Accession Number:

ADA171075

Title:

Canard/Tail Transonic Analysis.

Descriptive Note:

Final technical rept. Jun 81-Jun 85,

Corporate Author:

GRUMMAN AEROSPACE CORP BETHPAGE NY

Personal Author(s):

• Aidala,P.

Report Date:

1985-10-01

Pagination or Media Count:

123.0

Abstract:

The theoretical and operational characteristics of the CANTATA code are described. The code provides 3 D transonic analysis of wing-body-canard or wing-body-tail configurations. The relative placement of the two lifting surfaces is arbitrary. The potential flow solution of the code uses a new ADI algorithm, AF2YZ. The algorithm is a three step procedure which uses a split streamwise operator, with a simple factorization of the cross-plane terms. The analysis includes the ability to allow the vortex sheets from the lifting surfaces to move under the influence of the local velocity. Wake rollup is modeled by merging vortex lines such that a single-valued spanwise shape is maintained. Viscous effects are included through the use of a strip boundary layer method. The overall code includes a numerical optimization routine that can be used to alter the lifting surface geometry in an automated design procedure.

Descriptors:

• *WING BODY CONFIGURATIONS
• *TAILS(AIRCRAFT)
• *TRANSONIC CHARACTERISTICS
• *CANARD CONFIGURATIONS
• SHOCK WAVES
• COMPUTER PROGRAMMING
• VORTICES
• WAKE
• VISCOUS FLOW
• BOUNDARY LAYER FLOW
• THREE DIMENSIONAL FLOW

Subject Categories:

• Aircraft
• Computer Programming and Software
• Fluid Mechanics

Distribution Statement:

APPROVED FOR PUBLIC RELEASE