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MH 115 11.06% (mh115-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: MH 115 11.06% (mh115-il)
Reynolds number: 50,000
Max Cl/Cd: 37.51 at α=7.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-mh115-il-50000-n5.txt
Download as CSV file: xf-mh115-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: MH 115  11.06%                                  
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.3097   0.12316   0.11698  -0.0326   1.0000   0.0939
  -8.250  -0.3246   0.12252   0.11647  -0.0314   1.0000   0.0942
  -8.000  -0.3383   0.12161   0.11568  -0.0299   1.0000   0.0944
  -7.750  -0.3392   0.11934   0.11347  -0.0327   0.9955   0.0946
  -7.250  -0.3116   0.11082   0.10499  -0.0391   0.9835   0.0951
  -7.000  -0.2887   0.10231   0.09632  -0.0409   0.9792   0.0545
  -6.750  -0.2759   0.09838   0.09241  -0.0438   0.9728   0.0510
  -6.500  -0.2716   0.09300   0.08704  -0.0514   0.9620   0.0457
  -6.250  -0.2589   0.08920   0.08325  -0.0545   0.9543   0.0451
  -6.000  -0.2415   0.08458   0.07862  -0.0603   0.9469   0.0447
  -5.750  -0.2294   0.08027   0.07431  -0.0649   0.9376   0.0445
  -5.500  -0.2064   0.07439   0.06836  -0.0736   0.9309   0.0447
  -5.250  -0.1895   0.06924   0.06314  -0.0796   0.9218   0.0446
  -5.000  -0.1574   0.06249   0.05615  -0.0894   0.9164   0.0446
  -4.750  -0.1334   0.05672   0.05011  -0.0960   0.9081   0.0444
  -4.500  -0.0902   0.04963   0.04242  -0.1061   0.9037   0.0445
  -4.250  -0.0481   0.04371   0.03562  -0.1136   0.8987   0.0459
  -4.000  -0.0174   0.04149   0.03320  -0.1162   0.8925   0.0497
  -3.750   0.0279   0.03787   0.02876  -0.1211   0.8889   0.0546
  -3.500   0.0608   0.03603   0.02659  -0.1230   0.8832   0.0610
  -3.250   0.0951   0.03422   0.02430  -0.1247   0.8774   0.0698
  -3.000   0.1339   0.03276   0.02254  -0.1268   0.8733   0.0824
  -2.750   0.1607   0.03188   0.02147  -0.1269   0.8662   0.0961
  -2.500   0.1939   0.03101   0.02053  -0.1280   0.8606   0.1160
  -2.250   0.2339   0.03010   0.01953  -0.1303   0.8568   0.1494
  -2.000   0.2580   0.02974   0.01918  -0.1300   0.8482   0.1875
  -1.750   0.2958   0.02908   0.01867  -0.1321   0.8435   0.2542
  -1.500   0.3246   0.02875   0.01855  -0.1327   0.8365   0.3322
  -1.250   0.3557   0.02837   0.01847  -0.1334   0.8302   0.4313
  -1.000   0.3907   0.02782   0.01824  -0.1340   0.8263   0.5537
  -0.750   0.4042   0.02784   0.01853  -0.1311   0.8164   0.6526
  -0.500   0.4251   0.02721   0.01817  -0.1281   0.8116   0.8003
  -0.250   0.4428   0.02725   0.01812  -0.1263   0.8010   1.0000
   0.000   0.4836   0.02726   0.01773  -0.1286   0.7965   1.0000
   0.250   0.5062   0.02775   0.01798  -0.1282   0.7867   1.0000
   0.500   0.5449   0.02776   0.01770  -0.1300   0.7817   1.0000
   0.750   0.5671   0.02826   0.01801  -0.1294   0.7719   1.0000
   1.000   0.6048   0.02826   0.01780  -0.1309   0.7667   1.0000
   1.250   0.6265   0.02877   0.01817  -0.1302   0.7568   1.0000
   1.500   0.6641   0.02873   0.01797  -0.1316   0.7513   1.0000
   1.750   0.6849   0.02926   0.01841  -0.1307   0.7412   1.0000
   2.000   0.7230   0.02918   0.01820  -0.1321   0.7357   1.0000
   2.250   0.7426   0.02974   0.01870  -0.1310   0.7251   1.0000
   2.500   0.7817   0.02956   0.01843  -0.1324   0.7198   1.0000
   2.750   0.8000   0.03018   0.01902  -0.1311   0.7086   1.0000
   3.000   0.8406   0.02986   0.01864  -0.1326   0.7036   1.0000
   3.250   0.8577   0.03053   0.01930  -0.1311   0.6918   1.0000
   3.500   0.8827   0.03086   0.01962  -0.1306   0.6824   1.0000
   3.750   0.9161   0.03077   0.01954  -0.1310   0.6748   1.0000
   4.000   0.9359   0.03131   0.02010  -0.1299   0.6636   1.0000
   4.250   0.9764   0.03085   0.01964  -0.1311   0.6575   1.0000
   4.500   0.9933   0.03150   0.02032  -0.1295   0.6452   1.0000
   4.750   1.0148   0.03193   0.02083  -0.1285   0.6340   1.0000
   5.000   1.0544   0.03145   0.02038  -0.1295   0.6269   1.0000
   5.250   1.0714   0.03206   0.02106  -0.1279   0.6142   1.0000
   5.500   1.0917   0.03251   0.02161  -0.1266   0.6022   1.0000
   5.750   1.1189   0.03260   0.02177  -0.1261   0.5915   1.0000
   6.000   1.1514   0.03241   0.02164  -0.1262   0.5814   1.0000
   6.250   1.1690   0.03295   0.02230  -0.1246   0.5682   1.0000
   6.500   1.1881   0.03341   0.02285  -0.1231   0.5552   1.0000
   6.750   1.2094   0.03374   0.02327  -0.1219   0.5424   1.0000
   7.000   1.2328   0.03396   0.02359  -0.1209   0.5297   1.0000
   7.250   1.2573   0.03413   0.02386  -0.1200   0.5167   1.0000
   7.500   1.2817   0.03430   0.02412  -0.1190   0.5034   1.0000
   7.750   1.3015   0.03470   0.02461  -0.1176   0.4892   1.0000
   8.000   1.3177   0.03528   0.02531  -0.1157   0.4745   1.0000
   8.250   1.3338   0.03589   0.02601  -0.1139   0.4597   1.0000
   8.500   1.3494   0.03653   0.02675  -0.1121   0.4446   1.0000
   8.750   1.3642   0.03724   0.02754  -0.1102   0.4294   1.0000
   9.000   1.3782   0.03800   0.02841  -0.1082   0.4141   1.0000
   9.250   1.3910   0.03886   0.02935  -0.1062   0.3987   1.0000
   9.500   1.4026   0.03982   0.03039  -0.1042   0.3833   1.0000
   9.750   1.4128   0.04091   0.03155  -0.1021   0.3680   1.0000
  10.000   1.4216   0.04212   0.03285  -0.1000   0.3528   1.0000
  10.250   1.4289   0.04348   0.03432  -0.0978   0.3380   1.0000
  10.500   1.4350   0.04499   0.03593  -0.0958   0.3234   1.0000
  10.750   1.4400   0.04664   0.03769  -0.0938   0.3091   1.0000
  11.000   1.4440   0.04844   0.03960  -0.0918   0.2952   1.0000
  11.250   1.4476   0.05037   0.04164  -0.0900   0.2818   1.0000
  11.500   1.4506   0.05240   0.04378  -0.0883   0.2686   1.0000
  11.750   1.4537   0.05451   0.04601  -0.0868   0.2561   1.0000
  12.000   1.4574   0.05662   0.04820  -0.0854   0.2440   1.0000
  12.250   1.4613   0.05872   0.05034  -0.0840   0.2322   1.0000
  12.500   1.4589   0.06163   0.05346  -0.0828   0.2209   1.0000
  12.750   1.4580   0.06452   0.05650  -0.0818   0.2104   1.0000
  13.000   1.4589   0.06720   0.05926  -0.0809   0.2001   1.0000
  13.250   1.4599   0.06988   0.06203  -0.0801   0.1903   1.0000
  13.500   1.4543   0.07367   0.06607  -0.0797   0.1813   1.0000
  13.750   1.4543   0.07665   0.06913  -0.0792   0.1724   1.0000
  14.000   1.4498   0.08035   0.07299  -0.0790   0.1640   1.0000
  14.250   1.4447   0.08434   0.07715  -0.0791   0.1563   1.0000
  14.500   1.4449   0.08739   0.08025  -0.0790   0.1482   1.0000
  14.750   1.4325   0.09280   0.08593  -0.0801   0.1417   1.0000
  15.000   1.4362   0.09531   0.08838  -0.0800   0.1338   1.0000
  15.250   1.4179   0.10210   0.09555  -0.0821   0.1285   1.0000
  15.500   1.4209   0.10477   0.09818  -0.0823   0.1209   1.0000
  15.750   1.4012   0.11225   0.10598  -0.0853   0.1165   1.0000
  16.000   1.3922   0.11761   0.11150  -0.0874   0.1107   1.0000
  16.250   1.3849   0.12279   0.11678  -0.0895   0.1053   1.0000
  16.500   1.3615   0.13197   0.12622  -0.0943   0.1022   1.0000
  16.750   1.3720   0.13306   0.12722  -0.0942   0.0944   1.0000
  17.000   1.3425   0.14435   0.13881  -0.1008   0.0929   1.0000
  17.250   1.3011   0.15989   0.15449  -0.1105   0.0925   1.0000
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