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MH 117 9.8% (mh117-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: MH 117 9.8% (mh117-il)
Reynolds number: 200,000
Max Cl/Cd: 71.96 at α=4.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-mh117-il-200000-n5.txt
Download as CSV file: xf-mh117-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: MH 117  9.8%                                    
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.4660   0.08478   0.08124  -0.0335   1.0000   0.0103
  -9.500  -0.5632   0.05815   0.05464  -0.0480   1.0000   0.0084
  -9.250  -0.5854   0.04977   0.04625  -0.0557   1.0000   0.0081
  -9.000  -0.6034   0.04369   0.03995  -0.0595   1.0000   0.0076
  -8.750  -0.6135   0.03883   0.03467  -0.0604   1.0000   0.0081
  -8.500  -0.6154   0.03512   0.03062  -0.0596   1.0000   0.0080
  -8.250  -0.6105   0.03229   0.02737  -0.0585   1.0000   0.0084
  -8.000  -0.6044   0.02955   0.02425  -0.0569   1.0000   0.0087
  -7.750  -0.5846   0.02688   0.02126  -0.0577   0.9970   0.0090
  -7.500  -0.5543   0.02458   0.01863  -0.0598   0.9915   0.0093
  -7.250  -0.5234   0.02267   0.01645  -0.0615   0.9857   0.0097
  -7.000  -0.4915   0.02103   0.01453  -0.0632   0.9802   0.0101
  -6.750  -0.4606   0.01962   0.01290  -0.0645   0.9734   0.0108
  -6.500  -0.4271   0.01833   0.01138  -0.0661   0.9684   0.0117
  -6.250  -0.3968   0.01723   0.01009  -0.0669   0.9603   0.0128
  -6.000  -0.3636   0.01617   0.00890  -0.0685   0.9544   0.0152
  -5.750  -0.3331   0.01532   0.00798  -0.0692   0.9457   0.0206
  -5.500  -0.3005   0.01446   0.00706  -0.0704   0.9386   0.0322
  -5.250  -0.2687   0.01384   0.00649  -0.0714   0.9303   0.0513
  -5.000  -0.2367   0.01345   0.00607  -0.0723   0.9217   0.0697
  -4.750  -0.2043   0.01305   0.00567  -0.0733   0.9137   0.0865
  -4.500  -0.1743   0.01270   0.00529  -0.0738   0.9035   0.1010
  -4.250  -0.1442   0.01237   0.00491  -0.0742   0.8938   0.1154
  -3.750  -0.0860   0.01179   0.00428  -0.0746   0.8734   0.1498
  -3.500  -0.0580   0.01153   0.00402  -0.0746   0.8629   0.1704
  -3.250  -0.0301   0.01130   0.00377  -0.0745   0.8528   0.1931
  -3.000  -0.0026   0.01108   0.00357  -0.0744   0.8428   0.2204
  -2.750   0.0244   0.01088   0.00340  -0.0741   0.8322   0.2492
  -2.500   0.0515   0.01070   0.00325  -0.0739   0.8224   0.2812
  -2.250   0.0785   0.01051   0.00311  -0.0737   0.8130   0.3169
  -2.000   0.1052   0.01033   0.00301  -0.0734   0.8028   0.3558
  -1.750   0.1318   0.01015   0.00292  -0.0731   0.7933   0.4000
  -1.500   0.1583   0.00998   0.00285  -0.0727   0.7844   0.4495
  -1.250   0.1844   0.00979   0.00281  -0.0723   0.7745   0.5040
  -1.000   0.2102   0.00962   0.00279  -0.0717   0.7653   0.5631
  -0.500   0.2600   0.00927   0.00280  -0.0700   0.7466   0.6928
  -0.250   0.2838   0.00912   0.00282  -0.0686   0.7371   0.7606
   0.000   0.3078   0.00901   0.00283  -0.0672   0.7279   0.8286
   0.250   0.3365   0.00894   0.00282  -0.0668   0.7174   0.8954
   0.500   0.3757   0.00890   0.00277  -0.0689   0.7069   0.9547
   0.750   0.4166   0.00891   0.00271  -0.0716   0.6962   1.0000
   1.250   0.4679   0.00910   0.00274  -0.0705   0.6744   1.0000
   1.500   0.4937   0.00919   0.00278  -0.0701   0.6631   1.0000
   1.750   0.5197   0.00930   0.00282  -0.0696   0.6516   1.0000
   2.000   0.5457   0.00941   0.00289  -0.0692   0.6396   1.0000
   2.250   0.5717   0.00953   0.00295  -0.0687   0.6271   1.0000
   2.500   0.5977   0.00965   0.00303  -0.0682   0.6139   1.0000
   2.750   0.6236   0.00978   0.00312  -0.0678   0.5999   1.0000
   3.000   0.6495   0.00992   0.00324  -0.0673   0.5850   1.0000
   3.250   0.6753   0.01007   0.00335  -0.0668   0.5689   1.0000
   3.500   0.7009   0.01023   0.00348  -0.0663   0.5513   1.0000
   3.750   0.7263   0.01041   0.00362  -0.0658   0.5321   1.0000
   4.000   0.7514   0.01061   0.00379  -0.0652   0.5106   1.0000
   4.250   0.7761   0.01085   0.00396  -0.0645   0.4861   1.0000
   4.500   0.8002   0.01112   0.00416  -0.0638   0.4581   1.0000
   4.750   0.8238   0.01145   0.00440  -0.0630   0.4254   1.0000
   5.000   0.8465   0.01186   0.00467  -0.0621   0.3897   1.0000
   5.250   0.8688   0.01232   0.00499  -0.0612   0.3531   1.0000
   5.500   0.8907   0.01283   0.00535  -0.0603   0.3185   1.0000
   5.750   0.9126   0.01336   0.00576  -0.0594   0.2847   1.0000
   6.000   0.9344   0.01390   0.00621  -0.0585   0.2539   1.0000
   6.250   0.9563   0.01445   0.00667  -0.0577   0.2267   1.0000
   6.500   0.9779   0.01502   0.00716  -0.0568   0.2012   1.0000
   6.750   0.9990   0.01563   0.00768  -0.0559   0.1764   1.0000
   7.000   1.0202   0.01622   0.00823  -0.0550   0.1551   1.0000
   7.250   1.0410   0.01685   0.00884  -0.0541   0.1362   1.0000
   7.500   1.0615   0.01750   0.00945  -0.0531   0.1183   1.0000
   7.750   1.0815   0.01817   0.01010  -0.0520   0.1031   1.0000
   8.000   1.1011   0.01885   0.01078  -0.0509   0.0906   1.0000
   8.250   1.1202   0.01957   0.01150  -0.0498   0.0797   1.0000
   8.500   1.1384   0.02033   0.01228  -0.0485   0.0709   1.0000
   8.750   1.1564   0.02108   0.01307  -0.0472   0.0632   1.0000
   9.000   1.1737   0.02187   0.01395  -0.0458   0.0568   1.0000
   9.250   1.1897   0.02271   0.01483  -0.0443   0.0511   1.0000
   9.500   1.2047   0.02359   0.01580  -0.0427   0.0464   1.0000
   9.750   1.2191   0.02441   0.01670  -0.0410   0.0413   1.0000
  10.000   1.2291   0.02544   0.01776  -0.0387   0.0371   1.0000
  10.250   1.2427   0.02625   0.01870  -0.0370   0.0326   1.0000
  10.500   1.2515   0.02738   0.01985  -0.0348   0.0286   1.0000
  10.750   1.2623   0.02842   0.02101  -0.0330   0.0253   1.0000
  11.000   1.2720   0.02956   0.02222  -0.0313   0.0217   1.0000
  11.250   1.2783   0.03100   0.02377  -0.0294   0.0189   1.0000
  11.500   1.2859   0.03240   0.02530  -0.0278   0.0164   1.0000
  11.750   1.2887   0.03426   0.02721  -0.0261   0.0142   1.0000
  12.000   1.2932   0.03606   0.02916  -0.0247   0.0124   1.0000
  12.250   1.2979   0.03792   0.03113  -0.0237   0.0105   1.0000
  12.500   1.2970   0.04038   0.03370  -0.0226   0.0097   1.0000
  12.750   1.2952   0.04307   0.03654  -0.0218   0.0091   1.0000
  13.000   1.2946   0.04578   0.03944  -0.0213   0.0084   1.0000
  13.250   1.2913   0.04892   0.04276  -0.0211   0.0077   1.0000
  13.500   1.2877   0.05224   0.04624  -0.0212   0.0073   1.0000
  13.750   1.2826   0.05590   0.05007  -0.0217   0.0070   1.0000
  14.000   1.2756   0.06000   0.05433  -0.0226   0.0068   1.0000
  14.250   1.2668   0.06456   0.05906  -0.0240   0.0066   1.0000
  14.500   1.2560   0.06966   0.06432  -0.0258   0.0064   1.0000
  14.750   1.2426   0.07549   0.07032  -0.0283   0.0063   1.0000
  15.000   1.2323   0.08112   0.07612  -0.0308   0.0063   1.0000
  15.250   1.2146   0.08844   0.08360  -0.0344   0.0061   1.0000
  15.500   1.2017   0.09524   0.09057  -0.0380   0.0061   1.0000
  15.750   1.1878   0.10254   0.09804  -0.0419   0.0061   1.0000
  16.000   1.1735   0.11019   0.10585  -0.0461   0.0061   1.0000
  16.250   1.1581   0.11838   0.11421  -0.0508   0.0061   1.0000
  16.500   1.1436   0.12658   0.12255  -0.0555   0.0061   1.0000
  16.750   1.1282   0.13531   0.13143  -0.0605   0.0061   1.0000
  17.250   1.1010   0.15259   0.14899  -0.0706   0.0062   1.0000
  17.500   1.0873   0.16179   0.15832  -0.0760   0.0063   1.0000
  17.750   1.0715   0.17198   0.16863  -0.0819   0.0064   1.0000
  18.000   1.0508   0.18449   0.18127  -0.0890   0.0065   1.0000
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