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LWK 80-080 (lwk80080-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: LWK 80-080 (lwk80080-il)
Reynolds number: 200,000
Max Cl/Cd: 35.7 at α=4.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-lwk80080-il-200000-n5.txt
Download as CSV file: xf-lwk80080-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: LWK 80-080                                      
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.6717   0.08298   0.07953  -0.0114   1.0000   0.0114
  -9.500  -0.6847   0.07412   0.07069  -0.0195   1.0000   0.0113
  -9.250  -0.7005   0.06780   0.06430  -0.0237   1.0000   0.0111
  -9.000  -0.7160   0.06306   0.05946  -0.0243   1.0000   0.0110
  -8.750  -0.7290   0.05807   0.05432  -0.0238   1.0000   0.0109
  -8.500  -0.7381   0.05284   0.04886  -0.0227   1.0000   0.0109
  -8.250  -0.7423   0.04793   0.04368  -0.0211   1.0000   0.0108
  -8.000  -0.7443   0.04288   0.03826  -0.0190   1.0000   0.0106
  -7.750  -0.7432   0.03791   0.03285  -0.0164   1.0000   0.0108
  -7.500  -0.7371   0.03372   0.02818  -0.0139   1.0000   0.0109
  -7.250  -0.7269   0.03011   0.02407  -0.0115   1.0000   0.0111
  -7.000  -0.7127   0.02706   0.02051  -0.0093   1.0000   0.0119
  -6.750  -0.6929   0.02584   0.01896  -0.0079   1.0000   0.0130
  -6.500  -0.6768   0.02305   0.01581  -0.0061   1.0000   0.0138
  -6.250  -0.6578   0.02140   0.01398  -0.0048   1.0000   0.0148
  -6.000  -0.6378   0.01993   0.01233  -0.0033   1.0000   0.0155
  -5.750  -0.6178   0.01869   0.01096  -0.0019   1.0000   0.0163
  -5.500  -0.5987   0.01759   0.00970  -0.0003   1.0000   0.0174
  -5.250  -0.5807   0.01664   0.00866   0.0015   1.0000   0.0186
  -5.000  -0.5642   0.01585   0.00777   0.0035   1.0000   0.0201
  -4.750  -0.5395   0.01486   0.00673   0.0037   0.9916   0.0249
  -4.500  -0.5078   0.01433   0.00612   0.0026   0.9842   0.0318
  -4.250  -0.4769   0.01366   0.00544   0.0015   0.9771   0.0424
  -4.000  -0.4450   0.01310   0.00485   0.0003   0.9707   0.0573
  -3.750  -0.4136   0.01251   0.00433  -0.0009   0.9646   0.0846
  -3.500  -0.3826   0.01189   0.00390  -0.0021   0.9585   0.1310
  -3.250  -0.3535   0.01108   0.00350  -0.0031   0.9525   0.2309
  -3.000  -0.3310   0.00992   0.00312  -0.0028   0.9449   0.4147
  -2.750  -0.3118   0.00896   0.00306  -0.0011   0.9379   0.6268
  -2.500  -0.2844   0.00884   0.00313  -0.0007   0.9319   0.7091
  -2.250  -0.2534   0.00884   0.00313  -0.0011   0.9275   0.7488
  -2.000  -0.2264   0.00887   0.00314  -0.0007   0.9212   0.7758
  -1.750  -0.1979   0.00892   0.00318  -0.0004   0.9160   0.8023
  -1.500  -0.1694   0.00898   0.00324  -0.0001   0.9114   0.8253
  -1.250  -0.1432   0.00902   0.00327   0.0005   0.9055   0.8422
  -1.000  -0.1135   0.00904   0.00327   0.0003   0.9010   0.8540
  -0.750  -0.0854   0.00904   0.00325   0.0004   0.8957   0.8622
  -0.500  -0.0576   0.00904   0.00322   0.0004   0.8902   0.8693
  -0.250  -0.0275   0.00903   0.00319  -0.0001   0.8860   0.8747
   0.000   0.0000   0.00903   0.00319   0.0000   0.8801   0.8801
   0.250   0.0275   0.00903   0.00319   0.0001   0.8747   0.8860
   0.500   0.0577   0.00904   0.00322  -0.0004   0.8694   0.8902
   0.750   0.0854   0.00904   0.00325  -0.0004   0.8621   0.8957
   1.000   0.1134   0.00904   0.00327  -0.0003   0.8538   0.9009
   1.250   0.1431   0.00902   0.00327  -0.0005   0.8419   0.9055
   1.500   0.1694   0.00898   0.00324   0.0001   0.8253   0.9113
   1.750   0.1979   0.00891   0.00318   0.0005   0.8015   0.9161
   2.000   0.2263   0.00886   0.00314   0.0007   0.7748   0.9213
   2.250   0.2534   0.00884   0.00313   0.0011   0.7486   0.9275
   2.500   0.2846   0.00884   0.00315   0.0006   0.7118   0.9318
   2.750   0.3122   0.00895   0.00311   0.0010   0.6329   0.9378
   3.000   0.3304   0.00997   0.00313   0.0029   0.4063   0.9450
   3.250   0.3529   0.01116   0.00351   0.0031   0.2179   0.9528
   3.500   0.3826   0.01190   0.00390   0.0020   0.1293   0.9586
   3.750   0.4137   0.01250   0.00433   0.0009   0.0853   0.9647
   4.000   0.4451   0.01309   0.00486  -0.0003   0.0579   0.9707
   4.250   0.4770   0.01363   0.00540  -0.0015   0.0407   0.9770
   4.500   0.5080   0.01425   0.00604  -0.0026   0.0299   0.9840
   4.750   0.5384   0.01508   0.00689  -0.0036   0.0218   0.9918
   5.000   0.5641   0.01588   0.00781  -0.0035   0.0194   1.0000
   5.250   0.5805   0.01669   0.00871  -0.0014   0.0181   1.0000
   5.500   0.5985   0.01764   0.00975   0.0004   0.0165   1.0000
   5.750   0.6177   0.01873   0.01100   0.0019   0.0160   1.0000
   6.000   0.6375   0.01997   0.01236   0.0034   0.0150   1.0000
   6.250   0.6576   0.02146   0.01403   0.0048   0.0146   1.0000
   6.500   0.6765   0.02324   0.01601   0.0062   0.0138   1.0000
   6.750   0.6938   0.02554   0.01867   0.0078   0.0127   1.0000
   7.000   0.7121   0.02734   0.02082   0.0094   0.0119   1.0000
   7.250   0.7265   0.03022   0.02418   0.0115   0.0113   1.0000
   7.500   0.7368   0.03381   0.02827   0.0139   0.0110   1.0000
   7.750   0.7436   0.03778   0.03270   0.0163   0.0111   1.0000
   8.000   0.7465   0.04224   0.03757   0.0187   0.0110   1.0000
   8.250   0.7442   0.04744   0.04315   0.0209   0.0110   1.0000
   8.500   0.7375   0.05298   0.04901   0.0227   0.0109   1.0000
   8.750   0.7308   0.05769   0.05392   0.0237   0.0111   1.0000
   9.000   0.7188   0.06260   0.05899   0.0242   0.0111   1.0000
   9.250   0.7026   0.06739   0.06388   0.0237   0.0113   1.0000
   9.500   0.6866   0.07364   0.07021   0.0198   0.0115   1.0000
   9.750   0.6755   0.08168   0.07825   0.0124   0.0117   1.0000
  10.000   0.6664   0.08937   0.08589   0.0067   0.0117   1.0000
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