The Langley 8-foot transonic pressure tunnel was used in an effort to determine the effects of humidity at near-sonic speed on the longitudinal aerodynamic characteristics and wing pressure distributions of an area-rule research airplane model with an NASA supercritical wing. Effects of dewpoint at the normal tunnel operating stagnation temperature of 48.9 C (120 F) and effects of stagnation temperature at a relatively high dewpoint of 15.6 C (60 F) were investigated. The test tunnel stagnation pressure was 101 325 N/sq m (1 atmosphere).
Investigation at Near-Sonic Speed of Some Effects of Humidity on the Longitudinal Aerodynamic Characteristics of an NASA Supercritical Wing Research Airplane Model
1972
71 pages
Report
Keine Angabe
Englisch