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MH 114 13.02% (mh114-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: MH 114 13.02% (mh114-il)
Reynolds number: 50,000
Max Cl/Cd: 25.99 at α=7°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-mh114-il-50000-n5.txt
Download as CSV file: xf-mh114-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: MH 114  13.02%                                  
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.500  -0.1437   0.11164   0.10533  -0.0679   0.9343   0.1014
  -7.250  -0.1442   0.10939   0.10312  -0.0682   0.9262   0.1010
  -7.000  -0.1405   0.10281   0.09645  -0.0735   0.9206   0.0581
  -6.750  -0.1438   0.10074   0.09443  -0.0721   0.9117   0.0566
  -6.500  -0.1516   0.09600   0.08972  -0.0777   0.9035   0.0503
  -6.250  -0.1508   0.09347   0.08723  -0.0776   0.8951   0.0500
  -6.000  -0.1364   0.08956   0.08331  -0.0814   0.8901   0.0496
  -5.750  -0.1385   0.08701   0.08079  -0.0815   0.8808   0.0494
  -5.500  -0.1232   0.08266   0.07642  -0.0864   0.8752   0.0490
  -5.250  -0.1200   0.07906   0.07281  -0.0890   0.8666   0.0490
  -5.000  -0.1014   0.07406   0.06774  -0.0951   0.8607   0.0485
  -4.750  -0.0811   0.06872   0.06227  -0.1017   0.8548   0.0480
  -4.500  -0.0607   0.06339   0.05673  -0.1078   0.8477   0.0475
  -4.250  -0.0189   0.05652   0.04938  -0.1183   0.8440   0.0470
  -4.000   0.0348   0.04982   0.04186  -0.1292   0.8417   0.0480
  -3.750   0.0653   0.04624   0.03747  -0.1332   0.8345   0.0502
  -3.500   0.0992   0.04444   0.03552  -0.1358   0.8299   0.0539
  -3.250   0.1455   0.04164   0.03201  -0.1401   0.8271   0.0583
  -3.000   0.1716   0.04055   0.03070  -0.1407   0.8206   0.0635
  -2.750   0.2047   0.03927   0.02894  -0.1419   0.8152   0.0708
  -2.500   0.2417   0.03810   0.02761  -0.1436   0.8115   0.0824
  -2.250   0.2669   0.03755   0.02698  -0.1436   0.8051   0.0952
  -2.000   0.2963   0.03693   0.02632  -0.1443   0.7990   0.1153
  -1.750   0.3363   0.03606   0.02543  -0.1465   0.7954   0.1527
  -1.500   0.3612   0.03586   0.02535  -0.1467   0.7880   0.2000
  -1.250   0.3941   0.03544   0.02514  -0.1481   0.7823   0.2799
  -1.000   0.4329   0.03487   0.02488  -0.1499   0.7788   0.3874
  -0.750   0.4490   0.03524   0.02546  -0.1484   0.7696   0.4642
  -0.500   0.4787   0.03498   0.02539  -0.1481   0.7646   0.5613
  -0.250   0.4993   0.03498   0.02555  -0.1463   0.7582   0.6464
   0.000   0.5130   0.03503   0.02576  -0.1433   0.7503   0.7308
   0.250   0.5313   0.03422   0.02511  -0.1398   0.7462   0.8845
   0.500   0.5465   0.03497   0.02563  -0.1389   0.7350   1.0000
   0.750   0.5863   0.03494   0.02523  -0.1408   0.7310   1.0000
   1.000   0.6034   0.03585   0.02595  -0.1400   0.7208   1.0000
   1.250   0.6392   0.03587   0.02569  -0.1412   0.7160   1.0000
   1.750   0.6902   0.03681   0.02627  -0.1412   0.7008   1.0000
   2.000   0.7261   0.03669   0.02596  -0.1421   0.6966   1.0000
   2.250   0.7398   0.03776   0.02694  -0.1408   0.6856   1.0000
   2.500   0.7785   0.03740   0.02642  -0.1419   0.6822   1.0000
   2.750   0.7884   0.03871   0.02767  -0.1402   0.6702   1.0000
   3.000   0.8263   0.03832   0.02715  -0.1411   0.6666   1.0000
   3.250   0.8360   0.03967   0.02847  -0.1394   0.6547   1.0000
   3.500   0.8734   0.03924   0.02794  -0.1401   0.6510   1.0000
   3.750   0.8826   0.04064   0.02932  -0.1384   0.6390   1.0000
   4.000   0.9197   0.04017   0.02878  -0.1391   0.6352   1.0000
   4.250   0.9282   0.04163   0.03025  -0.1373   0.6232   1.0000
   4.500   0.9655   0.04108   0.02965  -0.1379   0.6193   1.0000
   4.750   0.9730   0.04264   0.03122  -0.1360   0.6072   1.0000
   5.000   1.0108   0.04199   0.03053  -0.1366   0.6034   1.0000
   5.250   1.0167   0.04369   0.03229  -0.1347   0.5911   1.0000
   5.500   1.0554   0.04292   0.03150  -0.1352   0.5874   1.0000
   6.000   1.0994   0.04385   0.03247  -0.1337   0.5712   1.0000
   6.500   1.1431   0.04477   0.03349  -0.1322   0.5551   1.0000
   6.750   1.1438   0.04695   0.03574  -0.1300   0.5422   1.0000
   7.000   1.1867   0.04566   0.03450  -0.1306   0.5388   1.0000
   7.500   1.1910   0.04992   0.03892  -0.1266   0.5145   1.0000
   7.750   1.2257   0.04917   0.03823  -0.1265   0.5091   1.0000
   8.250   1.2663   0.05025   0.03948  -0.1247   0.4925   1.0000
   8.750   1.3076   0.05124   0.04065  -0.1229   0.4757   1.0000
   9.000   1.2998   0.05441   0.04394  -0.1207   0.4629   1.0000
   9.500   1.3366   0.05577   0.04549  -0.1187   0.4457   1.0000
   9.750   1.3314   0.05890   0.04874  -0.1169   0.4337   1.0000
  10.000   1.3749   0.05693   0.04687  -0.1167   0.4285   1.0000
  10.250   1.3613   0.06095   0.05103  -0.1148   0.4159   1.0000
  10.500   1.3690   0.06279   0.05298  -0.1136   0.4062   1.0000
  10.750   1.3936   0.06268   0.05301  -0.1127   0.3982   1.0000
  11.000   1.3813   0.06686   0.05732  -0.1113   0.3863   1.0000
  11.250   1.4282   0.06410   0.05465  -0.1106   0.3807   1.0000
  11.500   1.4047   0.06963   0.06033  -0.1092   0.3682   1.0000
  11.750   1.3984   0.07332   0.06416  -0.1082   0.3574   1.0000
  12.000   1.4324   0.07181   0.06277  -0.1072   0.3505   1.0000
  12.250   1.4074   0.07803   0.06914  -0.1065   0.3383   1.0000
  12.500   1.4510   0.07508   0.06628  -0.1053   0.3321   1.0000
  12.750   1.4263   0.08140   0.07276  -0.1049   0.3205   1.0000
  13.000   1.4016   0.08817   0.07968  -0.1051   0.3088   1.0000
  13.250   1.4496   0.08407   0.07569  -0.1032   0.3031   1.0000
  13.500   1.4095   0.09336   0.08513  -0.1043   0.2908   1.0000
  13.750   1.3911   0.09974   0.09164  -0.1051   0.2801   1.0000
  14.000   1.4243   0.09744   0.08948  -0.1033   0.2737   1.0000
  14.250   1.3844   0.10778   0.09994  -0.1059   0.2617   1.0000
  14.500   1.4419   0.10102   0.09330  -0.1024   0.2571   1.0000
  14.750   1.3891   0.11390   0.10631  -0.1064   0.2449   1.0000
  15.000   1.3558   0.12406   0.11656  -0.1100   0.2336   1.0000
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