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WORTMANN FX 082-512 AIRFOIL (fx082512-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: WORTMANN FX 082-512 AIRFOIL (fx082512-il)
Reynolds number: 200,000
Max Cl/Cd: 63.64 at α=2.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx082512-il-200000.txt
Download as CSV file: xf-fx082512-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: WORTMANN FX 082-512 AIRFOIL                     
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.750  -0.6419   0.08461   0.08075  -0.0589   1.0000   0.0389
 -11.500  -0.6682   0.07814   0.07424  -0.0614   1.0000   0.0386
 -11.250  -0.6933   0.07262   0.06867  -0.0633   1.0000   0.0383
 -11.000  -0.7175   0.06782   0.06383  -0.0646   1.0000   0.0379
 -10.750  -0.7458   0.06332   0.05926  -0.0654   1.0000   0.0378
 -10.500  -0.7741   0.05974   0.05563  -0.0649   1.0000   0.0376
 -10.250  -0.8004   0.05633   0.05217  -0.0644   1.0000   0.0371
 -10.000  -0.8159   0.05099   0.04663  -0.0695   1.0000   0.0372
  -9.750  -0.8162   0.04466   0.03983  -0.0777   1.0000   0.0380
  -9.500  -0.8039   0.03969   0.03432  -0.0832   1.0000   0.0392
  -9.250  -0.7872   0.03720   0.03177  -0.0845   1.0000   0.0406
  -9.000  -0.7662   0.03572   0.03019  -0.0859   1.0000   0.0422
  -8.750  -0.7432   0.03399   0.02826  -0.0875   1.0000   0.0446
  -8.500  -0.7156   0.03188   0.02570  -0.0904   1.0000   0.0482
  -8.250  -0.6932   0.03043   0.02428  -0.0912   1.0000   0.0509
  -8.000  -0.6675   0.02939   0.02311  -0.0923   1.0000   0.0546
  -7.750  -0.6390   0.02787   0.02128  -0.0942   1.0000   0.0596
  -7.500  -0.6143   0.02672   0.02018  -0.0950   1.0000   0.0644
  -7.250  -0.5865   0.02602   0.01926  -0.0962   1.0000   0.0698
  -7.000  -0.5598   0.02431   0.01753  -0.0973   1.0000   0.0754
  -6.750  -0.5330   0.02353   0.01668  -0.0982   1.0000   0.0809
  -6.500  -0.5056   0.02316   0.01610  -0.0989   1.0000   0.0851
  -6.250  -0.4777   0.02168   0.01473  -0.1001   1.0000   0.0908
  -6.000  -0.4499   0.02108   0.01411  -0.1010   1.0000   0.0958
  -5.750  -0.4224   0.02068   0.01362  -0.1016   1.0000   0.0996
  -5.500  -0.3850   0.01996   0.01294  -0.1044   0.9987   0.1042
  -5.250  -0.3440   0.01954   0.01252  -0.1079   0.9965   0.1093
  -5.000  -0.3029   0.01935   0.01224  -0.1112   0.9943   0.1136
  -4.750  -0.2629   0.01893   0.01173  -0.1145   0.9914   0.1202
  -4.500  -0.2226   0.01853   0.01125  -0.1179   0.9891   0.1305
  -4.250  -0.1785   0.01779   0.01111  -0.1226   0.9878   0.2714
  -4.000  -0.1444   0.01836   0.01156  -0.1238   0.9836   0.2995
  -3.750  -0.1113   0.01919   0.01237  -0.1246   0.9791   0.3163
  -3.500  -0.0771   0.01997   0.01303  -0.1257   0.9752   0.3290
  -3.250  -0.0487   0.02064   0.01385  -0.1255   0.9700   0.3362
  -3.000  -0.0108   0.02105   0.01411  -0.1276   0.9673   0.3447
  -2.750   0.0157   0.02140   0.01458  -0.1272   0.9617   0.3492
  -2.500   0.0491   0.02181   0.01499  -0.1283   0.9578   0.3566
  -2.250   0.0872   0.02198   0.01513  -0.1304   0.9555   0.3624
  -2.000   0.1122   0.02218   0.01540  -0.1299   0.9492   0.3664
  -1.750   0.1474   0.02225   0.01545  -0.1315   0.9456   0.3711
  -1.500   0.1874   0.02222   0.01532  -0.1342   0.9433   0.3767
  -1.250   0.2144   0.02228   0.01547  -0.1341   0.9376   0.3799
  -1.000   0.2471   0.02228   0.01552  -0.1352   0.9330   0.3835
  -0.750   0.2937   0.02206   0.01522  -0.1387   0.9296   0.3900
  -0.500   0.3253   0.02184   0.01509  -0.1394   0.9223   0.3945
  -0.250   0.3656   0.02155   0.01490  -0.1414   0.9168   0.3996
   0.000   0.4170   0.02086   0.01419  -0.1457   0.9139   0.4032
   0.250   0.4486   0.02047   0.01376  -0.1464   0.9049   0.4053
   0.500   0.4976   0.01962   0.01292  -0.1501   0.9008   0.4076
   0.750   0.5488   0.01864   0.01204  -0.1540   0.8983   0.4103
   1.000   0.5854   0.01777   0.01125  -0.1548   0.8869   0.4126
   1.250   0.6361   0.01643   0.00999  -0.1581   0.8785   0.4153
   1.500   0.6864   0.01529   0.00889  -0.1615   0.8686   0.4182
   1.750   0.7287   0.01447   0.00809  -0.1634   0.8520   0.4210
   2.000   0.7610   0.01394   0.00759  -0.1636   0.8267   0.4232
   2.250   0.8181   0.01323   0.00684  -0.1685   0.7743   0.4266
   2.500   0.8591   0.01350   0.00647  -0.1701   0.6412   0.4301
   2.750   0.8576   0.01491   0.00683  -0.1637   0.4572   0.4319
   3.000   0.8569   0.01664   0.00755  -0.1584   0.2741   0.4336
   3.250   0.8664   0.01822   0.00829  -0.1554   0.1342   0.4357
   3.500   0.8882   0.01878   0.00878  -0.1542   0.1234   0.4381
   3.750   0.9104   0.01913   0.00924  -0.1530   0.1176   0.4405
   4.000   0.9303   0.01969   0.00985  -0.1514   0.1120   0.4431
   4.250   0.9481   0.02047   0.01063  -0.1495   0.1075   0.4458
   4.500   0.9697   0.02099   0.01124  -0.1483   0.1029   0.4493
   4.750   0.9904   0.02176   0.01198  -0.1470   0.0975   0.4530
   5.000   1.0129   0.02296   0.01317  -0.1462   0.0919   0.4563
   5.250   1.0369   0.02353   0.01386  -0.1454   0.0865   0.4601
   5.500   1.0661   0.02498   0.01524  -0.1460   0.0795   0.4644
   5.750   1.0923   0.02580   0.01618  -0.1455   0.0735   0.4687
   6.000   1.1188   0.02677   0.01717  -0.1455   0.0671   0.4730
   6.250   1.1476   0.02803   0.01859  -0.1456   0.0607   0.4781
   6.500   1.1726   0.02886   0.01948  -0.1450   0.0559   0.4838
   6.750   1.2033   0.03051   0.02123  -0.1457   0.0514   0.4901
   7.000   1.2266   0.03123   0.02216  -0.1446   0.0475   0.4973
   7.250   1.2501   0.03208   0.02313  -0.1439   0.0449   0.5049
   7.500   1.2813   0.03441   0.02559  -0.1447   0.0424   0.5146
   7.750   1.3057   0.03595   0.02755  -0.1436   0.0398   0.5242
   8.000   1.3279   0.03709   0.02890  -0.1426   0.0377   0.5367
   8.250   1.3493   0.03834   0.03033  -0.1417   0.0363   0.5536
   8.500   1.3730   0.04117   0.03341  -0.1415   0.0350   0.5806
   8.750   1.3895   0.04494   0.03786  -0.1394   0.0343   0.6269
   9.000   1.3969   0.04833   0.04215  -0.1355   0.0336   0.7790
   9.250   1.3937   0.05131   0.04566  -0.1297   0.0330   1.0000
   9.500   1.3951   0.05563   0.05041  -0.1258   0.0325   1.0000
   9.750   1.3909   0.06033   0.05549  -0.1216   0.0327   1.0000
  10.000   1.3830   0.06490   0.06039  -0.1173   0.0331   1.0000
  10.250   1.3707   0.06920   0.06496  -0.1128   0.0335   1.0000
  10.500   1.3549   0.07309   0.06906  -0.1082   0.0338   1.0000
  10.750   1.3392   0.07731   0.07345  -0.1044   0.0342   1.0000
  11.000   1.0224   0.10751   0.10481  -0.0951   0.0591   0.5672
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