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