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OAF102 AIRFOIL (oaf102-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: OAF102 AIRFOIL (oaf102-il)
Reynolds number: 100,000
Max Cl/Cd: 60.59 at α=5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-oaf102-il-100000-n5.txt
Download as CSV file: xf-oaf102-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: OAF102 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
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.6084   0.06264   0.05764  -0.0503   1.0000   0.0324
  -9.250  -0.6178   0.04889   0.04348  -0.0718   1.0000   0.0321
  -9.000  -0.6059   0.04093   0.03475  -0.0830   1.0000   0.0327
  -8.750  -0.5857   0.03734   0.03093  -0.0863   1.0000   0.0337
  -8.500  -0.5621   0.03472   0.02809  -0.0889   1.0000   0.0351
  -8.250  -0.5366   0.03238   0.02545  -0.0914   1.0000   0.0375
  -8.000  -0.5096   0.02986   0.02244  -0.0937   1.0000   0.0403
  -7.750  -0.4838   0.02772   0.02011  -0.0951   1.0000   0.0424
  -7.500  -0.4587   0.02633   0.01863  -0.0960   1.0000   0.0450
  -7.250  -0.4338   0.02507   0.01715  -0.0966   1.0000   0.0490
  -7.000  -0.4101   0.02377   0.01572  -0.0970   1.0000   0.0526
  -6.750  -0.3872   0.02283   0.01474  -0.0971   1.0000   0.0567
  -6.500  -0.3550   0.02177   0.01350  -0.0990   0.9964   0.0634
  -6.250  -0.3163   0.02071   0.01233  -0.1021   0.9906   0.0718
  -6.000  -0.2770   0.01975   0.01129  -0.1053   0.9852   0.0837
  -5.750  -0.2385   0.01889   0.01036  -0.1081   0.9791   0.0993
  -5.500  -0.1998   0.01812   0.00959  -0.1111   0.9728   0.1193
  -5.250  -0.1625   0.01755   0.00899  -0.1136   0.9658   0.1441
  -5.000  -0.1253   0.01715   0.00855  -0.1159   0.9587   0.1711
  -4.750  -0.0901   0.01683   0.00821  -0.1177   0.9505   0.1959
  -4.500  -0.0547   0.01657   0.00791  -0.1195   0.9430   0.2198
  -4.250  -0.0222   0.01639   0.00769  -0.1206   0.9336   0.2417
  -4.000   0.0109   0.01624   0.00746  -0.1217   0.9257   0.2625
  -3.750   0.0414   0.01612   0.00733  -0.1222   0.9159   0.2808
  -3.500   0.0718   0.01603   0.00719  -0.1227   0.9071   0.2984
  -3.250   0.1017   0.01595   0.00705  -0.1230   0.8984   0.3153
  -3.000   0.1308   0.01589   0.00695  -0.1232   0.8891   0.3318
  -2.750   0.1599   0.01583   0.00685  -0.1233   0.8815   0.3481
  -2.500   0.1883   0.01579   0.00678  -0.1233   0.8718   0.3642
  -2.250   0.2169   0.01575   0.00671  -0.1233   0.8642   0.3802
  -2.000   0.2454   0.01573   0.00667  -0.1233   0.8553   0.3964
  -1.750   0.2737   0.01570   0.00663  -0.1232   0.8474   0.4125
  -1.500   0.3021   0.01568   0.00660  -0.1232   0.8389   0.4282
  -1.250   0.3304   0.01566   0.00658  -0.1231   0.8309   0.4431
  -1.000   0.3587   0.01564   0.00657  -0.1230   0.8231   0.4575
  -0.750   0.3871   0.01564   0.00658  -0.1230   0.8155   0.4723
  -0.500   0.4154   0.01563   0.00660  -0.1229   0.8081   0.4877
  -0.250   0.4437   0.01564   0.00664  -0.1229   0.8010   0.5034
   0.000   0.4721   0.01566   0.00669  -0.1229   0.7937   0.5198
   0.250   0.5002   0.01567   0.00676  -0.1228   0.7872   0.5374
   0.500   0.5284   0.01569   0.00687  -0.1227   0.7797   0.5567
   0.750   0.5563   0.01569   0.00693  -0.1225   0.7735   0.5784
   1.000   0.5843   0.01571   0.00709  -0.1225   0.7656   0.6020
   1.250   0.6118   0.01568   0.00717  -0.1221   0.7595   0.6298
   1.500   0.6390   0.01567   0.00736  -0.1219   0.7511   0.6649
   1.750   0.6643   0.01554   0.00744  -0.1209   0.7447   0.7175
   2.000   0.6821   0.01521   0.00752  -0.1183   0.7365   0.8513
   2.250   0.7095   0.01518   0.00753  -0.1178   0.7298   1.0000
   2.500   0.7388   0.01542   0.00780  -0.1182   0.7215   1.0000
   2.750   0.7679   0.01560   0.00797  -0.1183   0.7148   1.0000
   3.000   0.7968   0.01585   0.00830  -0.1186   0.7063   1.0000
   3.250   0.8255   0.01604   0.00851  -0.1185   0.6995   1.0000
   3.500   0.8540   0.01630   0.00888  -0.1187   0.6904   1.0000
   3.750   0.8825   0.01648   0.00912  -0.1185   0.6825   1.0000
   4.000   0.9092   0.01651   0.00921  -0.1179   0.6645   1.0000
   4.250   0.9342   0.01632   0.00897  -0.1164   0.6316   1.0000
   4.500   0.9589   0.01624   0.00879  -0.1150   0.5914   1.0000
   4.750   0.9842   0.01637   0.00888  -0.1141   0.5498   1.0000
   5.000   1.0089   0.01665   0.00904  -0.1131   0.4970   1.0000
   5.250   1.0302   0.01736   0.00930  -0.1118   0.4041   1.0000
   5.500   1.0418   0.01960   0.01034  -0.1099   0.2181   1.0000
   5.750   1.0564   0.02168   0.01173  -0.1086   0.1199   1.0000
   6.000   1.0755   0.02303   0.01289  -0.1076   0.0894   1.0000
   6.250   1.0951   0.02422   0.01404  -0.1065   0.0751   1.0000
   6.500   1.1138   0.02543   0.01523  -0.1053   0.0657   1.0000
   7.000   1.1490   0.02791   0.01783  -0.1025   0.0545   1.0000
   7.250   1.1669   0.02905   0.01908  -0.1011   0.0499   1.0000
   7.500   1.1830   0.03040   0.02044  -0.0995   0.0467   1.0000
   7.750   1.1983   0.03201   0.02206  -0.0978   0.0444   1.0000
   8.000   1.2169   0.03335   0.02357  -0.0964   0.0417   1.0000
   8.250   1.2349   0.03469   0.02499  -0.0951   0.0389   1.0000
   8.500   1.2524   0.03622   0.02652  -0.0939   0.0370   1.0000
   8.750   1.2724   0.03827   0.02858  -0.0929   0.0355   1.0000
   9.000   1.2936   0.04009   0.03065  -0.0918   0.0341   1.0000
   9.250   1.3128   0.04194   0.03274  -0.0907   0.0323   1.0000
   9.500   1.3292   0.04370   0.03471  -0.0893   0.0306   1.0000
   9.750   1.3446   0.04562   0.03676  -0.0880   0.0294   1.0000
  10.000   1.3600   0.04794   0.03920  -0.0868   0.0286   1.0000
  10.250   1.3738   0.05095   0.04241  -0.0855   0.0279   1.0000
  10.500   1.3800   0.05393   0.04583  -0.0831   0.0274   1.0000
  10.750   1.3801   0.05703   0.04937  -0.0803   0.0268   1.0000
  11.000   1.3739   0.06009   0.05281  -0.0769   0.0262   1.0000
  11.250   1.3649   0.06335   0.05641  -0.0739   0.0257   1.0000
  11.500   1.3539   0.06687   0.06025  -0.0714   0.0252   1.0000
  11.750   1.3411   0.07070   0.06437  -0.0696   0.0248   1.0000
  12.000   1.3263   0.07495   0.06893  -0.0684   0.0245   1.0000
  12.250   1.3092   0.07973   0.07398  -0.0680   0.0243   1.0000
  12.500   1.2895   0.08518   0.07970  -0.0684   0.0242   1.0000
  12.750   1.2665   0.09150   0.08626  -0.0698   0.0242   1.0000
  13.000   1.2406   0.09884   0.09387  -0.0725   0.0243   1.0000
  13.250   1.2114   0.10754   0.10282  -0.0769   0.0246   1.0000
  13.500   1.1789   0.11821   0.11372  -0.0834   0.0250   1.0000
  13.750   1.1440   0.13173   0.12742  -0.0927   0.0257   1.0000
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