Aerodynamic configuration design using response surface methodology analysisAn investigation has been conducted to determine a set of optimal design parameters for a single-stage-to-orbit reentry vehicle. Several configuration geometry parameters which had a large impact on the entry vehicle flying characteristics were selected as design variables: the fuselage fineness ratio, the nose to body length ratio, the nose camber value, the wing planform area scale factor, and the wing location. The optimal geometry parameter values were chosen using a response surface methodology (RSM) technique which allowed for a minimum dry weight configuration design that met a set of aerodynamic performance constraints on the landing speed, and on the subsonic, supersonic, and hypersonic trim and stability levels. The RSM technique utilized, specifically the central composite design method, is presented, along with the general vehicle conceptual design process. Results are presented for an optimized configuration along with several design trade cases.
Document ID
19940034063
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Engelund, Walter C. (NASA Langley Research Center Hampton, VA, United States)
Stanley, Douglas O. (NASA Langley Research Center Hampton, VA, United States)
Lepsch, Roger A. (NASA Langley Research Center Hampton, VA, United States)
Mcmillin, Mark M. (NASA Langley Research Center Hampton, VA, United States)
Unal, Resit (Old Dominion Univ. Norfolk, VA, United States)
Date Acquired
August 16, 2013
Publication Date
August 1, 1993
Subject Category
Launch Vehicles And Space Vehicles
Report/Patent Number
AIAA PAPER 93-3967Report Number: AIAA PAPER 93-3967
Meeting Information
Meeting: AIAA, Aircraft Design, Systems and Operations Meeting