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Preliminary Subsonic Aerodynamic Model for Simulation Studies of the Hl-20 Lifting Body

National Aeronautics and Space Adm Nasa
Preliminary Subsonic Aerodynamic Model for Simulation Studies of the Hl-20 Lifting Body by National Aeronautics and Space Adm Nasa PDF

Author : National Aeronautics and Space Adm Nasa
Publisher : Independently Published
Page : 68 pages
File Size : 50,60 MB
Release : 2018-11-06
Category : Science
ISBN : 9781730830952

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A 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. Jackson, E. Bruce and Cruz, Christopher I. Langley Research Center...

Preliminary Subsonic Aerodynamic Model for Simulation Studies of the Hl-20 Lifting Body

National Aeronautics and Space Administration (NASA)
Preliminary Subsonic Aerodynamic Model for Simulation Studies of the Hl-20 Lifting Body by National Aeronautics and Space Administration (NASA) PDF

Author : National Aeronautics and Space Administration (NASA)
Publisher : Createspace Independent Publishing Platform
Page : 68 pages
File Size : 44,31 MB
Release : 2018-07-10
Category :
ISBN : 9781722698430

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A 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. Jackson, E. Bruce and Cruz, Christopher I. Langley Research Center...

Subsonic Aerodynamic Characteristics of the Hl-20 Lifting-Body Configuration

National Aeronautics and Space Administration (NASA)
Subsonic Aerodynamic Characteristics of the Hl-20 Lifting-Body Configuration by National Aeronautics and Space Administration (NASA) PDF

Author : National Aeronautics and Space Administration (NASA)
Publisher : Createspace Independent Publishing Platform
Page : 32 pages
File Size : 23,52 MB
Release : 2018-07-11
Category :
ISBN : 9781722826437

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The HL-20 is proposed as a possible future manned spacecraft. The configuration consists of a low-aspect-ratio body with a flat undersurface. Three fins (a small centerline fin and two outboard (tip) fins set at a dihedral angle of 50 deg) are mounted on the aft body. The control system consists of elevon surfaces on the outboard fins, a set of four body flaps on the upper and lower aft body, and an all-movable center fin. Both the elevons and body flaps were capable of trimming the model to angles of attack from -2 deg to above 20 deg. The maximum trimmed lift-drag ratio was 3.6. Replacing the flat-plate tip fins with airfoil tip fins increased the maximum trimmed lift-drag ratio to 4.2. The elevons were effective as a roll control, but they produced about as much yawing moment as rolling moment because of the tip-fin dihedral angle. The body flaps produced less rolling moment than the elevons and only small values of yawing moment. A limited investigation of the effect of varying tip-fin dihedral angle indicated that a dihedral angle of 50 deg was a reasonable compromise for longitudinal and lateral stability, longitudinal trim, and performance at subsonic speeds. Ware, George M. and Cruz, Christopher I. Langley Research Center RTOP 505-40-61-01...