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Effect of tail-fin span on stability and control characteristics of a Canard-controlled missile at supersonic Mach numbersAn experimental wind-tunnel investigation was conducted at Mach numbers from 1.60 to 3.50 to obtain the longitudinal and lateral-directional aerodynamic characteristics of a circular, cruciform, canard-controlled missile with variations in tail-fin span. In addition, comparisons were made with the experimental aerodynamic characteristics using three missile aeroprediction programs: MISSILE1, MISSILE2, and NSWCDM. The results of the investigation indicate that for the test Mach number range, canard roll control at low angles of attack is feasible on tail-fin configurations with tail-to-canard span ratios of less than or equal to 0.75. The conards are effective pitch and yaw control devices on each tail-fin span configuration tested. Programs MISSILE1 and MISSILE2 provide very good predictions of longitudinal aerodynamic characteristics and fair predictions of lateral-directional aerodynamic characteristics at low angles of attack, with MISSILE2 predictions generally in better agreement with test data. Program NSWCDM provides good longitudinal and lateral-directional aerodynamic predictions that improve with increases in tail-tin span.
Document ID
19830019688
Acquisition Source
Legacy CDMS
Document Type
Technical Publication (TP)
Authors
Blair, A. B., Jr. (NASA Langley Research Center Hampton, VA, United States)
Allen, J. M. (NASA Langley Research Center Hampton, VA, United States)
Hernandez, G. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 4, 2013
Publication Date
June 1, 1983
Subject Category
Aerodynamics
Report/Patent Number
L-15586
NASA-TP-2157
NAS 1.60:2157
Accession Number
83N27959
Funding Number(s)
PROJECT: RTOP 505-43-23-02
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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