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SIKORSKY SC1094R8 AIRFOIL (sc1095r8-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: SIKORSKY SC1094R8 AIRFOIL (sc1095r8-il)
Reynolds number: 50,000
Max Cl/Cd: 24.41 at α=4°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-sc1095r8-il-50000.txt
Download as CSV file: xf-sc1095r8-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: SIKORSKY SC1094R8 AIRFOIL                       
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -6.750  -0.4718   0.09959   0.09294   0.0044   1.0000   0.2587
  -6.500  -0.4900   0.09820   0.09168   0.0017   1.0000   0.2719
  -6.250  -0.4776   0.09452   0.08804   0.0033   1.0000   0.2883
  -6.000  -0.4770   0.09164   0.08525   0.0036   1.0000   0.3056
  -5.750  -0.4440   0.08720   0.08081   0.0079   1.0000   0.3308
  -5.500  -0.4546   0.08542   0.07916   0.0084   1.0000   0.3558
  -5.250  -0.4386   0.08241   0.07620   0.0118   1.0000   0.3890
  -5.000  -0.4365   0.08028   0.07416   0.0147   1.0000   0.4244
  -4.750  -0.3992   0.07650   0.07038   0.0194   1.0000   0.4721
  -4.500  -0.3868   0.07441   0.06836   0.0240   1.0000   0.5259
  -4.250  -0.3584   0.07174   0.06570   0.0291   1.0000   0.5948
  -4.000  -0.2956   0.06716   0.06107   0.0326   1.0000   0.6952
  -3.000  -0.3383   0.04306   0.03527  -0.0248   1.0000   0.2050
  -2.750  -0.3094   0.03959   0.03105  -0.0250   1.0000   0.1702
  -2.500  -0.2875   0.03700   0.02831  -0.0240   1.0000   0.1634
  -2.250  -0.2635   0.03457   0.02541  -0.0231   1.0000   0.1553
  -2.000  -0.2387   0.03285   0.02321  -0.0219   1.0000   0.1497
  -1.750  -0.2154   0.03085   0.02102  -0.0208   1.0000   0.1470
  -1.500  -0.1912   0.02919   0.01913  -0.0196   1.0000   0.1460
  -1.250  -0.1670   0.02790   0.01756  -0.0184   1.0000   0.1487
  -1.000  -0.1423   0.02686   0.01622  -0.0171   1.0000   0.1516
  -0.750  -0.1179   0.02536   0.01478  -0.0161   1.0000   0.1555
  -0.500  -0.0934   0.02439   0.01382  -0.0149   1.0000   0.1637
  -0.250  -0.0687   0.02347   0.01292  -0.0136   1.0000   0.1752
   0.000  -0.0439   0.02264   0.01214  -0.0125   1.0000   0.1910
   0.250  -0.0195   0.02172   0.01141  -0.0117   1.0000   0.2230
   0.500   0.0102   0.01798   0.01057  -0.0085   1.0000   1.0000
   0.750   0.0283   0.01832   0.01042  -0.0072   1.0000   1.0000
   1.000   0.0459   0.01873   0.01057  -0.0063   1.0000   1.0000
   1.250   0.0631   0.01924   0.01091  -0.0057   1.0000   1.0000
   1.500   0.0797   0.01990   0.01143  -0.0054   1.0000   1.0000
   1.750   0.1428   0.02086   0.01224  -0.0130   0.9793   1.0000
   2.000   0.2516   0.02123   0.01252  -0.0261   0.9298   1.0000
   2.250   0.3389   0.02065   0.01196  -0.0334   0.8785   1.0000
   2.500   0.3885   0.01996   0.01124  -0.0334   0.8257   1.0000
   2.750   0.4186   0.01943   0.01057  -0.0299   0.7695   1.0000
   3.000   0.4400   0.01921   0.01008  -0.0255   0.7067   1.0000
   3.250   0.4597   0.01931   0.00977  -0.0213   0.6408   1.0000
   3.500   0.4795   0.01977   0.00973  -0.0178   0.5752   1.0000
   3.750   0.5010   0.02053   0.00998  -0.0152   0.5158   1.0000
   4.000   0.5236   0.02145   0.01046  -0.0132   0.4651   1.0000
   4.250   0.5473   0.02248   0.01117  -0.0118   0.4247   1.0000
   4.500   0.5716   0.02351   0.01191  -0.0105   0.3933   1.0000
   4.750   0.5965   0.02460   0.01286  -0.0094   0.3677   1.0000
   5.000   0.6215   0.02568   0.01375  -0.0084   0.3473   1.0000
   5.250   0.6465   0.02682   0.01477  -0.0075   0.3299   1.0000
   5.500   0.6716   0.02812   0.01613  -0.0068   0.3158   1.0000
   5.750   0.6963   0.02952   0.01760  -0.0060   0.3036   1.0000
   6.000   0.7209   0.03085   0.01886  -0.0052   0.2929   1.0000
   6.250   0.7448   0.03231   0.02045  -0.0045   0.2828   1.0000
   6.500   0.7685   0.03409   0.02230  -0.0039   0.2763   1.0000
   6.750   0.7899   0.03616   0.02473  -0.0033   0.2698   1.0000
   7.000   0.8140   0.03772   0.02622  -0.0026   0.2637   1.0000
   7.250   0.8321   0.04023   0.02909  -0.0020   0.2582   1.0000
   7.500   0.8491   0.04288   0.03208  -0.0016   0.2534   1.0000
   7.750   0.8658   0.04574   0.03520  -0.0012   0.2507   1.0000
   8.000   0.8811   0.04888   0.03857  -0.0008   0.2489   1.0000
   8.250   0.8966   0.05200   0.04185  -0.0005   0.2472   1.0000
   8.500   0.9082   0.05575   0.04577  -0.0003   0.2456   1.0000
   8.750   0.9080   0.06087   0.05124  -0.0009   0.2454   1.0000
   9.000   0.9042   0.06653   0.05719  -0.0021   0.2464   1.0000
   9.250   0.8492   0.08028   0.07134  -0.0101   0.2618   1.0000
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