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FX 72-LS-160 (fx72ls160-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: FX 72-LS-160 (fx72ls160-il)
Reynolds number: 500,000
Max Cl/Cd: 121.16 at α=9°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx72ls160-il-500000.txt
Download as CSV file: xf-fx72ls160-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 72-LS-160                                    
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.000   0.1888   0.10276   0.09843  -0.1368   0.6810   0.0165
 -10.750   0.1964   0.10013   0.09582  -0.1381   0.6802   0.0169
 -10.500   0.1986   0.09718   0.09290  -0.1401   0.6793   0.0172
 -10.250   0.2024   0.09416   0.08991  -0.1415   0.6783   0.0174
 -10.000   0.2150   0.09194   0.08770  -0.1419   0.6772   0.0175
  -9.750   0.2243   0.08969   0.08547  -0.1428   0.6760   0.0177
  -9.500   0.2337   0.08759   0.08338  -0.1436   0.6747   0.0180
  -9.250   0.2416   0.08530   0.08110  -0.1445   0.6734   0.0185
  -9.000   0.2491   0.08298   0.07879  -0.1454   0.6721   0.0190
  -8.750   0.2544   0.08037   0.07619  -0.1467   0.6710   0.0198
  -8.500   0.2478   0.07663   0.07250  -0.1496   0.6699   0.0203
  -8.250   0.2547   0.07408   0.06996  -0.1503   0.6687   0.0204
  -8.000   0.2681   0.07245   0.06832  -0.1502   0.6676   0.0206
  -7.750   0.2760   0.07039   0.06626  -0.1509   0.6664   0.0208
  -7.500   0.2845   0.06854   0.06441  -0.1514   0.6648   0.0215
  -7.250   0.2895   0.06632   0.06222  -0.1522   0.6635   0.0221
  -6.750   0.2691   0.05889   0.05496  -0.1570   0.6613   0.0236
  -6.500   0.2791   0.05729   0.05338  -0.1572   0.6601   0.0238
  -6.250   0.2888   0.05531   0.05142  -0.1585   0.6588   0.0241
  -6.000   0.2992   0.05315   0.04927  -0.1603   0.6574   0.0249
  -5.750   0.3094   0.04989   0.04599  -0.1638   0.6560   0.0258
  -5.500   0.3179   0.04292   0.03888  -0.1709   0.6545   0.0274
  -5.250   0.3351   0.04144   0.03736  -0.1716   0.6531   0.0279
  -5.000   0.3346   0.02431   0.01900  -0.1774   0.6521   0.0207
  -4.750   0.3570   0.01913   0.01286  -0.1781   0.6510   0.0178
  -4.500   0.3846   0.01836   0.01196  -0.1785   0.6498   0.0182
  -4.250   0.4128   0.01774   0.01117  -0.1789   0.6487   0.0191
  -4.000   0.4409   0.01697   0.01017  -0.1792   0.6472   0.0195
  -3.750   0.4684   0.01624   0.00927  -0.1793   0.6459   0.0195
  -3.500   0.4962   0.01561   0.00855  -0.1795   0.6448   0.0198
  -3.250   0.5240   0.01515   0.00803  -0.1796   0.6434   0.0202
  -3.000   0.5518   0.01466   0.00755  -0.1799   0.6420   0.0210
  -2.750   0.5801   0.01439   0.00728  -0.1802   0.6406   0.0220
  -2.500   0.6087   0.01416   0.00703  -0.1805   0.6392   0.0232
  -2.250   0.6374   0.01394   0.00680  -0.1809   0.6379   0.0248
  -2.000   0.6665   0.01378   0.00662  -0.1813   0.6366   0.0276
  -1.750   0.6959   0.01359   0.00643  -0.1818   0.6353   0.0318
  -1.500   0.7258   0.01337   0.00629  -0.1824   0.6340   0.0560
  -1.250   0.7554   0.01329   0.00624  -0.1830   0.6327   0.0750
  -1.000   0.7851   0.01329   0.00623  -0.1836   0.6315   0.0899
  -0.750   0.8143   0.01339   0.00635  -0.1842   0.6299   0.1081
  -0.500   0.8424   0.01333   0.00642  -0.1846   0.6287   0.1429
  -0.250   0.8709   0.01312   0.00649  -0.1852   0.6275   0.2335
   0.000   0.9006   0.01272   0.00665  -0.1864   0.6260   0.4359
   0.250   0.9267   0.01204   0.00697  -0.1865   0.6246   0.7849
   0.500   0.9396   0.01203   0.00715  -0.1830   0.6230   0.8942
   0.750   0.9550   0.01205   0.00718  -0.1802   0.6214   0.9327
   1.000   0.9690   0.01198   0.00711  -0.1771   0.6198   0.9600
   1.250   0.9985   0.01191   0.00699  -0.1775   0.6184   0.9969
   1.500   1.0292   0.01199   0.00700  -0.1783   0.6172   1.0000
   1.750   1.0598   0.01209   0.00703  -0.1792   0.6160   1.0000
   2.000   1.0906   0.01223   0.00710  -0.1802   0.6148   1.0000
   2.250   1.1208   0.01253   0.00733  -0.1810   0.6132   1.0000
   2.500   1.1481   0.01268   0.00749  -0.1814   0.6119   1.0000
   2.750   1.1749   0.01283   0.00766  -0.1816   0.6103   1.0000
   3.000   1.2020   0.01297   0.00782  -0.1819   0.6084   1.0000
   3.250   1.2296   0.01311   0.00795  -0.1823   0.6066   1.0000
   3.500   1.2577   0.01323   0.00808  -0.1827   0.6050   1.0000
   3.750   1.2863   0.01335   0.00818  -0.1833   0.6035   1.0000
   4.000   1.3155   0.01345   0.00827  -0.1839   0.6021   1.0000
   4.250   1.3451   0.01355   0.00834  -0.1847   0.6009   1.0000
   4.500   1.3752   0.01365   0.00842  -0.1855   0.5996   1.0000
   4.750   1.4057   0.01379   0.00853  -0.1864   0.5982   1.0000
   5.000   1.4328   0.01406   0.00881  -0.1868   0.5965   1.0000
   5.250   1.4559   0.01428   0.00912  -0.1864   0.5947   1.0000
   5.500   1.4798   0.01451   0.00940  -0.1862   0.5927   1.0000
   5.750   1.5047   0.01469   0.00962  -0.1862   0.5907   1.0000
   6.000   1.5309   0.01481   0.00977  -0.1863   0.5888   1.0000
   6.250   1.5587   0.01488   0.00986  -0.1868   0.5871   1.0000
   6.500   1.5882   0.01486   0.00983  -0.1875   0.5853   1.0000
   6.750   1.6194   0.01482   0.00976  -0.1885   0.5834   1.0000
   7.000   1.6481   0.01498   0.00993  -0.1891   0.5813   1.0000
   7.250   1.6652   0.01523   0.01030  -0.1877   0.5786   1.0000
   7.500   1.6856   0.01537   0.01052  -0.1868   0.5756   1.0000
   7.750   1.7101   0.01538   0.01056  -0.1866   0.5728   1.0000
   8.000   1.7389   0.01517   0.01034  -0.1871   0.5697   1.0000
   8.250   1.7691   0.01503   0.01017  -0.1878   0.5661   1.0000
   8.500   1.7768   0.01525   0.01052  -0.1846   0.5615   1.0000
   8.750   1.7926   0.01520   0.01050  -0.1827   0.5565   1.0000
   9.000   1.8174   0.01500   0.01025  -0.1824   0.5513   1.0000
   9.250   1.8123   0.01547   0.01085  -0.1770   0.5459   1.0000
   9.500   1.8215   0.01577   0.01120  -0.1743   0.5408   1.0000
   9.750   1.8426   0.01589   0.01129  -0.1736   0.5362   1.0000
  10.000   1.8381   0.01677   0.01231  -0.1691   0.5303   1.0000
  10.250   1.8461   0.01734   0.01290  -0.1666   0.5238   1.0000
  10.500   1.8480   0.01832   0.01395  -0.1635   0.5171   1.0000
  10.750   1.8497   0.01940   0.01505  -0.1605   0.5090   1.0000
  11.000   1.8477   0.02086   0.01659  -0.1574   0.5007   1.0000
  11.250   1.8501   0.02218   0.01789  -0.1549   0.4919   1.0000
  11.500   1.8442   0.02421   0.02002  -0.1519   0.4828   1.0000
  11.750   1.8425   0.02604   0.02186  -0.1493   0.4733   1.0000
  12.000   1.8369   0.02823   0.02406  -0.1465   0.4620   1.0000
  12.250   1.8280   0.03081   0.02668  -0.1437   0.4492   1.0000
  12.500   1.8184   0.03356   0.02943  -0.1409   0.4345   1.0000
  12.750   1.8052   0.03669   0.03251  -0.1380   0.4169   1.0000
  13.000   1.7908   0.04008   0.03585  -0.1352   0.3974   1.0000
  13.250   1.7737   0.04387   0.03955  -0.1323   0.3755   1.0000
  13.500   1.7550   0.04795   0.04352  -0.1296   0.3545   1.0000
  13.750   1.7408   0.05180   0.04729  -0.1274   0.3341   1.0000
  14.000   1.7285   0.05559   0.05100  -0.1255   0.3138   1.0000
  14.250   1.7163   0.05950   0.05484  -0.1238   0.2946   1.0000
  14.500   1.7039   0.06359   0.05884  -0.1223   0.2756   1.0000
  14.750   1.6957   0.06729   0.06248  -0.1210   0.2563   1.0000
  15.000   1.6870   0.07118   0.06630  -0.1200   0.2382   1.0000
  15.250   1.6793   0.07502   0.07007  -0.1190   0.2200   1.0000
  15.500   1.6717   0.07893   0.07391  -0.1182   0.2026   1.0000
  16.000   1.6588   0.08671   0.08155  -0.1171   0.1684   1.0000
  16.250   1.6536   0.09054   0.08532  -0.1168   0.1521   1.0000
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