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GRUMMAN K-2 AIRFOIL (k2-il)

GRUMMAN K-2 AIRFOIL - Grumman K-2 transonic airfoil (GAC .80-.53-10.3)


Airfoil k2-il
Details Dat file Parser  
(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
 0.0543471 0.0303158
 0.0552100 0.0304943
 0.0560929 0.0306743
 0.0570100 0.0308586
 0.0579814 0.0310486
 0.0590343 0.0312515
 0.0601700 0.0314658
 0.0614343 0.0316986
 0.0628500 0.0319543
 0.0643114 0.0322129
 0.0659500 0.0325015
 0.0678614 0.0328200
 0.0699900 0.0331715
 0.0724200 0.0335629
 0.0751457 0.0339900
 0.0782357 0.0344600
 0.0816457 0.0349629
 0.0854129 0.0355015
 0.0895114 0.0360686
 0.0939043 0.0366543
 0.0985671 0.0372543
 0.1033900 0.0378500
 0.1083971 0.0384472
 0.1134700 0.0390272
 0.1186700 0.0395986
 0.1236771 0.0401272
 0.1287971 0.0406472
 0.1340686 0.0411600
 0.1395657 0.0416729
 0.1454129 0.0421972
 0.1517014 0.0427343
 0.1585786 0.0432943
 0.1661814 0.0438829
 0.1746343 0.0445015
 0.1840629 0.0451529
 0.1946286 0.0458329
 0.2063086 0.0465358
 0.2192486 0.0472572
 0.2334586 0.0479872
 0.2489000 0.0487129
 0.2655671 0.0494229
 0.2833329 0.0501072
 0.3023686 0.0507600
 0.3225600 0.0511112
 0.3438143 0.0519258
 0.3660086 0.0524215
 0.3890029 0.0528429
 0.4126457 0.0531829
 0.4367900 0.0534343
 0.4612471 0.0535986
 0.4858900 0.0536658
 0.5105614 0.0536386
 0.5351386 0.0535158
 0.5594529 0.0532986
 0.5834171 0.0529886
 0.6069171 0.0525900
 0.6298729 0.0521086
 0.6537371 0.0514986
 0.6991757 0.0500015
 0.7205300 0.0491215
 0.7407871 0.0481486
 0.7597571 0.0470886
 0.7772314 0.0459558
 0.7931586 0.0447829
 0.8075943 0.0436029
 0.8206986 0.0424372
 0.8325629 0.0413100
 0.8830800 0.0358143
 0.9139014 0.0314886
 0.9355000 0.0279629
 0.9512986 0.0250186
 0.9620486 0.0228029
 0.9760600 0.0196558
 0.9842657 0.0177100
 0.9911214 0.0160258
 0.9960857 0.0147872
 1.0000000 0.0137143

 0.0000000 0.0000000
 0.0000357 -.0010600
 0.0000800 -.0019214
 0.0001786 -.0027271
 0.0002386 -.0035357
 0.0003900 -.0046557
 0.0005357 -.0055257
 0.0006914 -.0063300
 0.0009500 -.0074671
 0.0012786 -.0086771
 0.0016286 -.0097700
 0.0022186 -.0112814
 0.0024929 -.0118785
 0.0030543 -.0129285
 0.0033800 -.0135014
 0.0038586 -.0141657
 0.0044857 -.0149100
 0.0052700 -.0156971
 0.0061586 -.0164685
 0.0072214 -.0172785
 0.0083929 -.0180728
 0.0097943 -.0189200
 0.0118800 -.0200357
 0.0140557 -.0210628
 0.0172786 -.0223985
 0.0207086 -.0236500
 0.0249829 -.0250342
 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
 0.8599543 0.0090729
 0.8822386 0.0130315
 0.8955871 0.0149929
 0.9128657 0.0169872
 0.9298800 0.0182600
 0.9447471 0.0187372
 0.9617657 0.0184372
 0.9757857 0.0169015
 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)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   k2-il50,000921.7 at α=4.75°Mach=0 Ncrit=9Xfoil predictionDetails
   k2-il50,000521.1 at α=6.25°Mach=0 Ncrit=5Xfoil predictionDetails
   k2-il100,000928.9 at α=4°Mach=0 Ncrit=9Xfoil predictionDetails
   k2-il100,000525.8 at α=7°Mach=0 Ncrit=5Xfoil predictionDetails
   k2-il200,000929 at α=6.75°Mach=0 Ncrit=9Xfoil predictionDetails
   k2-il200,000535.1 at α=7°Mach=0 Ncrit=5Xfoil predictionDetails
   k2-il500,000944 at α=6.25°Mach=0 Ncrit=9Xfoil predictionDetails
   k2-il500,000552.3 at α=6.25°Mach=0 Ncrit=5Xfoil predictionDetails
   k2-il1,000,000960.4 at α=6°Mach=0 Ncrit=9Xfoil predictionDetails
   k2-il1,000,000566.7 at α=7.25°Mach=0 Ncrit=5Xfoil predictionDetails
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