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MH 24 9.01% (mh24-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: MH 24 9.01% (mh24-il)
Reynolds number: 200,000
Max Cl/Cd: 68.43 at α=3.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-mh24-il-200000.txt
Download as CSV file: xf-mh24-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: MH 24  9.01%                                    
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.4928   0.08873   0.08536  -0.0425   1.0000   0.0364
  -8.750  -0.5076   0.08543   0.08207  -0.0429   1.0000   0.0364
  -8.500  -0.5266   0.08325   0.07989  -0.0404   1.0000   0.0364
  -8.250  -0.5462   0.08116   0.07780  -0.0370   1.0000   0.0364
  -8.000  -0.5600   0.07871   0.07530  -0.0344   1.0000   0.0365
  -7.750  -0.5723   0.07614   0.07264  -0.0318   1.0000   0.0365
  -7.500  -0.5823   0.07350   0.06989  -0.0290   1.0000   0.0366
  -7.250  -0.5997   0.06702   0.06339  -0.0269   1.0000   0.0373
  -7.000  -0.6003   0.06310   0.05954  -0.0249   1.0000   0.0383
  -6.750  -0.6001   0.06041   0.05685  -0.0226   1.0000   0.0391
  -6.500  -0.5995   0.05775   0.05413  -0.0202   1.0000   0.0403
  -6.250  -0.5977   0.05505   0.05133  -0.0179   1.0000   0.0416
  -6.000  -0.5947   0.05217   0.04830  -0.0156   1.0000   0.0435
  -5.750  -0.5894   0.04926   0.04512  -0.0131   1.0000   0.0469
  -5.500  -0.5894   0.04598   0.04124  -0.0095   1.0000   0.0506
  -5.250  -0.5792   0.04265   0.03800  -0.0081   1.0000   0.0523
  -5.000  -0.5681   0.04036   0.03564  -0.0062   1.0000   0.0551
  -4.750  -0.5587   0.03858   0.03322  -0.0030   1.0000   0.0636
  -4.500  -0.5445   0.03547   0.03015  -0.0018   1.0000   0.0661
  -4.250  -0.5288   0.03366   0.02814   0.0001   1.0000   0.0716
  -4.000  -0.5144   0.03140   0.02568   0.0019   1.0000   0.0802
  -3.750  -0.4765   0.02471   0.01762   0.0069   1.0000   0.0241
  -3.500  -0.4549   0.02212   0.01468   0.0086   1.0000   0.0221
  -3.250  -0.4321   0.02030   0.01257   0.0102   1.0000   0.0204
  -3.000  -0.4094   0.01882   0.01088   0.0117   1.0000   0.0197
  -2.750  -0.3865   0.01770   0.00964   0.0129   0.9997   0.0190
  -2.500  -0.3516   0.01669   0.00856   0.0117   0.9960   0.0199
  -2.250  -0.3169   0.01604   0.00779   0.0103   0.9919   0.0217
  -2.000  -0.2830   0.01533   0.00690   0.0093   0.9869   0.0346
  -1.750  -0.1522   0.01352   0.00875  -0.0081   1.0000   0.9932
  -1.500  -0.1002   0.01369   0.00869  -0.0136   1.0000   1.0000
  -1.250  -0.0842   0.01371   0.00861  -0.0121   0.9992   1.0000
  -1.000  -0.0377   0.01388   0.00860  -0.0165   0.9941   1.0000
  -0.750   0.0044   0.01392   0.00854  -0.0200   0.9878   1.0000
  -0.500   0.0509   0.01408   0.00860  -0.0244   0.9827   1.0000
  -0.250   0.0918   0.01409   0.00853  -0.0276   0.9756   1.0000
   0.000   0.1394   0.01416   0.00854  -0.0320   0.9703   1.0000
   0.250   0.1794   0.01411   0.00846  -0.0348   0.9625   1.0000
   0.500   0.2293   0.01405   0.00841  -0.0396   0.9572   1.0000
   0.750   0.2689   0.01393   0.00829  -0.0422   0.9488   1.0000
   1.000   0.3213   0.01374   0.00812  -0.0473   0.9440   1.0000
   1.250   0.3623   0.01351   0.00793  -0.0500   0.9353   1.0000
   1.500   0.4201   0.01313   0.00763  -0.0560   0.9309   1.0000
   1.750   0.4617   0.01274   0.00732  -0.0586   0.9212   1.0000
   2.000   0.5048   0.01226   0.00692  -0.0613   0.9122   1.0000
   2.250   0.5407   0.01176   0.00650  -0.0624   0.9005   1.0000
   2.500   0.5645   0.01135   0.00621  -0.0609   0.8832   1.0000
   2.750   0.5888   0.01090   0.00584  -0.0595   0.8640   1.0000
   3.000   0.6099   0.01054   0.00554  -0.0575   0.8375   1.0000
   3.250   0.6348   0.01016   0.00519  -0.0562   0.8018   1.0000
   3.500   0.6642   0.00987   0.00480  -0.0555   0.7457   1.0000
   3.750   0.6864   0.01003   0.00467  -0.0537   0.6752   1.0000
   4.000   0.7030   0.01044   0.00477  -0.0512   0.6006   1.0000
   4.250   0.7172   0.01097   0.00497  -0.0484   0.5276   1.0000
   4.500   0.7306   0.01155   0.00525  -0.0455   0.4560   1.0000
   4.750   0.7437   0.01216   0.00558  -0.0428   0.3883   1.0000
   5.000   0.7566   0.01281   0.00595  -0.0402   0.3230   1.0000
   5.250   0.7700   0.01347   0.00636  -0.0376   0.2618   1.0000
   5.500   0.7825   0.01422   0.00688  -0.0351   0.2016   1.0000
   5.750   0.7950   0.01502   0.00742  -0.0325   0.1481   1.0000
   6.000   0.8071   0.01591   0.00807  -0.0298   0.1031   1.0000
   6.250   0.8173   0.01697   0.00893  -0.0267   0.0717   1.0000
   6.500   0.8268   0.01809   0.01002  -0.0232   0.0563   1.0000
   6.750   0.8377   0.01914   0.01110  -0.0200   0.0474   1.0000
   7.000   0.8493   0.02041   0.01247  -0.0169   0.0420   1.0000
   7.250   0.8625   0.02131   0.01340  -0.0143   0.0360   1.0000
   7.500   0.8767   0.02301   0.01524  -0.0118   0.0311   1.0000
   8.000   0.9000   0.02491   0.01737  -0.0063   0.0173   1.0000
   8.250   0.9121   0.02685   0.01943  -0.0037   0.0151   1.0000
   8.500   0.9230   0.03077   0.02371  -0.0010   0.0141   1.0000
   8.750   0.9265   0.03478   0.02819   0.0027   0.0136   1.0000
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