Flight-Tests Measurements of Aileron Control Surface Behaviour at Supercritical Mach Numbers

reportActive / Technical Report | Accession Number: ADA800562 | Open PDF

Abstract:

Aileron upfloat occurring at critical Mach because of loss of pressure recovery on upper surface aft of shock wave causes large increases in aileron hinge moment. Pressure distribution data showed critical effect of Mach number on hinge-moment magnitude. Aileron oscillations encountered ranging from mild buzz to motion causing aileron deformation showed agreement with wind-tunnel test results on partial span wing section. Spasmodic low-amplitude buzz warns of more severe oscillations at higher Mach.

Author(s):
Brown, Harvery H. ; Rathert, Jr., George A. ; Clousing, Lawrence A.
Author Organization(s):
NATIONAL AERONAUTICS AND SPACE ADMINISTRATION MOFFETT FIELD CA AMES RESEARCH CENTER
Descriptive Note:
Research memo.
Supplementary Note:
National Aeronautics and Space Administration, Washington, DC
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):
NACA-RM-A7A15
 Subject Terms
Joint Capability Areas:
JCA_6_Net Centric; JCA_3.2_Engagement; JCA_3_Force Application; JCA_3.2.1_Kinetic Means; JCA_6.1.1_Wired Transmission; JCA_5_Command and Control; JCA_6.1.2_Wireless Transmission; JCA_6.1_Information Transport
Modernization Areas:
Directed Energy
Communities of Interest:
No COI(s) Identified
Descriptor(s):
*AILERONS, PRESSURE DISTRIBUTION
Keyword(s):
ATI 005968, ATI COLLECTION
Report Date:
1947 Apr 01
Creation Date:
2009 Jun 03