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NACA 22112 (naca22112-jf) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: NACA 22112 (naca22112-jf)
Reynolds number: 100,000
Max Cl/Cd: 36.82 at α=6.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-naca22112-jf-100000-n5.txt
Download as CSV file: xf-naca22112-jf-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 22112                                      
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -13.250  -0.4437   0.13770   0.13259  -0.0010   1.0000   0.0634
 -13.000  -0.4465   0.13469   0.12958  -0.0023   1.0000   0.0656
 -12.250  -0.6184   0.12124   0.11581  -0.0008   1.0000   0.0406
 -12.000  -0.6135   0.11767   0.11225  -0.0012   1.0000   0.0403
 -11.750  -0.5995   0.11774   0.11235   0.0011   1.0000   0.0439
 -11.500  -0.6103   0.10905   0.10368  -0.0038   1.0000   0.0390
 -11.000  -0.6867   0.08036   0.07476  -0.0267   1.0000   0.0342
 -10.750  -0.6995   0.07554   0.06986  -0.0290   1.0000   0.0340
 -10.500  -0.7148   0.07118   0.06539  -0.0302   1.0000   0.0338
 -10.250  -0.7306   0.06739   0.06148  -0.0297   1.0000   0.0337
 -10.000  -0.7445   0.06393   0.05786  -0.0281   1.0000   0.0336
  -9.750  -0.7534   0.06035   0.05406  -0.0266   1.0000   0.0335
  -9.500  -0.7585   0.05684   0.05030  -0.0248   1.0000   0.0334
  -9.250  -0.7601   0.05342   0.04659  -0.0229   1.0000   0.0334
  -9.000  -0.7585   0.05015   0.04298  -0.0208   1.0000   0.0334
  -8.750  -0.7541   0.04703   0.03950  -0.0187   1.0000   0.0336
  -8.500  -0.7502   0.04405   0.03593  -0.0159   1.0000   0.0342
  -8.250  -0.7352   0.04191   0.03375  -0.0148   1.0000   0.0350
  -8.000  -0.7197   0.04013   0.03186  -0.0135   1.0000   0.0359
  -7.750  -0.7048   0.03815   0.02965  -0.0118   1.0000   0.0367
  -7.500  -0.6891   0.03607   0.02730  -0.0100   1.0000   0.0371
  -7.250  -0.6720   0.03412   0.02506  -0.0083   1.0000   0.0376
  -7.000  -0.6537   0.03233   0.02301  -0.0066   1.0000   0.0382
  -6.750  -0.6345   0.03074   0.02115  -0.0050   1.0000   0.0392
  -6.500  -0.6151   0.02950   0.01954  -0.0032   1.0000   0.0407
  -6.250  -0.5942   0.02799   0.01807  -0.0022   1.0000   0.0420
  -6.000  -0.5727   0.02679   0.01683  -0.0010   1.0000   0.0431
  -5.750  -0.5510   0.02563   0.01563   0.0002   1.0000   0.0441
  -5.500  -0.5294   0.02458   0.01452   0.0015   1.0000   0.0454
  -5.250  -0.5083   0.02374   0.01358   0.0029   1.0000   0.0475
  -5.000  -0.4880   0.02278   0.01264   0.0043   1.0000   0.0494
  -4.750  -0.4687   0.02190   0.01185   0.0058   1.0000   0.0512
  -4.500  -0.4500   0.02114   0.01113   0.0074   1.0000   0.0529
  -4.250  -0.4317   0.02051   0.01050   0.0091   1.0000   0.0552
  -4.000  -0.4134   0.02001   0.00997   0.0108   1.0000   0.0580
  -3.750  -0.3916   0.01924   0.00926   0.0115   0.9979   0.0612
  -3.500  -0.3531   0.01859   0.00856   0.0091   0.9894   0.0659
  -3.250  -0.3145   0.01793   0.00787   0.0067   0.9804   0.0730
  -3.000  -0.2750   0.01736   0.00726   0.0043   0.9710   0.0830
  -2.750  -0.2400   0.01634   0.00660   0.0025   0.9599   0.1285
  -2.500  -0.2165   0.01420   0.00633   0.0025   0.9481   0.5070
  -2.250  -0.1855   0.01363   0.00635   0.0026   0.9356   0.6428
  -2.000  -0.1517   0.01341   0.00645   0.0026   0.9227   0.7296
  -1.750  -0.1174   0.01338   0.00656   0.0027   0.9080   0.7921
  -1.500  -0.0817   0.01353   0.00679   0.0028   0.8918   0.8449
  -1.250  -0.0454   0.01365   0.00686   0.0024   0.8731   0.8760
  -1.000  -0.0101   0.01367   0.00677   0.0017   0.8514   0.8922
  -0.750   0.0273   0.01369   0.00667   0.0006   0.8280   0.9047
  -0.500   0.0635   0.01372   0.00656  -0.0003   0.8014   0.9166
  -0.250   0.0978   0.01376   0.00644  -0.0008   0.7716   0.9285
   0.000   0.1304   0.01382   0.00631  -0.0011   0.7371   0.9407
   0.250   0.1696   0.01390   0.00619  -0.0029   0.6976   0.9485
   0.500   0.2048   0.01401   0.00607  -0.0040   0.6593   0.9583
   0.750   0.2422   0.01413   0.00598  -0.0057   0.6220   0.9669
   1.000   0.2795   0.01425   0.00591  -0.0075   0.5862   0.9750
   1.250   0.3157   0.01440   0.00587  -0.0092   0.5507   0.9836
   1.500   0.3542   0.01453   0.00581  -0.0114   0.5143   0.9908
   1.750   0.3921   0.01470   0.00578  -0.0137   0.4774   0.9977
   2.000   0.4195   0.01487   0.00578  -0.0139   0.4448   1.0000
   2.250   0.4414   0.01506   0.00582  -0.0129   0.4152   1.0000
   2.500   0.4631   0.01529   0.00588  -0.0120   0.3862   1.0000
   2.750   0.4846   0.01555   0.00599  -0.0110   0.3579   1.0000
   3.000   0.5061   0.01583   0.00613  -0.0100   0.3310   1.0000
   3.250   0.5272   0.01615   0.00630  -0.0089   0.3076   1.0000
   3.500   0.5486   0.01647   0.00653  -0.0079   0.2867   1.0000
   3.750   0.5697   0.01682   0.00677  -0.0068   0.2686   1.0000
   4.000   0.5907   0.01720   0.00705  -0.0057   0.2531   1.0000
   4.250   0.6117   0.01759   0.00735  -0.0046   0.2403   1.0000
   4.500   0.6326   0.01800   0.00770  -0.0035   0.2297   1.0000
   4.750   0.6539   0.01840   0.00807  -0.0024   0.2202   1.0000
   5.000   0.6745   0.01887   0.00844  -0.0012   0.2124   1.0000
   5.250   0.6961   0.01928   0.00889  -0.0002   0.2044   1.0000
   5.500   0.7168   0.01977   0.00931   0.0010   0.1981   1.0000
   5.750   0.7384   0.02024   0.00981   0.0020   0.1922   1.0000
   6.000   0.7597   0.02073   0.01032   0.0031   0.1864   1.0000
   6.250   0.7804   0.02131   0.01081   0.0042   0.1816   1.0000
   6.500   0.8022   0.02181   0.01142   0.0052   0.1763   1.0000
   6.750   0.8237   0.02237   0.01200   0.0061   0.1717   1.0000
   7.000   0.8450   0.02299   0.01258   0.0071   0.1677   1.0000
   7.250   0.8667   0.02361   0.01330   0.0080   0.1634   1.0000
   7.500   0.8883   0.02422   0.01401   0.0089   0.1589   1.0000
   7.750   0.9098   0.02487   0.01468   0.0098   0.1550   1.0000
   8.000   0.9314   0.02563   0.01539   0.0106   0.1516   1.0000
   8.250   0.9524   0.02634   0.01632   0.0115   0.1475   1.0000
   8.500   0.9733   0.02707   0.01718   0.0123   0.1435   1.0000
   8.750   0.9943   0.02780   0.01793   0.0132   0.1401   1.0000
   9.000   1.0153   0.02866   0.01878   0.0139   0.1369   1.0000
   9.250   1.0344   0.02955   0.01995   0.0149   0.1330   1.0000
   9.500   1.0535   0.03040   0.02097   0.0159   0.1292   1.0000
   9.750   1.0731   0.03119   0.02181   0.0168   0.1260   1.0000
  10.000   1.0928   0.03211   0.02271   0.0175   0.1231   1.0000
  10.250   1.1079   0.03323   0.02420   0.0189   0.1193   1.0000
  10.500   1.1238   0.03425   0.02540   0.0201   0.1158   1.0000
  10.750   1.1407   0.03506   0.02628   0.0211   0.1126   1.0000
  11.000   1.1577   0.03598   0.02720   0.0221   0.1099   1.0000
  11.250   1.1665   0.03747   0.02907   0.0238   0.1064   1.0000
  11.500   1.1767   0.03868   0.03051   0.0254   0.1031   1.0000
  11.750   1.1888   0.03958   0.03147   0.0267   0.1003   1.0000
  12.000   1.2022   0.04045   0.03230   0.0279   0.0980   1.0000
  12.250   1.1980   0.04245   0.03469   0.0306   0.0952   1.0000
  12.500   1.1954   0.04430   0.03679   0.0327   0.0926   1.0000
  12.750   1.1962   0.04594   0.03858   0.0341   0.0902   1.0000
  13.000   1.2010   0.04728   0.03996   0.0351   0.0881   1.0000
  13.250   1.2021   0.04919   0.04194   0.0358   0.0862   1.0000
  13.500   1.1846   0.05327   0.04638   0.0357   0.0843   1.0000
  13.750   1.1658   0.05798   0.05137   0.0343   0.0827   1.0000
  14.000   1.1436   0.06368   0.05732   0.0318   0.0814   1.0000
  14.250   1.1086   0.07202   0.06591   0.0270   0.0806   1.0000
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