Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

MH 70 11.08% (mh70-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: MH 70 11.08% (mh70-il)
Reynolds number: 100,000
Max Cl/Cd: 52.26 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-mh70-il-100000-n5.txt
Download as CSV file: xf-mh70-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: MH 70  11.08%                                   
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.3798   0.09083   0.08603  -0.0287   1.0000   0.0259
  -8.750  -0.3799   0.08656   0.08182  -0.0309   1.0000   0.0251
  -8.500  -0.3985   0.07694   0.07231  -0.0379   1.0000   0.0226
  -8.250  -0.4002   0.07306   0.06851  -0.0401   1.0000   0.0224
  -8.000  -0.4059   0.06881   0.06434  -0.0431   1.0000   0.0222
  -7.750  -0.4136   0.06331   0.05888  -0.0471   1.0000   0.0219
  -7.500  -0.4247   0.05892   0.05448  -0.0483   1.0000   0.0216
  -7.250  -0.4269   0.05371   0.04911  -0.0514   0.9891   0.0212
  -7.000  -0.4103   0.04641   0.04134  -0.0582   0.9729   0.0208
  -6.750  -0.3908   0.04047   0.03481  -0.0624   0.9595   0.0204
  -6.500  -0.3683   0.03593   0.02966  -0.0647   0.9478   0.0203
  -6.250  -0.3430   0.03228   0.02541  -0.0661   0.9376   0.0205
  -6.000  -0.3157   0.02940   0.02199  -0.0670   0.9283   0.0208
  -5.750  -0.2897   0.02711   0.01923  -0.0671   0.9180   0.0213
  -5.500  -0.2614   0.02514   0.01680  -0.0671   0.9094   0.0223
  -5.250  -0.2353   0.02382   0.01534  -0.0670   0.8996   0.0237
  -5.000  -0.2091   0.02277   0.01412  -0.0667   0.8902   0.0262
  -4.750  -0.1826   0.02156   0.01270  -0.0662   0.8817   0.0281
  -4.500  -0.1585   0.02058   0.01168  -0.0655   0.8718   0.0302
  -4.250  -0.1328   0.01970   0.01067  -0.0649   0.8637   0.0345
  -4.000  -0.1082   0.01899   0.00986  -0.0642   0.8540   0.0405
  -3.750  -0.0833   0.01818   0.00903  -0.0635   0.8455   0.0503
  -3.500  -0.0586   0.01741   0.00828  -0.0628   0.8367   0.0706
  -3.250  -0.0348   0.01649   0.00770  -0.0622   0.8280   0.1285
  -3.000  -0.0105   0.01578   0.00735  -0.0616   0.8197   0.2219
  -2.750   0.0135   0.01529   0.00715  -0.0609   0.8107   0.3117
  -2.500   0.0378   0.01483   0.00697  -0.0600   0.8029   0.4014
  -2.250   0.0615   0.01446   0.00684  -0.0590   0.7936   0.4833
  -2.000   0.0860   0.01410   0.00667  -0.0578   0.7862   0.5653
  -1.750   0.1090   0.01381   0.00662  -0.0563   0.7766   0.6512
  -1.500   0.1329   0.01354   0.00652  -0.0544   0.7692   0.7418
  -1.250   0.1608   0.01340   0.00649  -0.0533   0.7596   0.8289
  -1.000   0.2000   0.01330   0.00631  -0.0546   0.7516   0.9015
  -0.750   0.2447   0.01324   0.00610  -0.0575   0.7419   0.9528
  -0.500   0.2927   0.01317   0.00585  -0.0613   0.7323   0.9883
  -0.250   0.3251   0.01316   0.00565  -0.0622   0.7229   1.0000
   0.000   0.3478   0.01324   0.00560  -0.0613   0.7118   1.0000
   0.250   0.3711   0.01330   0.00553  -0.0603   0.7018   1.0000
   0.500   0.3948   0.01336   0.00545  -0.0593   0.6916   1.0000
   0.750   0.4185   0.01346   0.00544  -0.0584   0.6800   1.0000
   1.000   0.4426   0.01354   0.00542  -0.0576   0.6689   1.0000
   1.250   0.4672   0.01362   0.00537  -0.0567   0.6583   1.0000
   1.500   0.4917   0.01372   0.00539  -0.0560   0.6459   1.0000
   1.750   0.5163   0.01383   0.00543  -0.0552   0.6332   1.0000
   2.000   0.5412   0.01394   0.00546  -0.0545   0.6206   1.0000
   2.250   0.5662   0.01405   0.00549  -0.0538   0.6078   1.0000
   2.500   0.5912   0.01417   0.00553  -0.0531   0.5945   1.0000
   2.750   0.6163   0.01430   0.00558  -0.0524   0.5808   1.0000
   3.000   0.6413   0.01445   0.00568  -0.0517   0.5662   1.0000
   3.250   0.6662   0.01461   0.00579  -0.0511   0.5512   1.0000
   3.500   0.6911   0.01479   0.00591  -0.0504   0.5359   1.0000
   3.750   0.7159   0.01499   0.00605  -0.0497   0.5202   1.0000
   4.000   0.7406   0.01521   0.00622  -0.0491   0.5042   1.0000
   4.250   0.7651   0.01545   0.00642  -0.0484   0.4876   1.0000
   4.500   0.7894   0.01572   0.00664  -0.0478   0.4707   1.0000
   4.750   0.8136   0.01601   0.00688  -0.0471   0.4538   1.0000
   5.000   0.8375   0.01632   0.00717  -0.0464   0.4366   1.0000
   5.250   0.8613   0.01665   0.00747  -0.0457   0.4196   1.0000
   5.500   0.8847   0.01701   0.00779  -0.0450   0.4025   1.0000
   5.750   0.9079   0.01740   0.00816  -0.0443   0.3856   1.0000
   6.000   0.9308   0.01781   0.00854  -0.0435   0.3691   1.0000
   6.250   0.9534   0.01825   0.00894  -0.0428   0.3528   1.0000
   6.500   0.9757   0.01872   0.00940  -0.0420   0.3372   1.0000
   6.750   0.9976   0.01921   0.00988  -0.0412   0.3217   1.0000
   7.000   1.0193   0.01972   0.01039  -0.0404   0.3069   1.0000
   7.250   1.0406   0.02026   0.01095  -0.0395   0.2927   1.0000
   7.500   1.0615   0.02083   0.01153  -0.0387   0.2789   1.0000
   7.750   1.0821   0.02142   0.01214  -0.0378   0.2660   1.0000
   8.000   1.1020   0.02204   0.01280  -0.0368   0.2537   1.0000
   8.250   1.1213   0.02270   0.01347  -0.0358   0.2421   1.0000
   8.500   1.1399   0.02339   0.01418  -0.0347   0.2310   1.0000
   8.750   1.1585   0.02408   0.01494  -0.0337   0.2197   1.0000
   9.000   1.1763   0.02482   0.01575  -0.0325   0.2097   1.0000
   9.250   1.1924   0.02563   0.01655  -0.0312   0.2005   1.0000
   9.500   1.2088   0.02640   0.01744  -0.0300   0.1904   1.0000
   9.750   1.2239   0.02726   0.01836  -0.0286   0.1819   1.0000
  10.000   1.2369   0.02816   0.01931  -0.0271   0.1736   1.0000
  10.250   1.2493   0.02905   0.02033  -0.0254   0.1654   1.0000
  10.500   1.2583   0.03007   0.02135  -0.0234   0.1587   1.0000
  10.750   1.2690   0.03109   0.02253  -0.0218   0.1508   1.0000
  11.000   1.2763   0.03229   0.02374  -0.0201   0.1448   1.0000
  11.250   1.2856   0.03350   0.02512  -0.0186   0.1376   1.0000
  11.500   1.2912   0.03491   0.02657  -0.0171   0.1317   1.0000
  11.750   1.2988   0.03635   0.02818  -0.0159   0.1254   1.0000
  12.000   1.3034   0.03798   0.02988  -0.0147   0.1198   1.0000
  12.250   1.3083   0.03973   0.03175  -0.0137   0.1143   1.0000
  12.500   1.3122   0.04160   0.03376  -0.0128   0.1090   1.0000
  12.750   1.3139   0.04370   0.03588  -0.0121   0.1046   1.0000
  13.000   1.3167   0.04589   0.03831  -0.0115   0.0994   1.0000
  13.250   1.3170   0.04830   0.04081  -0.0112   0.0952   1.0000
  13.500   1.3168   0.05090   0.04351  -0.0110   0.0913   1.0000
  13.750   1.3159   0.05372   0.04652  -0.0110   0.0869   1.0000
  14.000   1.3131   0.05675   0.04964  -0.0112   0.0835   1.0000
  14.250   1.3103   0.05993   0.05289  -0.0116   0.0804   1.0000
  14.500   1.3061   0.06349   0.05668  -0.0122   0.0769   1.0000
  14.750   1.3007   0.06726   0.06059  -0.0132   0.0739   1.0000
  15.000   1.2951   0.07112   0.06450  -0.0143   0.0713   1.0000
  15.250   1.2884   0.07543   0.06897  -0.0157   0.0688   1.0000
  15.500   1.2798   0.08025   0.07401  -0.0175   0.0662   1.0000
  15.750   1.2717   0.08511   0.07904  -0.0195   0.0640   1.0000
  16.000   1.2640   0.08998   0.08399  -0.0216   0.0619   1.0000
  16.250   1.2576   0.09468   0.08873  -0.0236   0.0600   1.0000
  16.500   1.2431   0.10129   0.09560  -0.0268   0.0583   1.0000
  16.750   1.2286   0.10808   0.10260  -0.0303   0.0568   1.0000
  17.000   1.2136   0.11518   0.10987  -0.0341   0.0552   1.0000
  17.250   1.2009   0.12192   0.11673  -0.0378   0.0538   1.0000
  17.500   1.1976   0.12658   0.12141  -0.0403   0.0519   1.0000
  17.750   1.1852   0.13351   0.12844  -0.0443   0.0507   1.0000
  18.000   1.1541   0.14538   0.14052  -0.0515   0.0502   1.0000
<< Back to MH 70 11.08% (mh70-il)

Polar data table (+)

Polar graphs


<< Back to MH 70 11.08% (mh70-il)