Accession Number:

ADA429430

Title:

Flow Control Enabled Aircraft Design

Descriptive Note:

Final rept. 1 Aug 2002-1 Feb 2005

Corporate Author:

NANGIA AERO RESEARCH ASSOCIATES BRISTOL(UNITED KINGDOM)

Personal Author(s):

Report Date:

2004-07-01

Pagination or Media Count:

236.0

Abstract:

This report results from a contract tasking Nangia Aero Research Associates as follows Many future advanced aircraft concepts being considered by the Air Force fall outside the current aerodynamic design practice and will rely heavily on the use of flow control technology to optimize flight performance. Examples include SensorCraft, long range strike aircraft, ultra STOL transports, and hypersonic aircraft. To properly design and optimize the aerodynamic performance of these vehicle concepts high fidelity models and well-documented baseline configurations are desired. The key science issue is determining the correct mixture of passive shaping and active flow control in novel design situations, subject to the usual engineering constraints. Specific Work to be Accomplished The contractor will refine and employ high fidelity analytical models to assess vehicle performance for a generic sensor craft and supersonic strike aircraft. Sensitivities to wing configurations, high aspect ratio wings, wing junctions, wing tip configurations, scaling effects, wing geometry, inlet geometry, and flight Mach and altitude will be assessed. Numerical methods include previously developed and largely validated direct and inverse procedures, codes for subsonic, transonic and supersonic flows. The aim will be to assess active and passive flow control techniques and their relative merits.

Subject Categories:

  • Aerodynamics
  • Aircraft

Distribution Statement:

APPROVED FOR PUBLIC RELEASE