Reduction Of Drag Due To Lift At Supersonic Speeds

Item

Title
Reduction Of Drag Due To Lift At Supersonic Speeds
Date
1954
Index Abstract
Coming Soon
Photo Quality
Not Needed
Report Number
WADC TR 54-524 Part 1
Creator
Graham, E. W.
Lagerstrom. P. A.
Corporate Author
Douglas Aircraft Company, Inc.
Laboratory
Aeronautical Research Laboratory
Extent
10
PB Number
PB157269
NTRL Accession Number
AD063453
Identifier
AD0063453
Access Rights
Notice(s)
Distribution Classification
1
Contract
AF 33(616)-2170
DoD Project
1366
DoD Task
70166
DTIC Record Exists
Yes
Distribution Change Authority Correspondence
AFWAL ltr,
Distribution Change Action Date
6/2/2003
Distribution Conflict
Fix
Abstract
SEVERAL TOPICS RELATING TO THE REDUCTION OF DRAG DUE TO LIFT AT SUPERSONIC SPEEDS ARE DISCUSSED. The distribution of camber for optimial loading of diamond planform wings and some low drag geometries for rectangular wings are determined. It appears that substantial drag reduction, through the use of spanwise distribution of camber, may be achieved only for low reduced aspect ratios, M2-1 AR. The distribution of lift throughout volumes of prescribed shape is considered and some optimum distributions found for certain cases. It is shown that optimum spatial distributions of lift arc generally not unique. The possibility of using biplanes is explored and it is concluded that for non-interfering biplanes (wings acting as isolated monoplanes) there is an inherent structural advantage which is the result of a scale effect for geometrically similar structures The preacnt status of means for drag reduction is surveyed and the direction for further study indicated.
Report Availability
Full text available
Date Issued
1954-04
Provenance
Lockheed Martin Missiles & Fire Control
Type
report
Format
1 online resource