columbus · Investigation of Flow Separation on a Two-Dimensional Flat Plate Having a Variable-Span Trailing-Edge Flap at M = 3 and 5

Investigation of Flow Separation on a Two-Dimensional Flat Plate Having a Variable-Span Trailing-Edge Flap at M = 3 and 5

Title: Investigation of Flow Separation on a Two-Dimensional Flat Plate Having a Variable-Span Trailing-Edge Flap at M = 3 and 5
Date: 1964
Index Abstract: Coming Soon
Photo Quality: Incomplete
Report Number: AEDC TDR 64-14
Creator: Pate, S. R.
Corporate Author: ARO, Inc.
Extent: 34
Identifier: AD0432831
Distribution Classification: 1
Contract: AF 40(600)-1000
DoD Project: None Given
DoD Task: None Given
DTIC Record Exists: Yes
Distribution Change Authority Correspondence: None
Abstract: An experimental investigation of separated boundary-layer flow was conducted on a two-dimensional flat plate having a variable-span trailingedge flap in the 12-in. Supersonic Tunnel (D) of the von Karman Gas Dynamics Facility. The tests were made at Mach numers 3 and 5 at zero angle of attack and over a Reynolds number range (based on plate length) from 0.26 to 16.7 x 10 to the 6th power. Model surface pressure distributions, schlieren photographs, and velocity distributions are presented. The effects of unit Reynolds number, plate length, flap span, and flap deflection angle on the separated region are investigated, and comparisons are made with existing theory.
Report Availability: Full text available by request
Date Issued: 1964-03
Publisher: Arnold Air Force Station, TN : Arnold Engineering Development Center, Air Force Systems Command, United States Air Force
Provenance: IIT
Type: report
Format: 34 pages ; 28 cm.