.02667  -0.0977   0.9365   0.0319
  -6.000  -0.2660   0.03070   0.02297  -0.1000   0.9298   0.0323
  -5.750  -0.2333   0.02837   0.02026  -0.1022   0.9236   0.0337
  -5.500  -0.1968   0.02682   0.01855  -0.1047   0.9198   0.0359
  -5.250  -0.1680   0.02526   0.01672  -0.1053   0.9112   0.0372
  -5.000  -0.1319   0.02363   0.01483  -0.1070   0.9068   0.0384
  -4.750  -0.1005   0.02236   0.01335  -0.1078   0.8997   0.0398
  -4.250  -0.0292   0.02024   0.01114  -0.1113   0.8893   0.0464
  -4.000   0.0017   0.01947   0.01024  -0.1120   0.8807   0.0500
  -3.500   0.0713   0.01781   0.00854  -0.1152   0.8672   0.0668
  -3.250   0.1086   0.01695   0.00781  -0.1173   0.8616   0.1044
  -3.000   0.1410   0.01614   0.00739  -0.1189   0.8535   0.1906
  -2.750   0.1764   0.01484   0.00713  -0.1215   0.8471   0.4197
  -2.500   0.2021   0.01468   0.00750  -0.1204   0.8387   0.5759
  -2.250   0.2342   0.01478   0.00751  -0.1206   0.8315   0.6396
  -2.000   0.2627   0.01494   0.00755  -0.1203   0.8231   0.6760
  -1.750   0.2920   0.01504   0.00755  -0.1199   0.8161   0.7010
  -1.500   0.3193   0.01516   0.00756  -0.1194   0.8078   0.7226
  -1.250   0.3479   0.01522   0.00752  -0.1190   0.8008   0.7399
  -1.000   0.3736   0.01532   0.00753  -0.1182   0.7928   0.7552
  -0.750   0.4015   0.01537   0.00750  -0.1179   0.7861   0.7698
  -0.500   0.4270   0.01545   0.00751  -0.1171   0.7789   0.7831
  -0.250   0.4523   0.01549   0.00750  -0.1162   0.7719   0.7950
   0.000   0.4790   0.01553   0.00748  -0.1158   0.7656   0.8057
   0.250   0.5059   0.01561   0.00751  -0.1156   0.7585   0.8154
   0.500   0.5347   0.01562   0.00745  -0.1156   0.7533   0.8228
   0.750   0.5605   0.01573   0.00754  -0.1154   0.7459   0.8305
   1.000   0.5884   0.01577   0.00754  -0.1153   0.7402   0.8368
   1.250   0.6170   0.01588   0.00762  -0.1156   0.7344   0.8437
   1.500   0.6425   0.01597   0.00771  -0.1152   0.7278   0.8497
   1.750   0.6728   0.01603   0.00773  -0.1157   0.7229   0.8562
   2.000   0.6973   0.01618   0.00792  -0.1152   0.7160   0.8627
   2.250   0.7250   0.01626   0.00802  -0.1152   0.7100   0.8697
   2.500   0.7521   0.01637   0.00815  -0.1152   0.7040   0.8767
   2.750   0.7772   0.01649   0.00831  -0.1147   0.6968   0.8845
   3.000   0.8058   0.01653   0.00838  -0.1148   0.6910   0.8927
   3.250   0.8287   0.01668   0.00861  -0.1139   0.6825   0.9031
   3.500   0.8568   0.01668   0.00863  -0.1138   0.6757   0.9135
   3.750   0.8800   0.01676   0.00882  -0.1129   0.6659   0.9289
   4.000   0.9092   0.01678   0.00892  -0.1132   0.6564   0.9543
   4.250   0.9419   0.01681   0.00895  -0.1141   0.6459   1.0000
   4.500   0.9690   0.01698   0.00918  -0.1142   0.6331   1.0000
   4.750   0.9964   0.01713   0.00940  -0.1142   0.6200   1.0000
   5.000   1.0234   0.01728   0.00958  -0.1141   0.6062   1.0000
   5.250   1.0496   0.01743   0.00977  -0.1138   0.5912   1.0000
   5.500   1.0749   0.01758   0.00997  -0.1133   0.5747   1.0000
   5.750   1.0995   0.01774   0.01019  -0.1127   0.5564   1.0000
   6.000   1.1224   0.01795   0.01045  -0.1118   0.5356   1.0000
   6.250   1.1437   0.01818   0.01071  -0.1105   0.5101   1.0000
   6.500   1.1635   0.01848   0.01100  -0.1090   0.4773   1.0000
   6.750   1.1809   0.01889   0.01130  -0.1071   0.4305   1.0000
   7.000   1.1934   0.01962   0.01169  -0.1045   0.3736   1.0000
   7.250   1.2024   0.02068   0.01241  -0.1016   0.3191   1.0000
   7.500   1.2102   0.02187   0.01332  -0.0986   0.2725   1.0000
   7.750   1.2175   0.02303   0.01428  -0.0957   0.2351   1.0000
   8.000   1.2248   0.02421   0.01532  -0.0929   0.2043   1.0000
   8.250   1.2325   0.02542   0.01640  -0.0902   0.1792   1.0000
   8.500   1.2411   0.02662   0.01753  -0.0878   0.1587   1.0000
   8.750   1.2493   0.02788   0.01873  -0.0854   0.1420   1.0000
   9.000   1.2578   0.02916   0.01999  -0.0832   0.1283   1.0000
   9.250   1.2665   0.03047   0.02133  -0.0811   0.1172   1.0000
   9.500   1.2743   0.03190   0.02275  -0.0791   0.1082   1.0000
   9.750   1.2824   0.03335   0.02423  -0.0772   0.1000   1.0000
  10.000   1.2909   0.03484   0.02579  -0.0754   0.0931   1.0000
  10.250   1.2986   0.03644   0.02743  -0.0738   0.0873   1.0000
  10.500   1.3063   0.03812   0.02916  -0.0722   0.0824   1.0000
  10.750   1.3155   0.03973   0.03091  -0.0708   0.0772   1.0000
  11.000   1.3217   0.04162   0.03280  -0.0694   0.0733   1.0000
  11.250   1.3315   0.04337   0.03468  -0.0682   0.0698   1.0000
  11.500   1.3410   0.04514   0.03659  -0.0671   0.0661   1.0000
  11.750   1.3486   0.04707   0.03858  -0.0660   0.0630   1.0000
  12.000   1.3564   0.04914   0.04068  -0.0650   0.0602   1.0000
  12.250   1.3669   0.05105   0.04282  -0.0640   0.0574   1.0000
  12.500   1.3756   0.05311   0.04506  -0.0632   0.0548   1.0000
  12.750   1.3822   0.05529   0.04733  -0.0624   0.0525   1.0000
  13.000   1.3890   0.05764   0.04968  -0.0617   0.0504   1.0000
  13.250   1.3958   0.06010   0.05243  -0.0610   0.0484   1.0000
  13.500   1.4012   0.06274   0.05531  -0.0604   0.0464   1.0000
  13.750   1.4042   0.06551   0.05828  -0.0599   0.0445   1.0000
  14.000   1.4059   0.06835   0.06124  -0.0597   0.0429   1.0000
  14.250   1.4082   0.07123   0.06417  -0.0596   0.0414   1.0000
  14.500   1.4082   0.07471   0.06786  -0.0595   0.0402   1.0000
  14.750   1.4031   0.07883   0.07235  -0.0597   0.0389   1.0000
  15.000   1.3963   0.08322   0.07703  -0.0604   0.0377   1.0000
  15.250   1.3887   0.08777   0.08183  -0.0614   0.0365   1.0000
  15.500   1.3810   0.09240   0.08667  -0.0627   0.0355   1.0000
  15.750   1.3741   0.09700   0.09142  -0.0642   0.0346   1.0000
  16.000   1.3687   0.10150   0.09603  -0.0659   0.0337   1.0000
  16.250   1.3648   0.10587   0.10046  -0.0675   0.0329   1.0000
  16.500   1.3481   0.11284   0.10771  -0.0708   0.0325   1.0000
  16.750   1.3280   0.12086   0.11602  -0.0753   0.0322   1.0000
  17.000   1.3058   0.12987   0.12531  -0.0808   0.0321   1.0000
  17.250   1.2811   0.14012   0.13581  -0.0875   0.0321   1.0000
  17.500   1.2530   0.15213   0.14803  -0.0959   0.0323   1.0000
  17.750   1.2194   0.16697   0.16300  -0.1063   0.0327   1.0000
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