Computational Aerodynamics with Icing Effects
Abstract
A quick, inexpensive technique has been developed for the analysis of a full aircraft configuration with iced surfaces. A comprehensive literature search of icing analysis methods is presented. Viscous effects for the flow field about an airfoil with an iced leading edge are accounted for in a thin- layer Navier-Stokes code (ARC2D). A panel code (PMARC) solves the flow field away from the body. The results of the airfoil analysis represent the near-field solutions and are used to modify the boundary conditions in the three- dimensional calculations with the panel code by matching the local circulation. This process is repeated until the total lift coefficient between successive iterations differs by less than a specified value. Comparison with viscous experimental data shows excellent results for lift coefficient and a strong improvement over the basic PMARC for drag and pitching moment coefficients. For the full configuration considered, with ice simulated on the horizontal tail, pitching moment data predicts a very sudden unstable pitch break above angle of attack = 8 deg. This tendency models the pitch tendency described in the literature for a similar configurations with an iced horizontal tail. Thus, a quick method has been developed to handle a full configuration with viscous effects.
Document Details
- Document Type
- Technical Report
- Publication Date
- May 01, 1993
- Accession Number
- ADA267509
Entities
People
- Thomas N. Mouch
Organizations
- Air Force Institute of Technology