F-15 8.33-Percent Model Internozzle Dynamic Pressure Environment

Abstract

The F-15 Strategic Programs Office (ASD/TAF) requested the Structural Vibration and Acoustics Branch to record and analyze data from a wind tunnel test on an 8.33-percent model F-15 aircraft. The objective was to assess the effect various model configurations had on the aeroacoustic loads around the aft nozzle region.

Keywords

WIND TUNNEL
STRUCTURAL VIBRATION
TUNNEL TEST
ANALYZE DATA
PERCENT MODEL
PROGRAMS OFFICE
AFT NOZZLE

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