Search NASA⌕ Search

Engineering topics

Lee, D. J.

Publications and source records attributed to Lee, D. J..

7 records
All sourcesNASA NTRSDOE OSTI
NASA NTRS1995

Psychosocial correlates of immune responsiveness and illness episodes in US Air Force Academy cadets undergoing basic cadet training

This study examined psychosocial correlates of immune function and illness in 89 male first-year US Air Force Academy cadets. A psychosocial questionnaire was administered to cadets prior to their arrival at the academy and was readministered during cadet orientation and during the stressful environment of Basic Cadet Training (BCT). Immune responsiveness was analyzed by PHA-, PMA-, or anti-CD3-stimulated thymidine uptake in mononuclear leucocytes. Illness episodes were assessed via medical chart review and self-reported symptoms. There were significant increases in distress levels as cadets entered BCT. No psychosocial measure assessed prior to arrival at the academy predicted level of PHA-, PMA-, and anti-CD3-stimulated thymidine uptake or risk of illness. However, hostility levels reported during BCT predicted risk of illness in the four weeks following psychosocial assessment (odds ratio = 7.1; 95% confidence interval: 1.4-36.1). Elevated response to environmental stressors and lower well-being levels also predicted impending illness, but only in the cohort of cadets who had not contracted food poisoning prior to assessment during BCT (OR = 9.3, CI = 1.9-46.7; OR = 0.09, CI = 0.02-0.53). These results suggest that self-report measures of hostility, response to environmental stressors and well-being may be useful predictors of impending illness episodes in males encountering high stress environments.

NASA Discipline Regulatory Physiology↗
NASA NTRS1988

Surface pressure fluctuations due to impinging vortical flows upon an airfoil

A vortical flow impinging upon an airfoil is studied for the case of a strong vortical flow passing close by the airfoil leading and trailing edge. The vortical flow, having a nonuniform vorticity distribution in the core, is distorted and splits as it nears the leading edge of the airfoil. Significant pressure fluctuation occurs near the leading edge, which becomes a source of noise and vibration. A vortex method and a panel method are used to calculate the highly nonlinear, unsteady and rotational flow during the interaction. The flow is assumed to be two dimensional, incompressible and inviscid. The nonuniform vorticity in the vortex core is represented by multiple, discrete vortex elements whose strengths are variable depending on the initial velocity profile. Detailed surface pressure and vortex velocity vectors are calculated. The surface pressure is decomposed into quasi-steady and unsteady pressure, sometimes called 'impulsive pressure'. The first time derivative of the pressure related the strength of the noise, and its r.m.s. values are also calculated.

Lee, D. J.↗
NASA NTRS1985

An analysis of blade vortex interaction aerodynamics and acoustics

The impulsive noise associated with helicopter flight due to Blade-Vortex Interaction, sometimes called blade slap is analyzed especially for the case of a close encounter of the blade-tip vortex with a following blade. Three parts of the phenomena are considered: the tip-vortex structure generated by the rotating blade, the unsteady pressure produced on the following blade during the interaction, and the acoustic radiation due to the unsteady pressure field. To simplify the problem, the analysis was confined to the situation where the vortex is aligned parallel to the blade span in which case the maximum acoustic pressure results. Acoustic radiation due to the interaction is analyzed in space-fixed coordinates and in the time domain with the unsteady pressure on the blade surface as the source of chordwise compact, but spanwise non-compact radiation. Maximum acoustic pressure is related to the vortex core size and Reynolds number which are in turn functions of the blade-tip aerodynamic parameters. Finally noise reduction and performance are considered.

Lee, D. J.↗
NASA NTRS1985

Interaction of a turbulent vortex with a lifting surface

The impulsive noise due to blade-vortex-interaction is analyzing in the time domain for the extreme case when the blade cuts through the center of the vortex core with the assumptions of no distortion of the vortex path or of the vortex core. An analytical turbulent vortex core model, described in terms of the tip aerodynamic parameters, is used and its effects on the unsteady loading and maximum acoustic pressure during the interaction are determined.

Lee, D. J.↗
NASA NTRS1984

Studies in a transonic rotor aerodynamics and noise facility

The design, construction and testing of a transonic rotor aerodynamics and noise facility was undertaken, using a rotating arm blade element support technique. This approach provides a research capability intermediate between that of a stationary element in a moving flow and that of a complete rotating blade system, and permits the acoustic properties of blade tip elements to be studied in isolation. This approach is an inexpensive means of obtaining data at high subsonic and transonic tip speeds on the effect of variations in tip geometry. The facility may be suitable for research on broad band noise and discrete noise in addition to high-speed noise. Initial tests were conducted over the Mach number range 0.3 to 0.93 and confirmed the adequacy of the acoustic treatment used in the facility to avoid reflection from the enclosure.

Wright, S. E.↗