Accession Number:
ADA093739
Title:
Interference on a Model Afterbody from Downstream Support Hardware at Transonic Mach Numbers
Descriptive Note:
Final rept. 27 Jun-2 Jul 1979
Corporate Author:
ARO INC ARNOLD AFS TN
Personal Author(s):
Report Date:
1981-01-01
Pagination or Media Count:
51.0
Abstract:
An experimental program was conducted to parametrically study the interference on an afterbody model that would be produced by the aft-support blade used with a wingtip support system. Geometric variables included the blade axial location, thickness, span, chord, and leading- and trailing-edge contours. Data were obtained over the Mach number range from 0.6 to 1.2 with the model at zero angle of attack. Interference was evaluated by comparing afterbody drag from a reference configuration, which had the aft-support blade removed, to the various configurations with a blade installed. A reasonable correlation of the blade interference effects on the afterbody drag coefficient was obtained, which included the influence of support blade axial position and blockage. Decreasing blade leading-edge bluntness by a factor of two resulted in a significant reduction of interference in the Mach number range from 0.9 to 1.1. Significantly greater interference was measured without jet flow than with jet flow. It is shown that a Euler equation computer code is a useful tool for the design of minimum interference support systems.
Descriptors:
- *BLADES
- *BOATTAIL AFTERBODIES
- *DRAG
- *WING TIPS
- AERODYNAMIC CONFIGURATIONS
- CONTOURS
- EQUATIONS
- FIGHTER AIRCRAFT
- INTERFERENCE
- LEADING EDGES
- MACH NUMBER
- MATHEMATICAL ANALYSIS
- MEASUREMENT
- MODELS
- NOZZLE GAS FLOW
- PLUMES
- PRESSURE TRANSDUCERS
- SIMULATION
- STATIC PRESSURE
- SUPPORTS
- TRAILING EDGES
- TRANSONIC WIND TUNNELS
- WIND TUNNEL TESTS
Subject Categories:
- Aerodynamics
- Attack and Fighter Aircraft