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MH 110 10.01% (mh110-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: MH 110 10.01% (mh110-il)
Reynolds number: 100,000
Max Cl/Cd: 41.03 at α=8.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-mh110-il-100000-n5.txt
Download as CSV file: xf-mh110-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: MH 110  10.01%                                  
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.6621   0.09152   0.08704   0.0166   1.0000   0.0145
  -9.500  -0.6854   0.07625   0.07174   0.0057   1.0000   0.0133
  -9.250  -0.7028   0.06898   0.06433  -0.0004   1.0000   0.0130
  -9.000  -0.7167   0.06465   0.05985  -0.0020   1.0000   0.0129
  -8.750  -0.7323   0.06076   0.05577  -0.0013   1.0000   0.0128
  -8.500  -0.7423   0.05672   0.05153  -0.0004   1.0000   0.0127
  -8.250  -0.7476   0.05272   0.04725   0.0007   1.0000   0.0127
  -8.000  -0.7484   0.04879   0.04300   0.0021   1.0000   0.0126
  -7.750  -0.7453   0.04498   0.03880   0.0037   1.0000   0.0126
  -7.500  -0.7380   0.04144   0.03484   0.0053   1.0000   0.0127
  -7.250  -0.7268   0.03823   0.03121   0.0070   1.0000   0.0127
  -7.000  -0.7125   0.03530   0.02784   0.0085   1.0000   0.0128
  -6.750  -0.6970   0.03215   0.02431   0.0101   1.0000   0.0132
  -6.500  -0.6792   0.02980   0.02174   0.0112   1.0000   0.0142
  -6.250  -0.6585   0.02828   0.02004   0.0121   1.0000   0.0156
  -6.000  -0.6362   0.02663   0.01810   0.0131   1.0000   0.0172
  -5.750  -0.6130   0.02490   0.01614   0.0142   1.0000   0.0186
  -5.500  -0.5900   0.02324   0.01430   0.0154   1.0000   0.0197
  -5.250  -0.5689   0.02161   0.01256   0.0168   1.0000   0.0211
  -5.000  -0.5479   0.02032   0.01123   0.0179   1.0000   0.0246
  -4.750  -0.5254   0.01933   0.01013   0.0191   1.0000   0.0307
  -4.500  -0.5041   0.01814   0.00889   0.0205   1.0000   0.0412
  -4.250  -0.4839   0.01679   0.00786   0.0218   1.0000   0.0796
  -4.000  -0.4642   0.01555   0.00714   0.0229   1.0000   0.1646
  -3.750  -0.4440   0.01457   0.00667   0.0240   1.0000   0.2604
  -3.500  -0.4238   0.01376   0.00629   0.0253   1.0000   0.3533
  -3.250  -0.4037   0.01306   0.00600   0.0267   1.0000   0.4462
  -3.000  -0.3682   0.01243   0.00577   0.0254   0.9271   0.5577
  -2.750  -0.3287   0.01207   0.00564   0.0241   0.8586   0.6655
  -2.500  -0.2958   0.01202   0.00556   0.0245   0.8040   0.7460
  -2.250  -0.2604   0.01215   0.00555   0.0244   0.7583   0.8059
  -2.000  -0.2231   0.01237   0.00553   0.0237   0.7177   0.8481
  -1.750  -0.1854   0.01262   0.00550   0.0226   0.6808   0.8788
  -1.500  -0.1486   0.01286   0.00543   0.0216   0.6482   0.9033
  -1.250  -0.1099   0.01309   0.00538   0.0200   0.6174   0.9229
  -1.000  -0.0717   0.01330   0.00534   0.0184   0.5892   0.9403
  -0.750  -0.0324   0.01348   0.00525   0.0163   0.5629   0.9552
  -0.500   0.0079   0.01362   0.00515   0.0140   0.5379   0.9683
  -0.250   0.0495   0.01369   0.00501   0.0111   0.5142   0.9796
   0.000   0.0909   0.01373   0.00482   0.0082   0.4929   0.9896
   0.250   0.1322   0.01372   0.00465   0.0053   0.4722   0.9989
   0.500   0.1574   0.01375   0.00454   0.0055   0.4562   1.0000
   0.750   0.1804   0.01380   0.00447   0.0062   0.4417   1.0000
   1.000   0.2035   0.01387   0.00443   0.0070   0.4279   1.0000
   1.250   0.2269   0.01396   0.00442   0.0077   0.4152   1.0000
   1.500   0.2504   0.01406   0.00443   0.0084   0.4032   1.0000
   1.750   0.2739   0.01419   0.00449   0.0091   0.3919   1.0000
   2.000   0.2975   0.01434   0.00454   0.0098   0.3814   1.0000
   2.250   0.3213   0.01450   0.00465   0.0104   0.3710   1.0000
   2.500   0.3452   0.01468   0.00479   0.0111   0.3617   1.0000
   2.750   0.3690   0.01488   0.00495   0.0118   0.3536   1.0000
   3.000   0.3931   0.01508   0.00516   0.0124   0.3446   1.0000
   3.250   0.4170   0.01531   0.00536   0.0131   0.3368   1.0000
   3.500   0.4411   0.01555   0.00559   0.0138   0.3293   1.0000
   3.750   0.4652   0.01582   0.00590   0.0144   0.3227   1.0000
   4.000   0.4893   0.01610   0.00619   0.0150   0.3162   1.0000
   4.250   0.5134   0.01641   0.00650   0.0157   0.3103   1.0000
   4.500   0.5376   0.01671   0.00687   0.0163   0.3038   1.0000
   4.750   0.5615   0.01705   0.00722   0.0170   0.2988   1.0000
   5.000   0.5858   0.01741   0.00772   0.0176   0.2930   1.0000
   5.250   0.6099   0.01778   0.00814   0.0182   0.2881   1.0000
   5.500   0.6339   0.01818   0.00860   0.0188   0.2834   1.0000
   5.750   0.6580   0.01859   0.00916   0.0194   0.2777   1.0000
   6.000   0.6820   0.01901   0.00969   0.0201   0.2734   1.0000
   6.250   0.7059   0.01949   0.01029   0.0207   0.2689   1.0000
   6.500   0.7296   0.01996   0.01096   0.0213   0.2635   1.0000
   6.750   0.7534   0.02040   0.01147   0.0220   0.2590   1.0000
   7.000   0.7768   0.02092   0.01221   0.0227   0.2533   1.0000
   7.250   0.8001   0.02133   0.01277   0.0234   0.2468   1.0000
   7.500   0.8229   0.02172   0.01336   0.0241   0.2392   1.0000
   7.750   0.8458   0.02190   0.01365   0.0249   0.2303   1.0000
   8.000   0.8678   0.02209   0.01409   0.0257   0.2181   1.0000
   8.250   0.8896   0.02220   0.01440   0.0265   0.2038   1.0000
   8.500   0.9111   0.02241   0.01486   0.0272   0.1855   1.0000
   8.750   0.9323   0.02272   0.01535   0.0280   0.1620   1.0000
   9.000   0.9510   0.02349   0.01614   0.0287   0.1174   1.0000
   9.250   0.9588   0.02581   0.01807   0.0297   0.0694   1.0000
   9.500   0.9638   0.02842   0.02060   0.0309   0.0487   1.0000
   9.750   0.9671   0.03093   0.02319   0.0321   0.0384   1.0000
  10.000   0.9704   0.03319   0.02565   0.0333   0.0325   1.0000
  10.250   0.9646   0.03608   0.02869   0.0342   0.0286   1.0000
  10.500   0.9535   0.03908   0.03182   0.0349   0.0271   1.0000
  10.750   0.9406   0.04306   0.03598   0.0333   0.0257   1.0000
  11.000   0.9280   0.04795   0.04102   0.0305   0.0248   1.0000
  11.250   0.9167   0.05285   0.04603   0.0279   0.0242   1.0000
  11.500   0.9074   0.05740   0.05069   0.0258   0.0238   1.0000
  11.750   0.8981   0.06193   0.05531   0.0238   0.0229   1.0000
  12.000   0.8895   0.06637   0.05981   0.0220   0.0219   1.0000
  12.250   0.8819   0.07069   0.06419   0.0203   0.0209   1.0000
  12.500   0.8750   0.07486   0.06839   0.0188   0.0199   1.0000
  12.750   0.8720   0.07806   0.07158   0.0183   0.0187   1.0000
  13.000   0.8698   0.08181   0.07547   0.0170   0.0181   1.0000
  13.250   0.8641   0.08634   0.08016   0.0151   0.0169   1.0000
  13.500   0.8614   0.09042   0.08434   0.0136   0.0164   1.0000
  13.750   0.8551   0.09543   0.08947   0.0114   0.0153   1.0000
  14.000   0.8514   0.10000   0.09416   0.0095   0.0150   1.0000
  14.250   0.8452   0.10525   0.09952   0.0072   0.0145   1.0000
  14.500   0.8383   0.11085   0.10524   0.0046   0.0143   1.0000
  14.750   0.8298   0.11707   0.11159   0.0017   0.0143   1.0000
  15.000   0.8191   0.12402   0.11865  -0.0017   0.0141   1.0000
  15.250   0.8059   0.13206   0.12682  -0.0057   0.0145   1.0000
  15.500   0.7894   0.14142   0.13629  -0.0102   0.0148   1.0000
  15.750   0.7701   0.15247   0.14739  -0.0153   0.0152   1.0000
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