columbus · Static Aerodynamic Characteristics at Mach 5 and 8 of an Aerodynamically Controllable Winged Re-Entry Configuration. Part of an Investigation of Hypersonic Flow Separation and Control Characteristics

Static Aerodynamic Characteristics at Mach 5 and 8 of an Aerodynamically Controllable Winged Re-Entry Configuration. Part of an Investigation of Hypersonic Flow Separation and Control Characteristics

Item

Title: Static Aerodynamic Characteristics at Mach 5 and 8 of an Aerodynamically Controllable Winged Re-Entry Configuration. Part of an Investigation of Hypersonic Flow Separation and Control Characteristics
Date: 1963
Index Abstract: Coming Soon
Photo Quality: Complete
Report Number: FDL TDR 64-10
Corporate Author: Grumman Aircraft Engineering Corporation
Laboratory: AF Flight Dynamics Laboratory
Extent: 146
Identifier: AD0608304
Access Rights: OTS
Distribution Classification: 1
Contract: AF33(616)-8130
DoD Project: 8219
DoD Task: 821902
DTIC Record Exists: No
Distribution Change Authority Correspondence: None
Abstract: Six-component aerodynamic data were obtained at Mach 5 and 8 for a winged re-entry configuration having aerodynamic controls. The basic model consisted of a clipped delta wing with an over-slung body. The main controls tested were a deflected apex and partial-span trailing-edge flaps. Data were also obtained on the effect of tip fins, full-span trailing-edge flap, and trailing-edge spoiler. At Mach number 5 the data were obtained over an angle of attack range from -30 degrees to +45 degrees at a unit Reynolds number of 2.26 x 10 to the 6th power. At Mach number 8 the angle of attack range was -54 degrees to +54 degrees at the same unit Reynolds number.
Report Availability: Full text available
Date Issued: 1963-09
Provenance: Lockheed Martin Missiles & Fire Control
Type: report
Format: 1 online resource
Creator: Meckler, Lawrence

Media: FDLTDR64-010.pdf