THE AERODYNAMIC CHARACTERISTICS OF A 75-DEG SWEPT DELTA WING AT HIGH ANGLES OF ATTACK AND MACH NUMBERS OF 2 TO 8 (U)

reportActive / Technical Report | Accession Number: AD0329345 | Open PDF

Abstract:

An experimental investigation was conducted in a 12 in. supersonic tunnel and a 50 in. Mach 8 tunnel to determine the aerodynamic characteristics of a delta wing at high angles of attack. The configuration tested was a flat, blunt leading edge, delta wing with 75 degree sweepback. The tests were conducted at angles of attack from 30 to 105 degree and Mach numbers of 2, 3, 5, and 8. Longitudinal stability and drag characteristics, surface pressure distributions, and shock wave shapes are presented with theoretical estimates based on the Newtonian theory.

Author(s):
Clark, E. L. ; Spurlin, C. J.
Author Organization(s):
ARO INC ARNOLD AFS TN
Supplementary Note:
DOI: 10.21236/AD0329345
Pagination:
0036

Security Markings

DOCUMENT & CONTEXTUAL SUMMARY

Distribution:
Approved For Public Release
Distribution Statement:
Approved For Public Release; Distribution Is Unlimited.

RECORD

Collection: TR
Identifying Numbers
Report Number(s):
AEDC-TDR-62-99
Contract/Grant Number(s):
AF 40(600)-800
Monitor Series:
TDR-62-99, AEDC
 Subject Terms
Joint Capability Areas:
JCA_3_Force Application; JCA_3.1.1_Maneuver to Engage; JCA_3.1_Maneuver; JCA_3.2_Engagement; JCA_3.2.1_Kinetic Means; JCA_4.6_Engineering
Modernization Areas:
Hypersonics
Communities of Interest:
No COI(s) Identified
Descriptor(s):
*DELTA WINGS, *SWEPTBACK WINGS, LOAD DISTRIBUTION, PITCH(MOTION), SHOCK WAVES, MODEL TESTS, PRESSURE, PITCH(MATERIAL), WIND TUNNEL MODELS, AERODYNAMIC CHARACTERISTICS, SUPERSONIC FLOW, HYPERSONIC CHARACTERISTICS, DRAG
Field(s)/Group(s):
Fluid Mechanics
Report Date:
1962 May 01