Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

LOCKHEED C-141 BL610.61 AIRFOIL (c141d-il)

LOCKHEED C-141 BL610.61 AIRFOIL - Lockheed-Georgia C-141 transonic wing airfoils


Airfoil c141d-il
Details Dat file Parser  
(c141d-il) LOCKHEED C-141 BL610.61 AIRFOIL
Lockheed-Georgia C-141 transonic wing airfoils
Max thickness 10.8% at 40.2% chord.
Max camber 1.5% at 50% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
 LOCKHEED C-141 BL610.61 AIRFOIL
      33.0      33.0

 0.0000000 0.0000000
 0.0024080 0.0096720
 0.0096070 0.0176760
 0.0215300 0.0252210
 0.0380600 0.0322090
 0.0590400 0.0383290
 0.0842660 0.0437950
 0.1134950 0.0489290
 0.1464470 0.0535590
 0.1828040 0.0575740
 0.2222160 0.0610910
 0.2643030 0.0640580
 0.3086600 0.0663510
 0.3548590 0.0679610
 0.4024560 0.0688110
 0.4509930 0.0687390
 0.5000000 0.0677260
 0.5490110 0.0657640
 0.5975470 0.0629294
 0.6451440 0.0592500
 0.6913440 0.0548290
 0.7357000 0.0497900
 0.7777870 0.0442130
 0.8171990 0.0381870
 0.8535550 0.0321210
 0.8865070 0.0261360
 0.9157360 0.0202000
 0.9409620 0.0147810
 0.9619410 0.0099140
 0.9784710 0.0060800
 0.9903930 0.0033140
 0.9975930 0.0016490
 1.0000000 0.0010940

 0.0000000 0.0000000
 0.0024080 -.0085370
 0.0096070 -.0147070
 0.0215300 -.0200530
 0.0380600 -.0242830
 0.0590400 -.0276540
 0.0842660 -.0301000
 0.1134950 -.0324940
 0.1464470 -.0343300
 0.1828040 -.0359520
 0.2222160 -.0372210
 0.2643030 -.0381940
 0.3086600 -.0388130
 0.3548590 -.0390560
 0.4024560 -.0388470
 0.4509930 -.0380940
 0.5000000 -.0368320
 0.5490110 -.0350760
 0.5975470 -.0327420
 0.6451440 -.0300650
 0.6913440 -.0270740
 0.7357000 -.0239530
 0.7777870 -.0208780
 0.8171990 -.0179150
 0.8535550 -.0149510
 0.8865070 -.0120500
 0.9157360 -.0093340
 0.9409620 -.0069160
 0.9619410 -.0048570
 0.9784710 -.0031900
 0.9903930 -.0020200
 0.9975930 -.0013240
 1.0000000 -.0010940
No parser warnings Send to airfoil plotter
Add to comparison
Lednicer format dat file
Selig format dat file

Similar airfoils

LOCKHEED C-141 BL426.57 AIRFOILPreviewDetails
LOCKHEED C-141 BL761.11 AIRFOILPreviewDetails
NACA 0010-34 a=0.8 c(li)=0.2PreviewDetails
NACA 64A210PreviewDetails
S8065 (11% version of S8064)PreviewDetails
MH 26 10.99%PreviewDetails
NACA 64-210PreviewDetails
NACA 65-210PreviewDetails
HQ 1.5/11 AIRFOILPreviewDetails
BOEING-VERTOL VR-1 AIRFOILPreviewDetails

Polars for LOCKHEED C-141 BL610.61 AIRFOIL (c141d-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   c141d-il50,000931.5 at α=5.25°Mach=0 Ncrit=9Xfoil predictionDetails
   c141d-il50,000530.9 at α=5°Mach=0 Ncrit=5Xfoil predictionDetails
   c141d-il100,000947.2 at α=4.5°Mach=0 Ncrit=9Xfoil predictionDetails
   c141d-il100,000544.5 at α=4°Mach=0 Ncrit=5Xfoil predictionDetails
   c141d-il200,000967 at α=3.75°Mach=0 Ncrit=9Xfoil predictionDetails
   c141d-il200,000557.5 at α=2.75°Mach=0 Ncrit=5Xfoil predictionDetails
   c141d-il500,000982.4 at α=2.75°Mach=0 Ncrit=9Xfoil predictionDetails
   c141d-il500,000565.1 at α=7.25°Mach=0 Ncrit=5Xfoil predictionDetails
   c141d-il1,000,000983.6 at α=2.25°Mach=0 Ncrit=9Xfoil predictionDetails
   c141d-il1,000,000579.3 at α=7.25°Mach=0 Ncrit=5Xfoil predictionDetails
Reynolds number calculator
Set Reynolds number and Ncrit rangeLowHigh
Reynolds Number
NCrit