Publication Date:
2019-07-12
Description:
Computational Fluid Dynamic studies of a rigid parawing at Mach numbers from 0.8 to 4.65 were carried out using three established inviscid, viscous and independent panel method codes. Pressure distributions along four chordwise sections of the wing were compared to experimental wind tunnel data gathered from NASA technical reports. Results show good prediction of the overall trends and magnitudes of the pressure distributions for the inviscid and viscous solvers. Pressure results for the panel method code diverge from test data at large angles of attack due to shock interaction phenomena. Trends in the flow behavior and their effect on the integrated force and moments on this type of wing are examined in detail using the inviscid CFD code results.
Keywords:
Computer Programming and Software; Fluid Mechanics and Thermodynamics; Aircraft Design, Testing and Performance
Type:
NASA/TM-2014-218300
,
ARC-E-DAA-TN14829
Format:
application/pdf
Permalink
