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WORTMANN FX 72-MS-150A AIRFOIL (fx72150a-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: WORTMANN FX 72-MS-150A AIRFOIL (fx72150a-il)
Reynolds number: 100,000
Max Cl/Cd: 40.49 at α=1.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx72150a-il-100000-n5.txt
Download as CSV file: xf-fx72150a-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: WORTMANN FX 72-MS-150A AIRFOIL                  
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -11.000   0.1425   0.11242   0.10634  -0.1300   0.7980   0.0437
 -10.750   0.1423   0.11107   0.10499  -0.1320   0.7918   0.0450
 -10.500   0.1457   0.10914   0.10308  -0.1334   0.7856   0.0453
 -10.250   0.1638   0.10539   0.09926  -0.1331   0.7808   0.0463
 -10.000   0.1736   0.10307   0.09692  -0.1336   0.7751   0.0482
  -9.750   0.1804   0.10093   0.09479  -0.1345   0.7689   0.0495
  -9.500   0.1841   0.09912   0.09295  -0.1359   0.7640   0.0511
  -9.250   0.1824   0.09778   0.09164  -0.1378   0.7583   0.0517
  -8.750   0.2042   0.09210   0.08592  -0.1382   0.7484   0.0530
  -8.500   0.2144   0.08982   0.08361  -0.1384   0.7436   0.0542
  -8.250   0.2218   0.08774   0.08154  -0.1389   0.7383   0.0555
  -8.000   0.2279   0.08568   0.07946  -0.1397   0.7339   0.0572
  -7.750   0.2297   0.08389   0.07764  -0.1414   0.7302   0.0589
  -7.500   0.2221   0.08262   0.07647  -0.1433   0.7242   0.0596
  -7.250   0.2297   0.07998   0.07384  -0.1434   0.7198   0.0601
  -7.000   0.2466   0.07725   0.07105  -0.1426   0.7164   0.0612
  -6.750   0.2569   0.07511   0.06886  -0.1427   0.7134   0.0626
  -6.500   0.2599   0.07344   0.06726  -0.1424   0.7082   0.0641
  -6.250   0.2606   0.07187   0.06573  -0.1423   0.7036   0.0656
  -6.000   0.2571   0.07001   0.06388  -0.1474   0.6995   0.0684
  -5.750   0.2663   0.06669   0.06053  -0.1532   0.6966   0.0692
  -5.500   0.2742   0.06481   0.05871  -0.1504   0.6921   0.0699
  -5.250   0.2844   0.06278   0.05669  -0.1503   0.6880   0.0707
  -5.000   0.2976   0.06039   0.05428  -0.1521   0.6845   0.0717
  -4.500   0.3526   0.04550   0.03884  -0.1753   0.6785   0.0339
  -4.250   0.3758   0.04249   0.03568  -0.1795   0.6740   0.0327
  -4.000   0.4199   0.03662   0.02902  -0.1893   0.6706   0.0300
  -3.750   0.4547   0.03404   0.02604  -0.1933   0.6678   0.0304
  -3.500   0.4867   0.03252   0.02429  -0.1958   0.6654   0.0317
  -3.250   0.5243   0.03051   0.02178  -0.1990   0.6634   0.0328
  -3.000   0.5537   0.02912   0.02005  -0.2005   0.6600   0.0328
  -2.750   0.5823   0.02801   0.01863  -0.2014   0.6565   0.0328
  -2.500   0.6116   0.02705   0.01738  -0.2022   0.6535   0.0331
  -2.250   0.6415   0.02619   0.01628  -0.2028   0.6510   0.0336
  -2.000   0.6718   0.02545   0.01533  -0.2034   0.6489   0.0344
  -1.750   0.7022   0.02483   0.01465  -0.2041   0.6471   0.0356
  -1.500   0.7304   0.02449   0.01427  -0.2045   0.6449   0.0375
  -1.250   0.7515   0.02461   0.01443  -0.2039   0.6411   0.0408
  -1.000   0.7768   0.02460   0.01438  -0.2040   0.6379   0.0458
  -0.750   0.8055   0.02444   0.01415  -0.2045   0.6352   0.0524
  -0.500   0.8370   0.02418   0.01390  -0.2058   0.6331   0.0741
  -0.250   0.8748   0.02322   0.01415  -0.2089   0.6315   0.4772
   0.000   0.9002   0.02363   0.01461  -0.2079   0.6299   0.5782
   0.250   0.9163   0.02432   0.01539  -0.2056   0.6273   0.6298
   0.500   0.9309   0.02507   0.01616  -0.2037   0.6235   0.6487
   0.750   0.9519   0.02552   0.01654  -0.2030   0.6206   0.6579
   1.000   0.9776   0.02583   0.01673  -0.2030   0.6182   0.6663
   1.250   1.0044   0.02603   0.01683  -0.2031   0.6163   0.6735
   1.500   1.0338   0.02619   0.01685  -0.2036   0.6146   0.6822
   1.750   1.0638   0.02627   0.01681  -0.2041   0.6132   0.6891
   2.000   1.0748   0.02733   0.01792  -0.2023   0.6096   0.6954
   2.250   1.0811   0.02865   0.01930  -0.1998   0.6056   0.7012
   2.500   1.0969   0.02948   0.02013  -0.1986   0.6028   0.7079
   2.750   1.1188   0.03005   0.02066  -0.1982   0.6008   0.7162
   3.000   1.1434   0.03042   0.02100  -0.1980   0.5991   0.7244
   3.250   1.1715   0.03065   0.02119  -0.1984   0.5978   0.7336
   3.500   1.2015   0.03075   0.02127  -0.1990   0.5966   0.7435
   4.500   1.1883   0.03814   0.02913  -0.1851   0.5803   0.8085
   4.750   1.2120   0.03807   0.02917  -0.1844   0.5794   1.0000
   6.750   1.1119   0.07021   0.06170  -0.1665   0.5203   1.0000
   7.000   1.1320   0.07114   0.06263  -0.1662   0.5179   1.0000
   7.250   1.1555   0.07171   0.06322  -0.1660   0.5162   1.0000
   7.500   1.1826   0.07183   0.06334  -0.1660   0.5150   1.0000
   7.750   1.2105   0.07178   0.06330  -0.1658   0.5138   1.0000
   8.250   1.2115   0.07737   0.06901  -0.1636   0.4996   1.0000
   8.500   1.2386   0.07737   0.06906  -0.1635   0.4985   1.0000
   9.000   1.2384   0.08341   0.07524  -0.1616   0.4844   1.0000
   9.250   1.2649   0.08338   0.07526  -0.1613   0.4831   1.0000
   9.750   1.2690   0.08886   0.08092  -0.1597   0.4687   1.0000
  10.000   1.2895   0.08938   0.08151  -0.1593   0.4659   1.0000
  10.500   1.3050   0.09335   0.08566  -0.1580   0.4527   1.0000
  11.000   1.3179   0.09777   0.09029  -0.1568   0.4389   1.0000
  11.250   1.3439   0.09743   0.09004  -0.1564   0.4372   1.0000
  11.750   1.3588   0.10153   0.09437  -0.1554   0.4235   1.0000
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