Aerodynamics of Supersonic Lifting Bodies PDF Download
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Author: Martin C. Jischke
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 414
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Book Description
This report describes a combined theoretical and experimental program of research in the aerodynamics of supersonic lifting bodies. Analytical perturbation techniques are used to study the supersonic flow past slightly elliptical cones, cones whose cross-sections deviate slightly but arbitrarily from that of a right circular cone, cones of small longitudinal curvature, and right circular cones undergoing small harmonic pitching and/or plunging motions. These studies all involve perturbations of the well-known solution for supersonic flow past a right circular cone. Closed-form analytical results are achieved through the use of an approximation that accurately predicts results over the entire range of the hypersonic similarity parameter. These results give hypersonic limiting solutions that agree well with other independent analyses and, at the same time, agree exactly with linearized theory in the linear theory limit. Comparisons with experiment, where possible, also show good agreement.
Author: Martin C. Jischke
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 414
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Book Description
This report describes a combined theoretical and experimental program of research in the aerodynamics of supersonic lifting bodies. Analytical perturbation techniques are used to study the supersonic flow past slightly elliptical cones, cones whose cross-sections deviate slightly but arbitrarily from that of a right circular cone, cones of small longitudinal curvature, and right circular cones undergoing small harmonic pitching and/or plunging motions. These studies all involve perturbations of the well-known solution for supersonic flow past a right circular cone. Closed-form analytical results are achieved through the use of an approximation that accurately predicts results over the entire range of the hypersonic similarity parameter. These results give hypersonic limiting solutions that agree well with other independent analyses and, at the same time, agree exactly with linearized theory in the linear theory limit. Comparisons with experiment, where possible, also show good agreement.
Author: Charles J. Nietubicz
Publisher:
ISBN:
Category :
Languages : en
Pages : 80
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Book Description
Aerodynamic characteristics are presented for various lifting body configurations. Data were collected for an angle of attack sweep of -10 degrees to +10 degrees throughout a Mach number range of 1.5 to 4.0. The test Reynolds number per meter was 15,700,000. The data are presented as standard force coefficients which have additionally been transformed about a tunnel axis coordinate system to obtain lift and drag data. The normal force center of pressure was found to be invariant with angle of attack and Mach number for all configurations.
Author: Johns Hopkins University. Applied Physics Laboratory
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 372
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Book Description
Author: Leland H. Jorgensen
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 70
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Book Description
Author: Bernard Spencer
Publisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 86
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Book Description
Author:
Publisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 60
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Book Description
Author:
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 80
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Book Description
A free-flight rocket-propelled-model investigation was conducted at Mach numbers of 1.2 to 1.9 to determine the longitudinal and lateral aero-dynamic characteristics of a low-drag aircraft configuration. The model consisted of an aspect-ratio -1.86 arrow wing with 67.5 deg. leading-edge sweep and NACA 65A004 airfoil section and a triangular vertical tail with 60 deg. sweep and NACA 65A003 section in combination with a body of fineness ratio 20. Aerodynamic data in pitch, yaw, and roll were obtained from transient motions induced by small pulse rockets firing at intervals in the pitch and yaw directions. From the results of this brief aerodynamic investigation, it is observed that very slender body shapes can provide increased volumetric capacity with little or no increase in zero-lift drag and that body fineness ratios of the order of 20 should be considered in the design of long-range supersonic aircraft. The zero-lift drag and the drag-due-to-lift parameter of the test configuration varied linearly with Mach number. The maximum lift-drag ratio was 7.0 at a Mach number of 1.25 and decreased slightly to a value of 6.6 at a Mach number of 1.81. The optimum lift coefficient, normal-force-curve slope, lateral-force-curve slope, static stability in pitch and yaw, time to damp to one-half amplitude in pitch and yaw, the sum of the rotary damping derivatives in pitch and also in yaw, and the static rolling derivatives all decreased with an increase in Mach number. Values of certain rolling derivatives were obtained by application of the least-squares method to the differential equation of rolling motion. A comparison of the experimental and calculated total rolling-moment-coefficient variation during transient oscillations of the model indicated good agreement when the damping-in-roll contribution was included with the static rolling-moment terms.
Author: P. L. Roe
Publisher:
ISBN:
Category :
Languages : en
Pages :
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Book Description
Author: Charles H. McLellan
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 22
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Book Description
A study of the factors affecting the maximum lift-drag ratio has been conducted in an effort to determine how to obtain high aerodynamic values at high supersonic Mach numbers.
Author: National Aeronautics and Space Administration (NASA)
Publisher: Createspace Independent Publishing Platform
ISBN: 9781722218300
Category :
Languages : en
Pages : 28
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Book Description
Lifting bodies are of interest for possible use as space transportation vehicles because they have the volume required for significant payloads and the aerodynamic capability to negotiate the transition from high angles of attack to lower angles of attack (for cruise flight) and thus safely reenter the atmosphere and perform conventional horizontal landings. Results are presented for an experimental and theoretical study of the aerodynamic characteristics at supersonic speeds for a series of lifting bodies with 75 deg delta planforms, rounded noses, and various upper and lower surface cambers. The camber shapes varied in thickness and in maximum thickness location, and hence in body volume. The experimental results were obtained in the Langley Unitary Plan Wind Tunnel for both the longitudinal and the lateral aerodynamic characteristics. Selected experimental results are compared with calculated results obtained through the use of the Hypersonic Arbitrary-Body Aerodynamic Computer Program. Spearman, M. Leroy and Torres, Abel O. Langley Research Center RTOP 505-69-20-01...
