Minimum control airspeed testing of the F/A-18 E/F airplane

Author

Henry Melton III

Date of Award

8-2001

Degree Type

Thesis

Degree Name

Master of Science

Major

Aviation Systems

Major Professor

R. B. Richards

Committee Members

Ralph D. Kimberlin, U. Peter Solies

Abstract

The minimum control airspeed for an airplane has been classically defined based upon theory and methodology applicable to multi-engine, propeller-driven and low thrust-to-weight engine airplanes. This testing has traditionally been performed assuming aerodynamic characteristics remain constant throughout the test angle of attack (AOA) range, and controllability was primarily a function of dynamic pressure. For these airplanes, thrust level, thrust degradation and the interdependencies with the single engine minimum control airspeed were simple to flight test and analyze, as the results could be linearly extrapolated to a reference, sea level, standard day, condition. These extrapolations to reference conditions are critical to shipboard operations as these airspeeds are used as a basis to establish minimum catapult takeoff airspeeds during shipboard operations. Once established, safety margins over-and-above these airspeeds are applied to ensure controllability of the airplane is maintained in the event of a catastrophic engine failure during the critical catapult takeoff flight phase. For the modern high thrust-to-weight fighter airplane, V_mcA is largely dependent on atmospheric conditions and the classical test techniques are no longer valid and are unsafe. During the F/A-18 E/F Engineering and Manufacturing Development (EMD) program, flight test results revealed additional V_mcA dependencies on AOA, and lateral weight asymmetry. As a result, the test techniques and analysis of the results were significantly more complex to analyze. This thesis discusses the methodology used to establish and normalize the single engine minimum control airspeed flight test data for the F/A-18 E/F airplane, carrier environment, shipboard launching process, and the flight test demonstration requirements for airplanes which are catapult launched from ships. These discussions also include operational considerations, which must be made relative to operating in the shipboard environment.

Recommended Citation

Melton III, Henry, "Minimum control airspeed testing of the F/A-18 E/F airplane. " Master's Thesis, University of Tennessee, 2001.
https://trace.tennessee.edu/utk_gradthes/9681