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

WORTMANN FX 72-MS-150A AIRFOIL (fx72150a-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: WORTMANN FX 72-MS-150A AIRFOIL (fx72150a-il)
Reynolds number: 500,000
Max Cl/Cd: 123.11 at α=8°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx72150a-il-500000.txt
Download as CSV file: xf-fx72150a-il-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750   0.2072   0.09097   0.08706  -0.1409   0.7171   0.0188
  -9.500   0.2092   0.08844   0.08449  -0.1428   0.7124   0.0191
  -9.250   0.2100   0.08566   0.08174  -0.1450   0.7075   0.0192
  -9.000   0.2189   0.08307   0.07914  -0.1455   0.7026   0.0193
  -8.750   0.2325   0.08100   0.07701  -0.1453   0.6976   0.0195
  -8.500   0.2428   0.07894   0.07496  -0.1458   0.6930   0.0197
  -8.250   0.2521   0.07695   0.07296  -0.1463   0.6884   0.0201
  -8.000   0.2598   0.07483   0.07082  -0.1471   0.6838   0.0206
  -7.750   0.2673   0.07271   0.06866  -0.1479   0.6795   0.0207
  -7.500   0.2737   0.07036   0.06634  -0.1488   0.6755   0.0216
  -7.250   0.2714   0.06717   0.06318  -0.1513   0.6714   0.0224
  -7.000   0.2700   0.06394   0.05996  -0.1526   0.6674   0.0226
  -6.750   0.2786   0.06219   0.05817  -0.1523   0.6635   0.0227
  -6.500   0.2868   0.06060   0.05660  -0.1519   0.6598   0.0230
  -6.250   0.2934   0.05889   0.05491  -0.1521   0.6559   0.0232
  -6.000   0.3025   0.05682   0.05285  -0.1534   0.6521   0.0236
  -5.750   0.3124   0.05441   0.05041  -0.1557   0.6486   0.0241
  -5.500   0.3245   0.05145   0.04742  -0.1594   0.6452   0.0250
  -5.250   0.3530   0.03991   0.03574  -0.1823   0.6422   0.0263
  -5.000   0.3720   0.03838   0.03421  -0.1835   0.6388   0.0266
  -4.750   0.3955   0.03607   0.03183  -0.1869   0.6355   0.0271
  -4.500   0.4238   0.03309   0.02867  -0.1918   0.6325   0.0279
  -4.250   0.4670   0.02737   0.02230  -0.2011   0.6295   0.0305
  -4.000   0.4941   0.02585   0.02076  -0.2028   0.6268   0.0310
  -3.750   0.5240   0.02431   0.01910  -0.2049   0.6240   0.0321
  -3.500   0.5606   0.02188   0.01623  -0.2083   0.6212   0.0353
  -3.250   0.5901   0.02074   0.01501  -0.2096   0.6185   0.0365
  -3.000   0.6234   0.01939   0.01332  -0.2115   0.6159   0.0407
  -2.750   0.6537   0.01862   0.01241  -0.2126   0.6132   0.0431
  -2.500   0.6946   0.01468   0.00764  -0.2139   0.6112   0.0219
  -2.250   0.7246   0.01391   0.00679  -0.2145   0.6088   0.0217
  -2.000   0.7544   0.01338   0.00617  -0.2151   0.6062   0.0219
  -1.750   0.7840   0.01304   0.00574  -0.2155   0.6037   0.0224
  -1.500   0.8141   0.01261   0.00531  -0.2163   0.6012   0.0231
  -1.250   0.8440   0.01242   0.00509  -0.2170   0.5988   0.0245
  -1.000   0.8741   0.01236   0.00494  -0.2176   0.5962   0.0264
  -0.750   0.9044   0.01212   0.00472  -0.2184   0.5942   0.0279
  -0.500   0.9343   0.01195   0.00454  -0.2191   0.5922   0.0307
  -0.250   0.9663   0.01154   0.00435  -0.2203   0.5900   0.1135
   0.000   0.9988   0.01091   0.00452  -0.2222   0.5879   0.4644
   0.250   1.0270   0.01101   0.00464  -0.2225   0.5859   0.5068
   0.500   1.0551   0.01115   0.00478  -0.2226   0.5841   0.5359
   0.750   1.0830   0.01134   0.00495  -0.2227   0.5823   0.5620
   1.000   1.1111   0.01156   0.00514  -0.2229   0.5805   0.5804
   1.250   1.1393   0.01175   0.00532  -0.2231   0.5787   0.5909
   1.500   1.1669   0.01184   0.00542  -0.2233   0.5773   0.5982
   1.750   1.1943   0.01195   0.00556  -0.2234   0.5757   0.6058
   2.000   1.2221   0.01206   0.00566  -0.2236   0.5740   0.6117
   2.250   1.2498   0.01215   0.00575  -0.2239   0.5723   0.6155
   2.500   1.2775   0.01225   0.00587  -0.2241   0.5705   0.6200
   2.750   1.3054   0.01237   0.00598  -0.2244   0.5690   0.6251
   3.000   1.3334   0.01251   0.00609  -0.2247   0.5675   0.6300
   3.250   1.3614   0.01263   0.00623  -0.2250   0.5662   0.6345
   3.500   1.3896   0.01281   0.00641  -0.2254   0.5647   0.6397
   3.750   1.4185   0.01308   0.00665  -0.2260   0.5631   0.6458
   4.000   1.4452   0.01321   0.00685  -0.2261   0.5620   0.6518
   4.250   1.4716   0.01334   0.00706  -0.2261   0.5607   0.6588
   4.500   1.4980   0.01348   0.00726  -0.2262   0.5591   0.6662
   4.750   1.5245   0.01362   0.00746  -0.2263   0.5575   0.6737
   5.000   1.5512   0.01377   0.00766  -0.2264   0.5559   0.6826
   5.250   1.5779   0.01391   0.00789  -0.2266   0.5544   0.6920
   5.500   1.6049   0.01405   0.00807  -0.2268   0.5528   0.7030
   5.750   1.6318   0.01414   0.00819  -0.2269   0.5504   0.7169
   6.000   1.6600   0.01436   0.00842  -0.2273   0.5466   0.7342
   6.250   1.6813   0.01436   0.00860  -0.2264   0.5438   0.7588
   6.500   1.7023   0.01426   0.00874  -0.2254   0.5401   0.8260
   6.750   1.7237   0.01417   0.00877  -0.2244   0.5365   1.0000
   7.000   1.7491   0.01431   0.00890  -0.2243   0.5335   1.0000
   7.250   1.7758   0.01456   0.00912  -0.2245   0.5296   1.0000
   7.500   1.7940   0.01466   0.00934  -0.2230   0.5259   1.0000
   7.750   1.8146   0.01480   0.00954  -0.2220   0.5221   1.0000
   8.000   1.8355   0.01491   0.00969  -0.2210   0.5180   1.0000
   8.250   1.8540   0.01508   0.00985  -0.2196   0.5122   1.0000
   8.500   1.8632   0.01523   0.01011  -0.2164   0.5056   1.0000
   8.750   1.8733   0.01545   0.01029  -0.2134   0.4985   1.0000
   9.000   1.8769   0.01581   0.01077  -0.2095   0.4904   1.0000
   9.250   1.8803   0.01637   0.01132  -0.2057   0.4801   1.0000
   9.500   1.8819   0.01716   0.01212  -0.2019   0.4677   1.0000
   9.750   1.8811   0.01821   0.01320  -0.1981   0.4492   1.0000
  10.000   1.8676   0.02013   0.01502  -0.1929   0.4184   1.0000
  10.250   1.8486   0.02281   0.01755  -0.1876   0.3876   1.0000
  10.500   1.8201   0.02653   0.02110  -0.1819   0.3526   1.0000
  10.750   1.7929   0.03060   0.02503  -0.1769   0.3240   1.0000
  11.000   1.7650   0.03516   0.02947  -0.1725   0.2937   1.0000
  11.250   1.7356   0.04032   0.03450  -0.1686   0.2640   1.0000
  11.500   1.7077   0.04573   0.03978  -0.1653   0.2329   1.0000
  11.750   1.6836   0.05104   0.04497  -0.1627   0.2050   1.0000
  12.000   1.6581   0.05679   0.05057  -0.1603   0.1731   1.0000
  12.250   1.6352   0.06245   0.05606  -0.1584   0.1405   1.0000
  12.500   1.6138   0.06816   0.06159  -0.1568   0.1066   1.0000
  12.750   1.5947   0.07376   0.06700  -0.1556   0.0732   1.0000
  13.000   1.5730   0.07987   0.07288  -0.1544   0.0362   1.0000
  13.250   1.5667   0.08410   0.07704  -0.1538   0.0214   1.0000
  13.500   1.5684   0.08730   0.08027  -0.1534   0.0182   1.0000
  13.750   1.5723   0.09019   0.08320  -0.1530   0.0168   1.0000
<< Back to WORTMANN FX 72-MS-150A AIRFOIL (fx72150a-il)

Polar data table (+)

Polar graphs


<< Back to WORTMANN FX 72-MS-150A AIRFOIL (fx72150a-il)