GRUMMAN K-2 AIRFOIL (k2-il)
GRUMMAN K-2 AIRFOIL - Grumman K-2 transonic airfoil (GAC .80-.53-10.3)
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(k2-il) GRUMMAN K-2 AIRFOIL Grumman K-2 transonic airfoil (GAC .80-.53-10.3) Max thickness 10.3% at 38.9% chord. Max camber 1.3% at 88.3% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
GRUMMAN K-2 AIRFOIL
118. 61.
0.0000000 0.0000000
0.0000071 0.0011686
0.0000586 0.0023600
0.0001571 0.0035115
0.0003214 0.0047086
0.0005157 0.0056972
0.0007929 0.0066958
0.0010814 0.0074543
0.0014157 0.0081343
0.0018657 0.0088400
0.0022714 0.0094072
0.0025857 0.0097872
0.0032071 0.0104415
0.0042600 0.0113829
0.0057200 0.0125129
0.0072529 0.0135629
0.0088729 0.0145743
0.0108814 0.0157258
0.0138414 0.0172715
0.0179786 0.0192029
0.0277086 0.0228943
0.0350486 0.0253472
0.0361529 0.0256858
0.0372343 0.0260086
0.0383143 0.0263243
0.0393900 0.0266343
0.0404457 0.0269300
0.0414829 0.0272158
0.0425014 0.0274929
0.0434971 0.0277558
0.0444829 0.0280129
0.0454457 0.0282586
0.0463871 0.0284943
0.0473100 0.0287215
0.0482457 0.0289472
0.0491600 0.0291643
0.0500514 0.0293715
0.0509286 0.0295715
0.0517929 0.0297643
0.0526486 0.0299529
0.0534871 0.0301329
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1.0000000 0.0137143
0.0000000 0.0000000
0.0000357 -.0010600
0.0000800 -.0019214
0.0001786 -.0027271
0.0002386 -.0035357
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0.0005357 -.0055257
0.0006914 -.0063300
0.0009500 -.0074671
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0.0022186 -.0112814
0.0024929 -.0118785
0.0030543 -.0129285
0.0033800 -.0135014
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0.0052700 -.0156971
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0.0072214 -.0172785
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0.0118800 -.0200357
0.0140557 -.0210628
0.0172786 -.0223985
0.0207086 -.0236500
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0.0303257 -.0265757
0.0441514 -.0299185
0.0674014 -.0343642
0.0984300 -.0389171
0.1301371 -.0425057
0.1733000 -.0460371
0.2176486 -.0484471
0.2346743 -.0490971
0.2586657 -.0498071
0.2804057 -.0502528
0.3056800 -.0505628
0.4081186 -.0497214
0.5049714 -.0457500
0.5733271 -.0406200
0.6240286 -.0352600
0.6560914 -.0310600
0.6858271 -.0265457
0.7180000 -.0209700
0.7430657 -.0161371
0.7780843 -.0087542
0.8078343 -.0021085
0.8322400 0.0033372
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0.8822386 0.0130315
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0.9128657 0.0169872
0.9298800 0.0182600
0.9447471 0.0187372
0.9617657 0.0184372
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0.9862514 0.0154915
0.9923314 0.0142843
0.9969214 0.0133443
1.0000000 0.0127143
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Polars for GRUMMAN K-2 AIRFOIL (k2-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| k2-il | 50,000 | 9 | 21.7 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| k2-il | 50,000 | 5 | 21.1 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| k2-il | 100,000 | 9 | 28.9 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| k2-il | 100,000 | 5 | 25.8 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| k2-il | 200,000 | 9 | 29 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| k2-il | 200,000 | 5 | 35.1 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| k2-il | 500,000 | 9 | 44 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| k2-il | 500,000 | 5 | 52.3 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| k2-il | 1,000,000 | 9 | 60.4 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| k2-il | 1,000,000 | 5 | 66.7 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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