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GRUMMAN K-3 AIRFOIL (k3-il)

GRUMMAN K-3 AIRFOIL - Grumman K-3 transonic airfoil (GAC .70-.83-17.5)


Airfoil k3-il
Details Dat file Parser  
(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.

 0.0000000 0.0000000
 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
 0.0475314 0.0434614
 0.0502629 0.0444800
 0.0531729 0.0455200
 0.0562771 0.0465786
 0.0595929 0.0476571
 0.0631214 0.0487471
 0.0668914 0.0498514
 0.0709000 0.0509614
 0.0751571 0.0520743
 0.0796643 0.0531886
 0.0844271 0.0543029
 0.0894343 0.0554129
 0.0947000 0.0565229
 0.1002157 0.0576286
 0.1059843 0.0587314
 0.1120114 0.0598314
 0.1183043 0.0609286
 0.1248714 0.0620214
 0.1317014 0.0631071
 0.1388129 0.0641857
 0.1462143 0.0652586
 0.1539000 0.0663200
 0.1613686 0.0673043
 0.1691000 0.0682757
 0.1771143 0.0692371
 0.1854086 0.0701843
 0.1939843 0.0711143
 0.2028471 0.0720257
 0.2119943 0.0729143
 0.2214343 0.0737814
 0.2311686 0.0746200
 0.2411829 0.0754314
 0.2514843 0.0762086
 0.2620586 0.0769514
 0.2729143 0.0776557
 0.2840300 0.0783200
 0.2954000 0.0789414
 0.3070257 0.0795171
 0.3188786 0.0800457
 0.3309529 0.0805243
 0.3432414 0.0809471
 0.3557186 0.0813129
 0.3683757 0.0816186
 0.3811843 0.0818643
 0.3941443 0.0820457
 0.4072057 0.0821600
 0.4203357 0.0822086
 0.4335143 0.0821914
 0.4466657 0.0821071
 0.4597629 0.0819571
 0.4727386 0.0817443
 0.4855114 0.0814729
 0.4980371 0.0811443
 0.5102629 0.0807657
 0.5222157 0.0803371
 0.5338314 0.0798657
 0.5451071 0.0793529
 0.5559843 0.0788071
 0.5664200 0.0782329
 0.5764200 0.0776343
 0.5859743 0.0770171
 0.5951100 0.0763829
 0.6038271 0.0757414
 0.6121743 0.0750771
 0.6201800 0.0744171
 0.6278971 0.0737357
 0.6353586 0.0730486
 0.6426300 0.0723300
 0.6497643 0.0715957
 0.6568086 0.0708386
 0.6638243 0.0700414
 0.6709114 0.0692000
 0.6780857 0.0682914
 0.7176971 0.0623014
 0.7321471 0.0599429
 0.7470571 0.0573614
 0.7652600 0.0539671
 0.7819986 0.0506757
 0.7962300 0.0477214
 0.8118129 0.0443214
 0.8325857 0.0394843
 0.8546343 0.0340514
 0.8783143 0.0277714
 0.9022829 0.0207614
 0.9196157 0.0152829
 0.9376943 0.0090271
 0.9533286 0.0032571
 0.9728586 -.0038986
 0.9890486 -.0096900
 0.9960643 -.0120514
 1.0000000 -.0132229

 0.0000000 0.0000000
 0.0003100 -.0075229
 0.0011129 -.0125671
 0.0022557 -.0175200
 0.0036986 -.0218157
 0.0055971 -.0261943
 0.0080329 -.0306029
 0.0110157 -.0349057
 0.0157857 -.0403014
 0.0178443 -.0422057
 0.0198043 -.0439357
 0.0229600 -.0464700
 0.0281086 -.0501057
 0.0354271 -.0545171
 0.0451557 -.0594271
 0.0570871 -.0644200
 0.0704843 -.0690557
 0.0741900 -.0702771
 0.0859486 -.0735500
 0.1017029 -.0772429
 0.1137200 -.0796300
 0.1267543 -.0818786
 0.1390057 -.0837186
 0.1464771 -.0846900
 0.1522171 -.0854514
 0.1638014 -.0867786
 0.1665686 -.0870371
 0.1810486 -.0884686
 0.1909529 -.0892714
 0.2119743 -.0907386
 0.2299400 -.0916971
 0.2426600 -.0922214
 0.2575586 -.0926814
 0.2712729 -.0929600
 0.2857757 -.0931171
 0.3010900 -.0931100
 0.3172943 -.0929171
 0.3344229 -.0924971
 0.3549871 -.0916871
 0.3712514 -.0908000
 0.3866614 -.0897500
 0.4010714 -.0885829
 0.4114871 -.0876300
 0.4321914 -.0854586
 0.4542043 -.0827486
 0.4776771 -.0794414
 0.5024986 -.0755214
 0.5282900 -.0710729
 0.5531829 -.0665000
 0.5760700 -.0621257
 0.5908929 -.0592229
 0.6102186 -.0554214
 0.6282757 -.0518729
 0.6506800 -.0475157
 0.6724843 -.0433714
 0.6990900 -.0385157
 0.7192486 -.0350343
 0.7418586 -.0313214
 0.7755743 -.0262900
 0.7957643 -.0235871
 0.8177829 -.0209357
 0.8381357 -.0187900
 0.8609457 -.0167443
 0.8846300 -.0150700
 0.9127500 -.0137843
 0.9383243 -.0133900
 0.9598229 -.0137814
 0.9793386 -.0157214
 0.9912757 -.0180571
 0.9966357 -.0195957
 1.0000000 -.0208643
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Polars for GRUMMAN K-3 AIRFOIL (k3-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   k3-il50,000924.9 at α=6.25°Mach=0 Ncrit=9Xfoil predictionDetails
   k3-il50,000523 at α=7.75°Mach=0 Ncrit=5Xfoil predictionDetails
   k3-il100,000930.1 at α=6.75°Mach=0 Ncrit=9Xfoil predictionDetails
   k3-il100,000533.3 at α=3.25°Mach=0 Ncrit=5Xfoil predictionDetails
   k3-il200,000949.2 at α=2.75°Mach=0 Ncrit=9Xfoil predictionDetails
   k3-il200,000550.1 at α=1.75°Mach=0 Ncrit=5Xfoil predictionDetails
   k3-il500,000979.4 at α=1.5°Mach=0 Ncrit=9Xfoil predictionDetails
   k3-il500,000565.9 at α=0.25°Mach=0 Ncrit=5Xfoil predictionDetails
   k3-il1,000,000994.2 at α=0.5°Mach=0 Ncrit=9Xfoil predictionDetails
   k3-il1,000,000570.2 at α=5°Mach=0 Ncrit=5Xfoil predictionDetails
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