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MH 121 8.76% (mh121-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: MH 121 8.76% (mh121-il)
Reynolds number: 200,000
Max Cl/Cd: 82.42 at α=3.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-mh121-il-200000-n5.txt
Download as CSV file: xf-mh121-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: MH 121  8.76%                                   
  
 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  -0.4147   0.10977   0.10617  -0.0361   1.0000   0.0122
  -9.500  -0.4163   0.10649   0.10293  -0.0360   1.0000   0.0106
  -9.250  -0.4198   0.10300   0.09950  -0.0360   1.0000   0.0096
  -9.000  -0.4250   0.09951   0.09606  -0.0359   1.0000   0.0087
  -8.500  -0.4357   0.09103   0.08772  -0.0373   0.9992   0.0067
  -8.250  -0.4220   0.08671   0.08340  -0.0417   0.9963   0.0064
  -8.000  -0.4085   0.08296   0.07962  -0.0456   0.9933   0.0061
  -7.750  -0.4045   0.07755   0.07423  -0.0505   0.9880   0.0059
  -7.500  -0.3963   0.07151   0.06821  -0.0577   0.9823   0.0059
  -7.250  -0.3877   0.06399   0.06069  -0.0679   0.9735   0.0056
  -7.000  -0.3738   0.05588   0.05241  -0.0791   0.9667   0.0055
  -6.750  -0.3607   0.04965   0.04595  -0.0852   0.9598   0.0055
  -6.500  -0.3399   0.04343   0.03939  -0.0910   0.9561   0.0054
  -6.250  -0.3255   0.03871   0.03433  -0.0928   0.9494   0.0053
  -6.000  -0.3000   0.03378   0.02894  -0.0957   0.9463   0.0055
  -5.750  -0.2703   0.02977   0.02442  -0.0981   0.9443   0.0058
  -5.500  -0.2484   0.02641   0.02052  -0.0984   0.9394   0.0067
  -5.250  -0.2230   0.02468   0.01856  -0.1000   0.9364   0.0095
  -5.000  -0.1923   0.02217   0.01550  -0.1009   0.9345   0.0101
  -4.750  -0.1606   0.01993   0.01287  -0.1017   0.9331   0.0100
  -4.500  -0.1284   0.01812   0.01080  -0.1025   0.9319   0.0101
  -4.250  -0.0960   0.01664   0.00914  -0.1035   0.9309   0.0103
  -4.000  -0.0745   0.01571   0.00808  -0.1024   0.9259   0.0106
  -3.750  -0.0444   0.01477   0.00697  -0.1031   0.9236   0.0115
  -3.500  -0.0119   0.01404   0.00601  -0.1042   0.9218   0.0136
  -3.250   0.0216   0.01292   0.00517  -0.1059   0.9204   0.0873
  -3.000   0.0531   0.01134   0.00490  -0.1084   0.9193   0.4237
  -2.750   0.0860   0.01117   0.00476  -0.1095   0.9181   0.4831
  -2.500   0.1094   0.01118   0.00468  -0.1087   0.9135   0.5162
  -2.250   0.1381   0.01112   0.00465  -0.1089   0.9107   0.5545
  -2.000   0.1684   0.01106   0.00461  -0.1095   0.9086   0.5868
  -1.750   0.2004   0.01099   0.00450  -0.1104   0.9069   0.6029
  -1.500   0.2332   0.01092   0.00437  -0.1115   0.9055   0.6151
  -1.250   0.2582   0.01095   0.00433  -0.1111   0.9015   0.6264
  -1.000   0.2858   0.01095   0.00432  -0.1111   0.8981   0.6380
  -0.750   0.3162   0.01091   0.00429  -0.1118   0.8957   0.6504
  -0.500   0.3479   0.01086   0.00425  -0.1127   0.8938   0.6632
  -0.250   0.3804   0.01079   0.00422  -0.1137   0.8921   0.6766
   0.000   0.4029   0.01087   0.00437  -0.1127   0.8870   0.6903
   0.250   0.4313   0.01085   0.00442  -0.1129   0.8836   0.7052
   0.500   0.4623   0.01078   0.00443  -0.1136   0.8810   0.7214
   0.750   0.4948   0.01069   0.00442  -0.1145   0.8788   0.7391
   1.000   0.5160   0.01076   0.00459  -0.1132   0.8724   0.7583
   1.250   0.5454   0.01067   0.00466  -0.1134   0.8685   0.7799
   1.500   0.5754   0.01055   0.00466  -0.1136   0.8646   0.8039
   1.750   0.5976   0.01051   0.00476  -0.1123   0.8573   0.8331
   2.000   0.6275   0.01030   0.00468  -0.1122   0.8518   0.8685
   2.250   0.6520   0.01013   0.00466  -0.1111   0.8423   0.9275
   2.500   0.6850   0.00995   0.00456  -0.1119   0.8303   1.0000
   2.750   0.7157   0.00975   0.00446  -0.1120   0.8128   1.0000
   3.000   0.7408   0.00965   0.00440  -0.1110   0.7888   1.0000
   3.250   0.7663   0.00961   0.00439  -0.1102   0.7617   1.0000
   3.500   0.7912   0.00960   0.00434  -0.1091   0.7144   1.0000
   3.750   0.8099   0.01012   0.00417  -0.1065   0.5710   1.0000
   4.000   0.8134   0.01149   0.00469  -0.1017   0.4135   1.0000
   4.250   0.8206   0.01287   0.00537  -0.0982   0.2736   1.0000
   4.500   0.8276   0.01461   0.00619  -0.0951   0.1141   1.0000
   4.750   0.8407   0.01605   0.00696  -0.0929   0.0257   1.0000
   5.000   0.8595   0.01704   0.00797  -0.0913   0.0055   1.0000
   5.250   0.8805   0.01783   0.00894  -0.0899   0.0046   1.0000
   5.500   0.9006   0.01878   0.01009  -0.0884   0.0041   1.0000
   5.750   0.9197   0.01989   0.01138  -0.0867   0.0038   1.0000
   6.000   0.9384   0.02121   0.01286  -0.0850   0.0036   1.0000
   6.250   0.9584   0.02278   0.01460  -0.0835   0.0035   1.0000
   6.500   0.9809   0.02472   0.01675  -0.0824   0.0034   1.0000
   6.750   1.0057   0.02699   0.01928  -0.0817   0.0034   1.0000
   7.000   1.0303   0.02973   0.02238  -0.0808   0.0034   1.0000
   7.250   1.0517   0.03292   0.02602  -0.0793   0.0035   1.0000
   7.500   1.0683   0.03646   0.03004  -0.0771   0.0036   1.0000
   7.750   1.0797   0.04032   0.03438  -0.0743   0.0037   1.0000
   8.000   1.0863   0.04439   0.03892  -0.0711   0.0038   1.0000
   8.250   1.0885   0.04862   0.04355  -0.0675   0.0039   1.0000
   8.500   1.0865   0.05284   0.04814  -0.0638   0.0040   1.0000
   8.750   1.0807   0.05698   0.05259  -0.0601   0.0041   1.0000
   9.000   1.0699   0.06073   0.05660  -0.0561   0.0041   1.0000
   9.250   1.0553   0.06436   0.06044  -0.0521   0.0042   1.0000
   9.500   1.0388   0.06819   0.06446  -0.0489   0.0043   1.0000
   9.750   1.0212   0.07231   0.06875  -0.0469   0.0043   1.0000
  10.000   1.0024   0.07696   0.07357  -0.0460   0.0043   1.0000
  10.250   0.9832   0.08225   0.07900  -0.0465   0.0043   1.0000
  10.500   0.9645   0.08830   0.08518  -0.0487   0.0044   1.0000
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