Airfoil Optimization through the Adaptive Control of Camber and Thickness. Phase II: Transonic Wind Tunnel Test and Program Summary.

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Abstract:

A new interactive wind tunnel technique for optimizing airfoil shape has been demonstrated satisfactorily under both low speed and transonic flow conditions. The transonic program reported herein, was conducted in the two-dimensional section of the General Dynamics High Speed Tunnel GDHST of blow-down type at a nominal Mach number of 0.75. The program utilized a flexible airfoil model whose shape could be conformally varied during a run of approximately one minute duration by means of five pair of hydraulic actuators. The airfoil shape and angle of attack were controlled by a link-up of three analog and digital computers which analyzed the wind tunnel balance data on-line and adjusted the airfoil shape and angle of attack to optimize a given merit function.

Author(s):
Levinsky, E. S. ; Schappelle, R. H. ; Pountney, S.
Author Organization(s):
GENERAL DYNAMICS SAN DIEGO CALIF CONVAIR AEROSPACE DIV
Descriptive Note:
Final technical rept. 15 Dec 73-30 Sep 75,
Pagination:
0122

Security Markings

DOCUMENT & CONTEXTUAL SUMMARY

Distribution:
Approved For Public Release

RECORD

Collection: TR
Identifying Numbers
Report Number(s):
CASD-NSC-75-004
Contract/Grant Number(s):
N00014-74-C-0127
Project Number(s):
NR-212-224
 Subject Terms
Communities of Interest:
No COI(s) Identified
Descriptor(s):
*ADAPTIVE CONTROL SYSTEMS, *AIRFOILS, *COMPUTER APPLICATIONS, *TRANSONIC FLOW, COMPUTER PROGRAMS, DATA PROCESSING, THICKNESS, OPTIMIZATION, SHAPE, ANGLE OF ATTACK, WIND TUNNEL TESTS, DATA ACQUISITION, DIGITAL COMPUTERS, WIND TUNNEL MODELS, ANALOG COMPUTERS, HYDRAULIC ACTUATORS
Field(s)/Group(s):
Aircraft, Computer Programming and Software, Computer Hardware, Fluid Mechanics
Keyword(s):
Variable camber
Report Date:
1975 Sep 01