A Reynolds-average Navier Stokes method developed for rotorcraft type of flow problems is applied for predicting the forces and moments of forebody models at high-angle-of-attack dynamic conditions and for providing insight into the flow characteristics at these conditions. Wind-tunnel results from rotary testing on generic forebody models conducted by NASA Langley and DERA are used for comparison. This paper focuses on the steady-state flow problem. The stability and control at post-stall maneuvering flight conditions are of major concern in the design of advanced agile airplanes. At these flight conditions the flows about this type of aircraft tend to be unsteady and the aerodynamic forces and moments show strong nonlinear variations with rotation rates. During the development process of these airplanes, numerous hours are spent testing scaled models in ground facilities with complex special purpose equipment to determine the dynamic stability and control characteristics. Much of this testing is conducted using sub-scale models of simplified geometry at low Reynolds numbers.
Prediction of Flows about Forebodies at High-Angle-of-Attack Dynamic Conditions
2004
20 pages
Report
No indication
English
Aerodynamics , Fluid Mechanics , Algebra, Analysis, Geometry, & Mathematical Logic , Steady state , Angle of attack , Aerodynamic forces , Computational fluid dynamics , Rotary wing aircraft , High angles , Computerized simulation , Experimental data , Stability , Flow visualization , Flow separation , Wind tunnel tests , Mathematical prediciton , Navier Stokes equation , Reynolds number
British Library Online Contents | 1992
|Sideslip Behavior of Elliptic Cross-Sectional Forebodies at High Angle of Attack
Online Contents | 1997
|Simulation of Flow About Rotating Forebodies at High Angles of Attack
Online Contents | 2004
|