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S7055 (10.5%) Flat-Bottomed (s7055-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: S7055 (10.5%) Flat-Bottomed (s7055-il)
Reynolds number: 50,000
Max Cl/Cd: 31.13 at α=9.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s7055-il-50000.txt
Download as CSV file: xf-s7055-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S7055 (10.5%) Flat-Bottomed                     
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.3511   0.11441   0.10781  -0.0317   1.0000   0.1923
  -9.000  -0.3264   0.10849   0.10187  -0.0299   1.0000   0.2026
  -8.750  -0.3510   0.10891   0.10249  -0.0318   1.0000   0.2070
  -8.500  -0.3270   0.10345   0.09701  -0.0298   1.0000   0.2188
  -8.250  -0.3237   0.10025   0.09389  -0.0291   1.0000   0.2268
  -8.000  -0.3395   0.09954   0.09335  -0.0288   1.0000   0.2351
  -7.750  -0.3294   0.09588   0.08974  -0.0270   1.0000   0.2470
  -7.500  -0.3304   0.09339   0.08736  -0.0250   1.0000   0.2590
  -7.250  -0.3604   0.09356   0.08775  -0.0224   1.0000   0.2641
  -7.000  -0.3624   0.09121   0.08550  -0.0192   1.0000   0.2778
  -6.750  -0.3972   0.09151   0.08599  -0.0157   1.0000   0.2793
  -6.500  -0.3769   0.08735   0.08184  -0.0121   1.0000   0.3009
  -6.250  -0.4088   0.08734   0.08200  -0.0088   1.0000   0.3077
  -6.000  -0.4164   0.08540   0.08015  -0.0055   1.0000   0.3220
  -5.750  -0.4288   0.08376   0.07861  -0.0023   1.0000   0.3371
  -5.500  -0.4426   0.08224   0.07719   0.0004   1.0000   0.3524
  -5.250  -0.4315   0.07897   0.07397   0.0053   1.0000   0.3748
  -5.000  -0.4499   0.07785   0.07294   0.0082   1.0000   0.3959
  -4.750  -0.4447   0.07514   0.07027   0.0130   1.0000   0.4216
  -4.500  -0.4487   0.07317   0.06837   0.0176   1.0000   0.4515
  -3.750  -0.3786   0.05003   0.04329  -0.0301   1.0000   0.1770
  -3.500  -0.3526   0.04504   0.03769  -0.0318   1.0000   0.1524
  -3.250  -0.3289   0.04194   0.03397  -0.0322   1.0000   0.1467
  -3.000  -0.3069   0.03924   0.03085  -0.0321   1.0000   0.1445
  -2.750  -0.2834   0.03675   0.02782  -0.0319   1.0000   0.1421
  -2.500  -0.2606   0.03505   0.02555  -0.0314   1.0000   0.1472
  -2.250  -0.2393   0.03343   0.02368  -0.0308   1.0000   0.1531
  -2.000  -0.2172   0.03221   0.02212  -0.0302   1.0000   0.1603
  -1.750  -0.1961   0.03121   0.02096  -0.0296   1.0000   0.1730
  -1.500  -0.1733   0.03028   0.01981  -0.0290   1.0000   0.1831
  -1.250  -0.1505   0.02971   0.01916  -0.0286   0.9993   0.2033
  -1.000  -0.1008   0.02922   0.01869  -0.0327   0.9897   0.2447
  -0.750  -0.0369   0.02596   0.01801  -0.0376   0.9822   1.0000
  -0.500   0.0070   0.02705   0.01841  -0.0415   0.9704   1.0000
  -0.250   0.0451   0.02800   0.01891  -0.0446   0.9581   1.0000
   0.000   0.0812   0.02893   0.01947  -0.0473   0.9456   1.0000
   0.250   0.1166   0.02986   0.02011  -0.0498   0.9331   1.0000
   0.500   0.1512   0.03080   0.02080  -0.0521   0.9205   1.0000
   0.750   0.1854   0.03174   0.02151  -0.0542   0.9079   1.0000
   1.000   0.2195   0.03268   0.02226  -0.0563   0.8953   1.0000
   1.250   0.2543   0.03361   0.02303  -0.0584   0.8827   1.0000
   1.500   0.2909   0.03454   0.02381  -0.0607   0.8704   1.0000
   1.750   0.3172   0.03539   0.02456  -0.0613   0.8572   1.0000
   2.000   0.3434   0.03626   0.02535  -0.0619   0.8440   1.0000
   2.250   0.3698   0.03716   0.02617  -0.0624   0.8307   1.0000
   2.500   0.3955   0.03807   0.02703  -0.0629   0.8176   1.0000
   2.750   0.4218   0.03899   0.02790  -0.0633   0.8044   1.0000
   3.000   0.4481   0.03991   0.02880  -0.0638   0.7913   1.0000
   3.250   0.4747   0.04081   0.02970  -0.0641   0.7782   1.0000
   3.500   0.5015   0.04172   0.03060  -0.0645   0.7650   1.0000
   3.750   0.5288   0.04259   0.03148  -0.0649   0.7519   1.0000
   4.000   0.5572   0.04343   0.03234  -0.0653   0.7390   1.0000
   4.250   0.5873   0.04418   0.03316  -0.0657   0.7260   1.0000
   4.500   0.6198   0.04480   0.03384  -0.0663   0.7131   1.0000
   4.750   0.6407   0.04577   0.03486  -0.0657   0.6993   1.0000
   5.000   0.6619   0.04674   0.03589  -0.0651   0.6855   1.0000
   5.250   0.6832   0.04770   0.03696  -0.0645   0.6716   1.0000
   5.500   0.7054   0.04862   0.03796  -0.0638   0.6576   1.0000
   5.750   0.7273   0.04953   0.03897  -0.0631   0.6435   1.0000
   6.000   0.7501   0.05037   0.03991  -0.0624   0.6293   1.0000
   6.250   0.7733   0.05116   0.04085  -0.0616   0.6150   1.0000
   6.500   0.7959   0.05196   0.04178  -0.0607   0.6008   1.0000
   6.750   0.8204   0.05257   0.04252  -0.0598   0.5864   1.0000
   7.000   0.8449   0.05312   0.04322  -0.0587   0.5719   1.0000
   7.250   0.8726   0.05331   0.04362  -0.0576   0.5575   1.0000
   7.500   0.9050   0.05295   0.04347  -0.0564   0.5430   1.0000
   7.750   0.9544   0.05099   0.04179  -0.0556   0.5284   1.0000
   8.000   1.0029   0.04900   0.04012  -0.0547   0.5125   1.0000
   8.250   0.9780   0.05325   0.04437  -0.0513   0.4954   1.0000
   8.500   1.0057   0.05286   0.04420  -0.0495   0.4781   1.0000
   8.750   1.1256   0.04428   0.03614  -0.0506   0.4534   1.0000
   9.000   1.1802   0.04151   0.03351  -0.0499   0.4264   1.0000
   9.250   1.2142   0.04044   0.03248  -0.0483   0.3983   1.0000
   9.500   1.2378   0.04013   0.03225  -0.0460   0.3694   1.0000
   9.750   1.2546   0.04030   0.03243  -0.0432   0.3398   1.0000
  10.000   1.2661   0.04072   0.03283  -0.0401   0.3093   1.0000
  10.250   1.2746   0.04135   0.03337  -0.0367   0.2781   1.0000
  10.500   1.2815   0.04218   0.03399  -0.0333   0.2466   1.0000
  10.750   1.2867   0.04345   0.03492  -0.0301   0.2158   1.0000
  11.000   1.2779   0.04555   0.03714  -0.0259   0.1945   1.0000
  11.250   1.2764   0.04759   0.03899  -0.0225   0.1714   1.0000
  11.500   1.2703   0.04998   0.04139  -0.0190   0.1539   1.0000
  11.750   1.2759   0.05258   0.04370  -0.0169   0.1334   1.0000
  12.000   1.2731   0.05543   0.04663  -0.0144   0.1202   1.0000
  12.250   1.2623   0.05871   0.05026  -0.0118   0.1130   1.0000
  12.500   1.2587   0.06219   0.05384  -0.0100   0.1045   1.0000
  12.750   1.2658   0.06565   0.05722  -0.0089   0.0947   1.0000
  13.000   1.2466   0.06979   0.06177  -0.0073   0.0933   1.0000
  13.250   1.2264   0.07442   0.06675  -0.0066   0.0921   1.0000
  13.500   1.2056   0.07954   0.07216  -0.0066   0.0916   1.0000
  13.750   1.1830   0.08534   0.07822  -0.0076   0.0921   1.0000
  14.000   1.1571   0.09183   0.08494  -0.0095   0.0928   1.0000
  14.250   1.1317   0.09903   0.09231  -0.0123   0.0939   1.0000
  14.500   1.1087   0.10665   0.10005  -0.0155   0.0949   1.0000
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