Prediction Of Normal Force Pitching Moment And Yawing Force On Bodies Of Revolution At Angles Of Attack Up To 50 Degrees Using A Concentrated Vortex Flow Field Model

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Prediction of Normal Force, Pitching Moment, and Yawing Force on Bodies of Revolution at Angles of Attack Up to 50 Degrees Using a Concentrated Vortex Flow-field Model

Andrew B. Wardlaw (Jr.),W. J. Glowacki
Prediction of Normal Force Pitching Moment and Yawing Force on Bodies of Revolution at Angles of Attack Up to 50 Degrees Using a Concentrated Vortex Flow field Model Book PDF

Author : Andrew B. Wardlaw (Jr.),W. J. Glowacki
Publisher : Unknown
Page : 100 pages
File Size : 52,7 Mb
Release : 1973
Category : Angle of attack (Aerodynamics)
ISBN : UOM:39015095152867

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Prediction of Normal Force, Pitching Moment, and Yawing Force on Bodies of Revolution at Angles of Attack Up to 50 Degrees Using a Concentrated Vortex Flow-field Model by Andrew B. Wardlaw (Jr.),W. J. Glowacki Pdf

A method initially proposed by Bryson is extended to include asymmetric shedding. This method employs the impulsive flow analogy, and models each wake vortex using a single-point vortex. Free parameters inherent in the problem formulation are determined empirically. Normal force, pitching moment and yawing force coefficients are predicted for slender bodies with a nose fineness ratio greater than four and at a Mach number less than 0.9. (Modified author abstract).

Induced Side Forces on Bodies of Revolution at High Angle of Attack

Wardlaw, Jr. (Andrew B.),Alfred Merle Morrison
Induced Side Forces on Bodies of Revolution at High Angle of Attack Book PDF

Author : Wardlaw, Jr. (Andrew B.),Alfred Merle Morrison
Publisher : Unknown
Page : 52 pages
File Size : 51,8 Mb
Release : 1975
Category : Aerodynamic load
ISBN : UOM:39015095247162

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Induced Side Forces on Bodies of Revolution at High Angle of Attack by Wardlaw, Jr. (Andrew B.),Alfred Merle Morrison Pdf

Linear regression techniques are used to establish a quantitative description of side forces on bodies at high incidence. A data base is assembled concerning the key side force characteristics of maximum observed side force, angle of occurrence, and minimum angle of attack at which a side force is observed. This information is examined to determine the important trends and a predictive model for side force based on the crossflow analogy is developed to suggest other important variables. A linear regression model for these quantities is developed to include only those variables which are statistically significant. Results indicate that peak side force coefficients are a function of Mach number and only weakly of Reynolds number. Nose fineness is the critical model dimension which suggests that peak side force is a product of the nose flow field. The angle at which peak side forces occur is found to be dependent on model length and Mach number, while the onset angle of attack is a function of model length only.

Naval Research Reviews

Anonim
Naval Research Reviews Book PDF

Author : Anonim
Publisher : Unknown
Page : 520 pages
File Size : 47,9 Mb
Release : 1976
Category : Naval research
ISBN : UOM:39015000504624

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Naval Research Reviews by Anonim Pdf

Boundary Layer Effects

Anthony W. Fiore
Boundary Layer Effects Book PDF

Author : Anthony W. Fiore
Publisher : Unknown
Page : 962 pages
File Size : 50,5 Mb
Release : 1978
Category : Turbulent boundary layer
ISBN : UOM:39015095313683

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Boundary Layer Effects by Anthony W. Fiore Pdf

In 1975 the U.S. Air Force and the Federal Republic of Germany signed a Data Exchange Agreement numbered AF-75-G-7440 entitled 'Viscous and Interacting Flow Fields.' The purpose was to exchange data in the area of boundary layer research. It includes both experimental and theoretical boundary layer research at speeds from subsonic to hypersonic Mach numbers in the presence of laminar, transitional, and turbulent boundary layers. The main effort in recent years has been on turbulent boundary layers, both attached and separated in the presence of such parameters as pressure gradients, wall temperature, surface roughness, etc. In the United States the research was conducted in various Department of Defense, NASA, aircraft corporations, and various university laboratories. In the Federal Republic of Germany it was carried out within the various DFVLR, industrial, and university research centers.

Applied Mechanics Reviews

Anonim
Applied Mechanics Reviews Book PDF

Author : Anonim
Publisher : Unknown
Page : 620 pages
File Size : 41,6 Mb
Release : 1974
Category : Mechanics, Applied
ISBN : UCAL:C2682447

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Applied Mechanics Reviews by Anonim Pdf

A Collection of Technical Papers

Anonim
A Collection of Technical Papers Book PDF

Author : Anonim
Publisher : Unknown
Page : 782 pages
File Size : 55,9 Mb
Release : 1975
Category : Fluid dynamics
ISBN : PSU:000011909200

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A Collection of Technical Papers by Anonim Pdf

NASA Contractor Report

Anonim
NASA Contractor Report Book PDF

Author : Anonim
Publisher : Unknown
Page : 364 pages
File Size : 43,5 Mb
Release : 1984
Category : Aeronautics
ISBN : MINN:319510008444477

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NASA Contractor Report by Anonim Pdf

Tactical Missile Aerodynamics

Michael J. Hemsch,Jack Norman Nielsen
Tactical Missile Aerodynamics Book PDF

Author : Michael J. Hemsch,Jack Norman Nielsen
Publisher : Unknown
Page : 890 pages
File Size : 42,8 Mb
Release : 1986
Category : Technology & Engineering
ISBN : UOM:39015011191429

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Tactical Missile Aerodynamics by Michael J. Hemsch,Jack Norman Nielsen Pdf

Tactical Missile Aerodynamics

American Institute of Aeronautics and Astronautics
Tactical Missile Aerodynamics Book PDF

Author : American Institute of Aeronautics and Astronautics
Publisher : AIAA (American Institute of Aeronautics & Astronautics)
Page : 806 pages
File Size : 41,6 Mb
Release : 1992
Category : Guided missiles
ISBN : 1563470160

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Tactical Missile Aerodynamics by American Institute of Aeronautics and Astronautics Pdf

Prediction Methodology contains updated versions of nine chapters from the first edition and chapters on drag prediction, component build-up methods, Euler methods and Navier-Stokes solvers. Special attention is paid to nonlinear flow phenomena and unconventional airframe shapes. Eight colour plates and more than 540 figures are included.

An Investigation of Separated Flow about a Hemisphere-cylinder at 0- to 19-deg Incidence in the Mach Number Range from 0.6 to 1.5

T. Hsieh
An Investigation of Separated Flow about a Hemisphere cylinder at 0 to 19 deg Incidence in the Mach Number Range from 0 6 to 1 5 Book PDF

Author : T. Hsieh
Publisher : Unknown
Page : 242 pages
File Size : 42,9 Mb
Release : 1976
Category : Aerodynamics, Transonic
ISBN : UOM:39015104975530

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An Investigation of Separated Flow about a Hemisphere-cylinder at 0- to 19-deg Incidence in the Mach Number Range from 0.6 to 1.5 by T. Hsieh Pdf

The objective of this investigation was to evaluate various jet simulation parameters in an attempt to establish a method of matching hot jet interference with cold jet flows. Successful parameters were determined based on their ability to correlate integrated afterbody pressure drag, a measurement of aerodynamic interference, for jet flows of varying total temperature. Data used in this investigation were obtained from experiments conducted in the AEDC Propulsion Wind Tunnel (16T) with three different isolated nozzle/afterbody configurations at free-stream Mach numbers from 0.6 to 1.5. Gas temperature effects on pressure drag were acquired with a convergent nozzle utilizing an air/ethylene burner to produce gas temperatures from 540 to 3,300 R. In addition, the jet effects of varying internal nozzle geometry, specifically nozzle divergence half-angle and nozzle exit-to-throat area ratio, were investigated utilizing high-pressure air as the nozzle exhaust gas. Jet simulation parameters were evaluated for jet flows where nozzle exit-to-throat area ratio was varied from 1.0 to approximately 1.5 and where divergence half-angle was varied from 0 to 10 deg.

High Angle of Attack Missile Aerodynamics at Mach Numbers 0.30 to 1.5

Valentine Dahlem,Jack I. Flaherty,Donald E. Shereda,Christian E. G. Przirembel
High Angle of Attack Missile Aerodynamics at Mach Numbers 0 30 to 1 5 Book PDF

Author : Valentine Dahlem,Jack I. Flaherty,Donald E. Shereda,Christian E. G. Przirembel
Publisher : Unknown
Page : 328 pages
File Size : 43,6 Mb
Release : 1980
Category : Air-to-air missiles
ISBN : UOM:39015095299106

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High Angle of Attack Missile Aerodynamics at Mach Numbers 0.30 to 1.5 by Valentine Dahlem,Jack I. Flaherty,Donald E. Shereda,Christian E. G. Przirembel Pdf