Flow Field Measurements Around an Ogive-Cylinder at Angles of Attack up to 15 Degrees for Mach Numbers 3.5 and 4

Ragsdale, William C.

Flow Field Measurements Around an Ogive-Cylinder at Angles of Attack up to 15 Degrees for Mach Numbers 3.5 and 4

Active / Technical Report | Accession Number: AD0752025 |

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Abstract:

The flow field was surveyed at one station XD 6.5 on an ogive- cylinder having a tangent ogive nose with a fineness ratio of 4. The surveys were performed with pitot tubes and cone pressure probes at angles of attack of 0, 5, 10 and 15 degrees for Mach numbers 3.52 and 4.07. Surface static pressures were also measured. The results of the tests are presented in tabular and plotted form. Comparisons are made with inviscid flow fields calculations and with experimental results from other investigations.

Author(s):

Ragsdale, William C.

Author Organization(s):

NAVAL ORDNANCE LAB WHITE OAK MD

Pagination:

0129

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):

NOLTR-72-198

Project Number(s):

A310-310A/WR02-403-001

Monitor Series:

NOL

Subject Terms

Joint Capability Areas:

JCA_3.2_Engagement; JCA_3_Force Application; JCA_3.2.1_Kinetic Means; JCA_6_Net Centric; JCA_6.2.1_Information Sharing; JCA_6.2.2_Computing Services; JCA_6.4.1_Secure Information Exchange; JCA_5_Command and Control

Modernization Areas:

Hypersonics

Communities of Interest:

Air Platforms

Descriptor(s):

*HYPERVELOCITY PROJECTILES, TEST METHODS, ANGLE OF ATTACK, FLOW VISUALIZATION, FLOW FIELDS, CYLINDRICAL BODIES, PRESSURE, SUPERSONIC CHARACTERISTICS, FLOW SEPARATION, WIND TUNNEL MODELS, RAMJET INLETS, NOSE CONES

Field(s)/Group(s):

Guided Missile Dynamics, Configurations and Control Surfaces, Ammunition and Explosives

Keyword(s):

STATIC PRESSURE

Report Date:

1972 Aug 24