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LWK 80-100 (lwk80100-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: LWK 80-100 (lwk80100-il)
Reynolds number: 200,000
Max Cl/Cd: 38.32 at α=6.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-lwk80100-il-200000-n5.txt
Download as CSV file: xf-lwk80100-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: LWK 80-100                                      
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.750  -0.7206   0.08852   0.08503  -0.0162   1.0000   0.0137
 -11.500  -0.7737   0.06829   0.06465  -0.0308   1.0000   0.0129
 -11.250  -0.8086   0.05974   0.05587  -0.0355   1.0000   0.0125
 -11.000  -0.8370   0.05379   0.04967  -0.0365   1.0000   0.0124
 -10.750  -0.8588   0.04936   0.04499  -0.0354   1.0000   0.0125
 -10.500  -0.8773   0.04567   0.04102  -0.0327   1.0000   0.0127
 -10.250  -0.8909   0.04230   0.03734  -0.0292   1.0000   0.0128
 -10.000  -0.8959   0.03903   0.03371  -0.0263   1.0000   0.0128
  -9.750  -0.8952   0.03605   0.03036  -0.0237   1.0000   0.0132
  -9.500  -0.8897   0.03333   0.02728  -0.0213   1.0000   0.0135
  -9.250  -0.8800   0.03093   0.02452  -0.0193   1.0000   0.0139
  -9.000  -0.8669   0.02884   0.02209  -0.0174   1.0000   0.0147
  -8.750  -0.8511   0.02709   0.02004  -0.0159   1.0000   0.0152
  -8.500  -0.8357   0.02532   0.01809  -0.0143   1.0000   0.0160
  -8.250  -0.8184   0.02420   0.01689  -0.0130   1.0000   0.0169
  -8.000  -0.8000   0.02353   0.01612  -0.0119   1.0000   0.0184
  -7.750  -0.7818   0.02237   0.01482  -0.0104   1.0000   0.0195
  -7.500  -0.7639   0.02127   0.01359  -0.0088   1.0000   0.0207
  -7.250  -0.7466   0.02036   0.01254  -0.0072   1.0000   0.0218
  -7.000  -0.7333   0.01925   0.01143  -0.0049   0.9962   0.0237
  -6.750  -0.7019   0.01850   0.01061  -0.0063   0.9850   0.0271
  -6.500  -0.6697   0.01781   0.00978  -0.0078   0.9759   0.0307
  -6.250  -0.6387   0.01691   0.00886  -0.0091   0.9670   0.0358
  -6.000  -0.6059   0.01635   0.00820  -0.0106   0.9597   0.0413
  -5.750  -0.5749   0.01561   0.00746  -0.0118   0.9526   0.0486
  -5.500  -0.5440   0.01504   0.00684  -0.0130   0.9458   0.0569
  -5.250  -0.5127   0.01456   0.00627  -0.0141   0.9397   0.0662
  -5.000  -0.4836   0.01404   0.00578  -0.0148   0.9328   0.0800
  -4.750  -0.4539   0.01354   0.00532  -0.0156   0.9271   0.0989
  -4.500  -0.4284   0.01307   0.00492  -0.0155   0.9203   0.1264
  -4.250  -0.4026   0.01251   0.00455  -0.0156   0.9148   0.1743
  -4.000  -0.3809   0.01188   0.00422  -0.0149   0.9085   0.2450
  -3.750  -0.3624   0.01112   0.00389  -0.0136   0.9022   0.3489
  -3.500  -0.3472   0.01031   0.00363  -0.0115   0.8965   0.4769
  -3.250  -0.3317   0.00980   0.00368  -0.0088   0.8907   0.6043
  -3.000  -0.3079   0.00976   0.00381  -0.0076   0.8865   0.6729
  -2.750  -0.2829   0.00981   0.00387  -0.0067   0.8822   0.7073
  -2.500  -0.2581   0.00987   0.00390  -0.0059   0.8776   0.7289
  -2.250  -0.2325   0.00996   0.00395  -0.0052   0.8737   0.7486
  -2.000  -0.2072   0.01007   0.00402  -0.0043   0.8702   0.7694
  -1.750  -0.1829   0.01021   0.00417  -0.0032   0.8657   0.7860
  -1.500  -0.1580   0.01031   0.00426  -0.0023   0.8616   0.7995
  -1.250  -0.1315   0.01039   0.00430  -0.0018   0.8581   0.8096
  -1.000  -0.1047   0.01043   0.00433  -0.0014   0.8547   0.8173
  -0.750  -0.0798   0.01046   0.00434  -0.0008   0.8502   0.8243
  -0.500  -0.0534   0.01046   0.00433  -0.0005   0.8463   0.8295
  -0.250  -0.0256   0.01047   0.00432  -0.0004   0.8429   0.8338
   0.000   0.0000   0.01047   0.00432   0.0000   0.8386   0.8386
   0.250   0.0257   0.01047   0.00432   0.0004   0.8338   0.8429
   0.500   0.0535   0.01046   0.00433   0.0005   0.8295   0.8462
   0.750   0.0799   0.01046   0.00434   0.0008   0.8243   0.8503
   1.000   0.1048   0.01044   0.00433   0.0014   0.8173   0.8548
   1.250   0.1315   0.01038   0.00430   0.0018   0.8095   0.8581
   1.500   0.1581   0.01030   0.00425   0.0024   0.7992   0.8616
   1.750   0.1830   0.01020   0.00416   0.0033   0.7855   0.8657
   2.000   0.2073   0.01007   0.00402   0.0043   0.7693   0.8702
   2.250   0.2324   0.00995   0.00394   0.0052   0.7477   0.8737
   2.500   0.2582   0.00987   0.00390   0.0059   0.7288   0.8776
   2.750   0.2829   0.00981   0.00387   0.0067   0.7065   0.8822
   3.000   0.3079   0.00976   0.00381   0.0076   0.6724   0.8865
   3.250   0.3315   0.00981   0.00366   0.0089   0.5997   0.8908
   3.500   0.3473   0.01031   0.00363   0.0115   0.4771   0.8965
   3.750   0.3634   0.01106   0.00388   0.0135   0.3577   0.9022
   4.000   0.3819   0.01181   0.00421   0.0148   0.2548   0.9085
   4.250   0.4028   0.01250   0.00455   0.0156   0.1755   0.9148
   4.500   0.4287   0.01305   0.00494   0.0155   0.1286   0.9202
   4.750   0.4542   0.01352   0.00531   0.0156   0.1007   0.9271
   5.000   0.4840   0.01401   0.00577   0.0147   0.0820   0.9327
   5.250   0.5132   0.01450   0.00624   0.0140   0.0677   0.9396
   5.500   0.5442   0.01501   0.00681   0.0129   0.0576   0.9458
   5.750   0.5752   0.01559   0.00744   0.0118   0.0486   0.9526
   6.000   0.6062   0.01630   0.00814   0.0105   0.0410   0.9595
   6.250   0.6392   0.01684   0.00879   0.0090   0.0350   0.9669
   6.500   0.6704   0.01770   0.00966   0.0077   0.0298   0.9756
   6.750   0.7028   0.01834   0.01044   0.0062   0.0255   0.9848
   7.000   0.7328   0.01933   0.01147   0.0050   0.0227   0.9987
   7.250   0.7468   0.02035   0.01256   0.0072   0.0215   1.0000
   7.500   0.7640   0.02130   0.01364   0.0089   0.0200   1.0000
   7.750   0.7817   0.02241   0.01487   0.0105   0.0189   1.0000
   8.000   0.7998   0.02348   0.01606   0.0119   0.0178   1.0000
   8.250   0.8179   0.02433   0.01700   0.0132   0.0166   1.0000
   8.500   0.8337   0.02576   0.01853   0.0146   0.0153   1.0000
   8.750   0.8509   0.02721   0.02022   0.0160   0.0148   1.0000
   9.000   0.8663   0.02902   0.02232   0.0176   0.0143   1.0000
   9.250   0.8791   0.03114   0.02476   0.0194   0.0138   1.0000
   9.500   0.8886   0.03354   0.02751   0.0215   0.0132   1.0000
   9.750   0.8943   0.03620   0.03053   0.0238   0.0130   1.0000
  10.000   0.8954   0.03910   0.03378   0.0264   0.0128   1.0000
  10.250   0.8898   0.04239   0.03742   0.0293   0.0125   1.0000
  10.500   0.8780   0.04551   0.04083   0.0327   0.0124   1.0000
  10.750   0.8584   0.04941   0.04502   0.0355   0.0124   1.0000
  11.000   0.8304   0.05471   0.05063   0.0365   0.0126   1.0000
  11.250   0.8069   0.06006   0.05619   0.0353   0.0126   1.0000
  11.500   0.7737   0.06838   0.06473   0.0306   0.0126   1.0000
  11.750   0.7125   0.09140   0.08789   0.0144   0.0136   1.0000
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