A Study of Potential Test Capabilities of the NASA Langley 0.3-Meter Transonic Cryogenic Wind Tunnel

摘要

The cryogenic and high pressure capabilities of the NASA Langley 0.3-Meter Transonic Cryogenic Tunnel provide a relatively unique, small-scale, high-Reynolds number aerodynamic research facility. However, its usefulness is currently restricted by reliance on a two-dimensional adaptive wall test section coupled with an underperforming facility control system. Access to the test section is restricted, the adaptive walls can be slow to converge, and the tunnel often requires excessive time to reach a set point, particularly at low Mach numbers. As a result, productivity and operational efficiency are compromised. As part of an effort to revitalize the facility, this paper documents a study conducted into design concepts for a new transonic test section with a variable configuration and passive ventilated walls. The new test section will be adaptable so as to simulate the characteristics of a variety of existing large transonic facilities, such as the National Transonic Facility and the Transonic Dynamics Tunnel, both at NASA Langley, and the NASA Ames 11ft transonic tunnel. The ability to simulate test section conditions in a variety of other transonic facilities would provide researchers with enhanced opportunities for risk reduction, test development, and validation of fundamental flow problems such as the study of wall interference correction techniques and application of modern fluid dynamic measurement methods under high Reynolds number conditions.