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Preliminary subsonic aerodynamic model for simulation studies of the HL-20 lifting bodyA nonlinear, six-degree-of-freedom aerodynamic model for an early version of the HL-20 lifting body is described and compared with wind tunnel data upon which it is based. Polynomial functions describing most of the aerodynamic parameters are given and tables of these functions are presented. Techniques used to arrive at these functions are described. Basic aerodynamic coefficients were modeled as functions of angles of attack and sideslip. Vehicle lateral symmetry was assumed. Compressibility (Mach) effects were ignored. Control-surface effectiveness was assumed to vary linearly with angle of deflection and was assumed to be invariant with the angle of sideslip. Dynamic derivatives were obtained from predictive aerodynamic codes. Landing-gear and ground effects were scaled from Space Shuttle data. The model described is provided to support pilot-in-the-loop simulation studies of the HL-20. By providing the data in tabular format, the model is suitable for the data interpolation architecture of many existing engineering simulation facilities. Because of the preliminary nature of the data, however, this model is not recommended for study of the absolute performance of the HL-20.
Document ID
Acquisition Source
Legacy CDMS
Document Type
Technical Memorandum (TM)
Jackson, E. Bruce
(NASA Langley Research Center Hampton, VA, United States)
Cruz, Christopher I.
(NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 6, 2013
Publication Date
August 1, 1992
Subject Category
Aircraft Stability And Control
Report/Patent Number
NAS 1.15:4302
Accession Number
Funding Number(s)
PROJECT: RTOP 505-64-40-01
Distribution Limits
Work of the US Gov. Public Use Permitted.
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