Wind-tunnel investigation of a flush airdata system at Mach numbers from 0.7 to 1.4

摘要: Flush pressure orifices installed on the nose section of a 1/7-scale model F-14 airplane were evaluated for use as flush airdata system (FADS). Wing-tunnel tests conducted in 11- by 11-ft Unitary Wind Tunnel at NASA Ames Research Center. A full-scale FADS same configuration was previously tested using an aircraft Dryden Flight Facility Center (Ames-Dryden). These tests, which published, are part program to assess accuracies aircraft. The test also provides data validate algorithms shuttle entry developed Langley wind-tunnel Mach numbers 0.73, 0.90, 1.05, 1.20, and 1.39. Angles attack varied 2 deg increments from -4 20 deg. Sideslip angles 4 -8 8 Airdata parameters determination free-stream values stagnation pressure, static angle attack, sideslip, number. are, most cases, investigated flight program. basic presented tabular form. discussion more accurate is included.