Title

Validation of USAF Stability and Control Datcom Methodologies for Straight-Tapered Sweptforward Wings

Date

1985

Index Abstract

Coming Soon

Photo Quality

Not Needed

Report Number

AFWAL TR 84-3084

Corporate Author

Design Prediction Group

Laboratory

Flight Dynamics Laboratory

Date Issued

1985-07-01

Extent

210

Identifier

ADA161876

Access Rights

Approved for public release; distribution unlimited

Distribution Classification

1

Contract

Laboratory Research - No Contract

DoD Project

2403

DoD Task

240305

DTIC Record Exists

No

Distribution Change Authority Correspondence

None

Abstract

A detailed review of USAF Stability and Control Datcom methodologies was conducted to determine their validity for application to straight tapered, sweptforward wing configurations. To the extent possible the format found in the Datcom is repeated in this report. Several methods were modified to enable more accurate coefficient prediction (e.g., Wing Zero-Lift Angle of Attack, Downwash and Yawing Moment due to Yaw Rate) irrespective of sweep sign. At supersonic speeds, the reversibility theorem enabled most methodologies to be used without any modifications to account for sweptforward leading-edge designs. For the methodologies validated, sweptforward-wing estimation results were generally as accurate as the sweptback-wing results presented in the Datcom. Unfortunately, lack of test data prevented validation of several empirical methodologies (e.g., Subsonic High Angle-of-Attack Pitching Moment and Transonic Pitching Moment). No estimation methodologies are proposed in these cases.

Report Availability

Full text available

Provenance

AFRL/VACA

Type

report

Format

1 online resource

Subject

Sweptforward Wings

Mathematical Models

Methodology

Experimental Data

Yaw

Predictions

Validation

Aerodynamic Stability

Rates

Moments

Angle of Attack

Estimates

Coefficients

Leading Edges

Taper

Supersonic Characteristics

Wing Body Configurations

Aerodynamic Lift

Downwash

Creator

Sharpes, Daniel G.