FX 74-Cl5-140 MOD (smoothed) (fx74modsm-il)
FX 74-Cl5-140 MOD (smoothed) - Modified Wortmann FX 74-CL5-140 high lift airfoil
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(fx74modsm-il) FX 74-Cl5-140 MOD (smoothed) Modified Wortmann FX 74-CL5-140 high lift airfoil Max thickness 13.1% at 27.1% chord. Max camber 9.7% at 41.6% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Selig format |
FX 74-Cl5-140 MOD (smoothed)
1.00000 0.00009
0.99754 0.00189
0.99070 0.00624
0.98037 0.01150
0.96698 0.01741
0.95044 0.02402
0.93064 0.03188
0.90775 0.04001
0.88202 0.04848
0.85370 0.05718
0.82309 0.06616
0.79048 0.07549
0.75616 0.08510
0.72043 0.09482
0.68359 0.10446
0.64594 0.11385
0.60778 0.12287
0.56937 0.13137
0.53099 0.13916
0.49265 0.14604
0.45435 0.15177
0.41638 0.15606
0.37887 0.15868
0.34204 0.15944
0.30609 0.15820
0.27120 0.15493
0.23760 0.14964
0.20549 0.14243
0.17504 0.13344
0.14648 0.12292
0.11999 0.11110
0.09576 0.09826
0.07395 0.08459
0.05468 0.07030
0.03811 0.05576
0.02433 0.04145
0.01338 0.02769
0.00548 0.01518
0.00098 0.00518
0.00000 -0.00021
0.00098 -0.00435
0.00548 -0.00787
0.01338 -0.00871
0.02433 -0.00754
0.03811 -0.00539
0.05468 -0.00292
0.07395 -0.00022
0.09576 0.00270
0.11999 0.00584
0.14648 0.00921
0.17504 0.01279
0.20549 0.01651
0.23760 0.02030
0.27120 0.02410
0.30609 0.02786
0.34204 0.03152
0.37887 0.03503
0.41638 0.03832
0.45435 0.04134
0.49265 0.04400
0.53099 0.04624
0.56937 0.04801
0.60778 0.04925
0.64594 0.04992
0.68359 0.04997
0.72043 0.04936
0.75616 0.04807
0.79048 0.04608
0.82309 0.04334
0.85370 0.03978
0.88202 0.03537
0.90775 0.03013
0.93064 0.02434
0.95044 0.01851
0.96698 0.01290
0.98037 0.00756
0.99070 0.00319
0.99754 0.00068
1.00000 -0.00003
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Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file |
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Polars for FX 74-Cl5-140 MOD (smoothed) (fx74modsm-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| fx74modsm-il | 50,000 | 9 | 6.2 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx74modsm-il | 50,000 | 5 | 28.8 at α=1.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx74modsm-il | 100,000 | 9 | 41.7 at α=1.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx74modsm-il | 100,000 | 5 | 58.1 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx74modsm-il | 200,000 | 9 | 76.4 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx74modsm-il | 200,000 | 5 | 84.1 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx74modsm-il | 500,000 | 9 | 118.7 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx74modsm-il | 500,000 | 5 | 119.7 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx74modsm-il | 1,000,000 | 9 | 152.6 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx74modsm-il | 1,000,000 | 5 | 149.8 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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