Airfoil Tools
Search 1638 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

UNIVERSITY OF ALBERTA UA 79-SF-187 AIRFOIL MAIN ELEMENT (ua79sfm-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: UNIVERSITY OF ALBERTA UA 79-SF-187 AIRFOIL MAIN ELEMENT (ua79sfm-il)
Reynolds number: 100,000
Max Cl/Cd: 41.3 at α=11.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-ua79sfm-il-100000.txt
Download as CSV file: xf-ua79sfm-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: UNIVERSITY OF ALBERTA UA 79-SF-187 AIRFOIL MAIN 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.3635   0.10875   0.10499  -0.0448  -0.0009   4.3309
 -10.250  -0.3373   0.10620   0.10241  -0.0413  -0.0009   4.3212
 -10.000  -0.3558   0.10275   0.09904  -0.0433  -0.0009   4.3092
  -9.750  -0.3457   0.09964   0.09594  -0.0419  -0.0009   4.3009
  -9.500  -0.3506   0.09682   0.09316  -0.0421  -0.0009   4.2864
  -9.250  -0.3582   0.09337   0.08976  -0.0426  -0.0009   4.2764
  -9.000  -0.3534   0.09095   0.08736  -0.0416  -0.0009   4.2611
  -8.750  -0.3733   0.08744   0.08393  -0.0433  -0.0009   4.2476
  -8.500  -0.3615   0.08518   0.08168  -0.0415  -0.0009   4.2306
  -8.250  -0.3848   0.08179   0.07836  -0.0433  -0.0009   4.2136
  -8.000  -0.3745   0.07958   0.07617  -0.0415  -0.0009   4.1943
  -7.750  -0.3910   0.07640   0.07306  -0.0423  -0.0009   4.1739
  -7.500  -0.4027   0.07399   0.07069  -0.0424  -0.0009   4.1505
  -7.250  -0.4003   0.07124   0.06797  -0.0413  -0.0009   4.1280
  -7.000  -0.4432   0.06856   0.06537  -0.0429  -0.0009   4.1080
  -5.500  -0.4956   0.03617   0.03064  -0.0428  -0.0009   4.4366
  -5.250  -0.4852   0.03358   0.02774  -0.0409  -0.0009   4.4426
  -5.000  -0.4742   0.03135   0.02510  -0.0388  -0.0009   4.4466
  -4.750  -0.4624   0.02955   0.02314  -0.0371  -0.0009   4.4483
  -4.500  -0.4495   0.02795   0.02114  -0.0350  -0.0009   4.4501
  -4.250  -0.4366   0.02660   0.01969  -0.0334  -0.0009   4.4507
  -4.000  -0.4231   0.02541   0.01834  -0.0317  -0.0009   4.4513
  -3.750  -0.4093   0.02440   0.01720  -0.0300  -0.0009   4.4516
  -3.500  -0.3956   0.02352   0.01625  -0.0284  -0.0009   4.4516
  -3.250  -0.3821   0.02277   0.01546  -0.0269  -0.0009   4.4513
  -3.000  -0.3693   0.02212   0.01480  -0.0253  -0.0009   4.4508
  -2.750  -0.3572   0.02157   0.01421  -0.0237  -0.0009   4.4499
  -2.500  -0.3462   0.02102   0.01370  -0.0222  -0.0009   4.4484
  -2.250  -0.1692   0.03310   0.02837  -0.0241  -0.0009   2.0490
  -2.000  -0.1415   0.03496   0.02998  -0.0240  -0.0009   2.0009
  -1.750  -0.1392   0.03436   0.02927  -0.0228  -0.0009   2.0009
  -1.500  -0.1364   0.03382   0.02862  -0.0216  -0.0009   2.0009
  -1.250  -0.1332   0.03333   0.02802  -0.0204  -0.0009   2.0009
  -1.000  -0.1182   0.03251   0.02707  -0.0205  -0.0005   2.0009
  -0.750  -0.0991   0.03265   0.02705  -0.0211  -0.0001   2.0009
  -0.500  -0.0898   0.03197   0.02627  -0.0205   0.0001   2.0009
  -0.250  -0.0739   0.03183   0.02599  -0.0205   0.0000   2.0009
   0.000  -0.0544   0.03337   0.02739  -0.0211  -0.0002   2.0009
   0.250  -0.0505   0.03158   0.02556  -0.0196  -0.0011   2.0009
   0.500  -0.0316   0.03245   0.02630  -0.0199  -0.0015   2.0009
   0.750  -0.0279   0.03157   0.02538  -0.0184  -0.0015   2.0009
   1.000  -0.0098   0.03222   0.02592  -0.0185  -0.0010   2.0009
   1.250  -0.0062   0.03170   0.02536  -0.0170  -0.0004   2.0009
   1.500   0.0112   0.03225   0.02583  -0.0170   0.0000   2.0009
   1.750   0.0152   0.03192   0.02548  -0.0156  -0.0001   2.0009
   2.000   0.0335   0.03259   0.02607  -0.0156  -0.0004   2.0009
   2.250   0.0367   0.03215   0.02561  -0.0141  -0.0001   2.0009
   2.500   0.0576   0.03328   0.02667  -0.0143   0.0010   2.0009
   2.750   0.0622   0.03270   0.02608  -0.0129   0.0053   2.0009
   3.000   0.0686   0.03271   0.02606  -0.0117   0.0105   2.0009
   3.250   0.0906   0.03371   0.02701  -0.0120   0.0164   2.0009
   3.500   0.1001   0.03352   0.02681  -0.0110   0.0262   2.0009
   3.750   0.1119   0.03353   0.02679  -0.0101   0.0374   2.0009
   4.000   0.1548   0.03287   0.02603  -0.0109   0.0885   2.0009
   4.250   0.1772   0.03288   0.02601  -0.0106   0.1169   2.0009
   4.500   0.1926   0.03280   0.02591  -0.0098   0.1452   2.0009
   4.750   0.2049   0.03278   0.02589  -0.0088   0.1721   2.0009
   5.000   0.2190   0.03285   0.02596  -0.0079   0.1968   2.0009
   5.250   0.2453   0.03310   0.02620  -0.0078   0.2135   2.0009
   5.500   0.2521   0.03306   0.02619  -0.0064   0.2428   2.0009
   5.750   0.2608   0.03309   0.02625  -0.0052   0.2731   2.0009
   6.000   0.2725   0.03323   0.02640  -0.0042   0.3020   2.0009
   6.250   0.2957   0.03338   0.02658  -0.0038   0.3231   2.0009
   6.500   0.2999   0.03348   0.02671  -0.0023   0.3605   2.0009
   6.750   0.3091   0.03367   0.02697  -0.0011   0.3935   2.0009
   7.000   0.3315   0.03377   0.02710  -0.0006   0.4165   2.0009
   7.250   0.3339   0.03397   0.02736   0.0009   0.4568   2.0009
   7.500   0.3642   0.03400   0.02744   0.0011   0.4725   2.0009
   7.750   0.3634   0.03423   0.02772   0.0028   0.5172   2.0009
   8.000   0.3675   0.03449   0.02805   0.0042   0.5571   2.0009
   8.250   0.3945   0.03434   0.02797   0.0047   0.5772   2.0009
   8.500   0.3939   0.03469   0.02839   0.0063   0.6234   2.0009
   8.750   0.4270   0.03434   0.02811   0.0067   0.6375   2.0009
   9.000   0.4234   0.03475   0.02860   0.0084   0.6883   2.0009
   9.250   0.4219   0.03523   0.02916   0.0099   0.7372   2.0009
   9.500   0.4542   0.03468   0.02871   0.0105   0.7535   2.0009
   9.750   0.4486   0.03530   0.02941   0.0121   0.8079   2.0009
  10.000   0.4467   0.03590   0.03010   0.0135   0.8592   2.0009
  10.250   0.4766   0.03526   0.02958   0.0144   0.8790   2.0009
  10.750   0.4693   0.03671   0.03120   0.0171   0.9883   2.0009
  11.000   0.4983   0.03588   0.03052   0.0183   1.0123   2.0009
  11.250   0.4929   0.03670   0.03143   0.0195   1.0720   2.0009
  11.500   0.4946   0.03719   0.03203   0.0208   1.1264   2.0009
  11.750   0.6889   0.01668   0.01151   0.0285   1.4225   2.0009
  12.000   0.6851   0.01674   0.01144   0.0309   1.6202   2.0009
  12.250   0.6775   0.01725   0.01188   0.0330   1.8100   2.0009
  12.500   0.6691   0.01787   0.01238   0.0350   2.0286   2.0009
  12.750   0.6568   0.01878   0.01311   0.0368   2.3119   2.0009
  13.000   0.6420   0.01994   0.01407   0.0383   2.6191   2.0009
  13.250   0.6272   0.02127   0.01520   0.0396   2.9607   2.0009
  13.500   0.6091   0.02293   0.01658   0.0406   3.3995   2.0009
  13.750   0.5928   0.02460   0.01804   0.0413   3.7171   2.0009
  14.000   0.5834   0.02594   0.01937   0.0421   3.8111   2.0009
  14.250   0.5773   0.02706   0.02059   0.0427   3.8448   2.0009
  14.500   0.5709   0.02828   0.02191   0.0433   3.8700   2.0009
  14.750   0.5642   0.02954   0.02328   0.0436   3.8866   2.0009
  15.000   0.5581   0.03081   0.02466   0.0439   3.8957   2.0009
  15.250   0.5520   0.03212   0.02611   0.0442   3.9055   2.0009
  15.500   0.5460   0.03347   0.02759   0.0443   3.9119   2.0009
  15.750   0.5399   0.03486   0.02909   0.0443   3.9188   2.0009
  16.000   0.5341   0.03624   0.03056   0.0444   3.9242   2.0009
  16.250   0.5300   0.03743   0.03184   0.0445   3.9289   2.0009
  16.500   0.5285   0.03833   0.03285   0.0448   3.9326   2.0009
  16.750   0.5300   0.03894   0.03354   0.0454   3.9368   2.0009
  17.000   0.5373   0.03889   0.03355   0.0466   3.9422   2.0009
  17.250   0.5616   0.03720   0.03188   0.0494   3.9484   2.0009
  17.500   0.5995   0.03545   0.03014   0.0530   3.9492   2.0009
  17.750   0.6248   0.03550   0.03034   0.0552   3.9447   2.0009
  18.000   0.6351   0.03656   0.03158   0.0562   3.9394   2.0009
  18.250   0.6372   0.03801   0.03322   0.0568   3.9346   2.0009
  18.500   0.6385   0.03958   0.03494   0.0572   3.9296   2.0009
  18.750   0.6314   0.04138   0.03693   0.0570   3.9254   2.0009
  19.000   0.6050   0.04389   0.03972   0.0553   3.9211   2.0009
  19.250   0.5808   0.04694   0.04302   0.0533   3.9161   2.0009
<< Back to UNIVERSITY OF ALBERTA UA 79-SF-187 AIRFOIL MAIN ELEMENT (ua79sfm-il)

Polar data table (+)

Polar graphs


<< Back to UNIVERSITY OF ALBERTA UA 79-SF-187 AIRFOIL MAIN ELEMENT (ua79sfm-il)