Title

Investigation of High-Angle-of-Attack Maneuver-Limiting Factors Part III Appendices - Aerodynamic Models

Date

1980

Index Abstract

Not Available

Photo Quality

Not Needed

Report Number

AFWAL TR 80-3141 Part 3

Creator

Mitchell, David G.

Teper, Gary L.

Johnston, Donald E

Myers, Thomas T.

Corporate Author

Systems Technology, Inc.

Laboratory

Flight Dynamics Laboratory

Extent

124

Identifier

ADA101648

Access Rights

Approved for public release; distribution unlimited

Distribution Classification

1

Contract

F33615-76-C-3072

DoD Project

2403

DoD Task

240305

DTIC Record Exists

No

Distribution Change Authority Correspondence

None

Abstract

The high-angle-of-attack, low-speed stall/departure characteristics of the F-4J and F-14A are analyzed, using a six-degree-of-freedom mathematical model with nonlinear aerodynamics. Cause-effect relationships are investigated for maneuver limiting factors including wing rock, nose slice, and rolling departures. Cross-derivatives of zeta primed sub alpha, n primed sub alpha and m sub Beta alter key transfer function parameters. A piloted simulation validates analytic predictions and demonstrates that departure warning, susceptibility, and severity are strongly influenced by the static cross-derivatives. A connection between roll numerator parameter values and pilot perception of departure susceptibility and severity is identified. Potential modifications for the high AOA sections of the MIL-F-8785B Flying Qualities Specification are proposed: a criterion for the real part of the roll numerator root, further recommendations for minimizing departure susceptibility and certain sideslip influences, and a flying quality rating form for assessing departure and recovery characteristics. Part I, Analysis and Simulation, presents a summary of the complete investigation and results. Part II, Piloted Simulation Assessment of Bihrle Departure Criteria, presents a detailed comparison of analytical prediction and piloted simulation results for a specific set of programmed control deflections. Part III, Appendices-Aerodynamic Models, contains the detailed aerodynamic models employed in the F-4J and F-14A high-angle-of-attack analysis and validation and the equations of motion, aerodynamic models, control system configurations, etc., employed in the piloted simulation.

Report Availability

Full text available

Date Issued

1980-12-01

Provenance

AFRL/VACA

Type

report

Format

1 online resource