Title

Drag Measurements of Upswept Afterbodies and Analytical Study on Axisymmetric Separation

Date

1974

Index Abstract

Not Available

Photo Quality

Complete

Report Number

AFFDL TR 73-153

Creator

Hahn, Mansop

Rubbert, Paul E.

Nark, T. C.

Brune, Gunter W.

Corporate Author

Boeing Airplane Company

Laboratory

Air Force Flight Dynamics Laboratory

Date Issued

1974-02

Extent

70

Identifier

AD0778819

Access Rights

Approved for public release; distribution is unlimited

Distribution Classification

1

Contract

F33615-73-C-3037

DoD Project

1476

DoD Task

147601

DTIC Record Exists

No

Distribution Conflict

No

Abstract

The drag of several afterbodies was measured for various upsweep angles and presented as a function of three afterbody geometric parameters. Carpet plots were used to empirically predict the afterbody drag increment. Although present test results were obtained for a single forebody configuration incorporating a low wing position and a 2 degree wing incidence angle, agreement between the present results and other available experimental data appeared to be reasonable. A theoretical approach to the problem of predicting three-dimensional separated flow was developed that allows application of the best numerical procedure for each type of flow encountered. Viscous separated flow, boundary layers, and inviscid flow are numerically matched by a procedure that is conceptually simple and economical. The method was explored for the model problem of axisymmetric laminar separated flow about an ellipsoid, and rapi convergence to an accurately matched solution including drag prediction was demonstrated. A feasibility study of applying the method to the problem of three-dimensional separation from swept wings was conducted.

Report Availability

Full text available

Provenance

Bombardier/Aero

Type

report

Format

1 online resource