GRUMMAN K-3 AIRFOIL (k3-il)
GRUMMAN K-3 AIRFOIL - Grumman K-3 transonic airfoil (GAC .70-.83-17.5)
| Details | Dat file | Parser | |
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(k3-il) GRUMMAN K-3 AIRFOIL Grumman K-3 transonic airfoil (GAC .70-.83-17.5) Max thickness 17.3% at 33.1% chord. Max camber 2.6% at 74.7% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
GRUMMAN K-3 AIRFOIL
113. 71.
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0.0004886 0.0057214
0.0015386 0.0106043
0.0020200 0.0120129
0.0025914 0.0134300
0.0031186 0.0145029
0.0038543 0.0157514
0.0047071 0.0169829
0.0058000 0.0183600
0.0068843 0.0195829
0.0082629 0.0209986
0.0099843 0.0226014
0.0120957 0.0243900
0.0139586 0.0258471
0.0163900 0.0276143
0.0183529 0.0289471
0.0217043 0.0310729
0.0250600 0.0330343
0.0382014 0.0396357
0.0403171 0.0405543
0.0426057 0.0415114
0.0449714 0.0424686
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0.0502629 0.0444800
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0.0668914 0.0498514
0.0709000 0.0509614
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0.9966357 -.0195957
1.0000000 -.0208643
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Polars for GRUMMAN K-3 AIRFOIL (k3-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| k3-il | 50,000 | 9 | 24.9 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| k3-il | 50,000 | 5 | 23 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| k3-il | 100,000 | 9 | 30.1 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| k3-il | 100,000 | 5 | 33.3 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| k3-il | 200,000 | 9 | 49.2 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| k3-il | 200,000 | 5 | 50.1 at α=1.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| k3-il | 500,000 | 9 | 79.4 at α=1.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| k3-il | 500,000 | 5 | 65.9 at α=0.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| k3-il | 1,000,000 | 9 | 94.2 at α=0.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| k3-il | 1,000,000 | 5 | 70.2 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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