Title

Investigation of High-Angle-of-Attack Maneuver-Limiting Factors Part II. Piloted Simulation Assessment of Bihrle Departure Criteria

Date

1980

Index Abstract

Coming Soon

Photo Quality

Not Needed

Report Number

AFWAL TR 80-3141 Part 2

Creator

Mitchell, David G.

Johnston, Donald E.

Corporate Author

Systems Technology, Inc.

Laboratory

Flight Dynamics Laboratory

Extent

50

Identifier

ADA101647

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 L alpha, N alpha, and M 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

Subject

Mathematical Models

Aircraft

Performance (Engineering)

Jet Fighters

Recovery

Transfer Functions

Equations of Motion

Parameters

Matrices (Mathematics)

Deflection

Angle of Attack

Low Velocity

Stalling

Nonlinear Systems

Mathematical Prediction

Aerodynamic Characteristics

Sideslip

Closed Loop Systems