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Author : Frankie Gale Moore,Roy Mitchell McInville,Tom Hymer
Publisher : Unknown
Page : 148 pages
File Size : 53,6 Mb
Release : 1997
Category : Aerodynamics
ISBN : UOM:39015095342120
Author : Frank G. Moore,Roy Mitchell McInville,Tom Hymer,Naval Surface Warfare Center (U.S.). Dahlgren Division
Publisher : Unknown
Page : 139 pages
File Size : 53,7 Mb
Release : 1997-09-01
Category : Aerodynamics
ISBN : 1423570952
An improved method has been developed to compute aerodynamics of noncircular cross section shapes. The improved method is based on extending current state of the art methods for computing aerodynamics of noncircular wing- body shapes based on circular wing-body methods. Specific additions to the state of the art methods presently in use include extensions to a broader class of cross section bodies and to a higher angle of attack (AOA); extensions to allow improved accuracy at low cross flow Mach number and to allow body cross section shape to impact the critical cross flow Reynolds number; and a method to treat wing-body interference factor corrections as a function of body geometry, Mach number, and AOA. The new methods were applied to a broad class of noncircular body alone and wing body configurations for which wind tunnel data were available. In general, results for normal force, axial force and center of pressure were quite good over the Mach number and AOA range where data was available. This included Mach numbers as low as 0.3 and as high as 14 and AOAs to 60 degrees.
Author : Anonim
Publisher : Unknown
Page : 0 pages
File Size : 41,9 Mb
Release : 1997
Category : Electronic
ISBN : OCLC:946121268
An improved method has been developed to compute aerodynamics of noncircular cross section shapes. The improved method is based on extending current state of the art methods for computing aerodynamics of noncircular wing-body shapes based on circular wing-body methods. Specific additions to the state of the art methods presently in use include extensions to a broader class of cross section bodies and to a higher angle of attack (AOA); extensions to allow improved accuracy at low cross flow Mach number and to allow body cross section shape to impact the critical cross flow Reynolds number; and a method to treat wing-body interference factor corrections as a function of body geometry, Mach number, and AOA. The new methods were applied to a broad class of noncircular body alone and wing body configurations for which wind tunnel data were available. In general, results for normal force, axial force and center of pressure were quite good over the Mach number and AOA range where data was available. This included Mach numbers as low as 0.3 and as high as 14 and AOAs to 60 degrees.
Author : Frankie Gale Moore,Thomas C. Hymer
Publisher : Unknown
Page : 232 pages
File Size : 53,8 Mb
Release : 2002
Category : Aerodynamics
ISBN : UOM:39015095342161
A new version of the aeroprediction code (APC), the AP02, has been developed to address the requirements arising from advanced weapon concepts. The AP02 was formed by adding significant new technology and several productivity improvements to the previous version of the APC, the AP98. New technology added included 6 and 8 fin aerodynamics, improved nonlinear aerodynamics, improved pitch damping predictions, improved power-on base drag estimates, base-bleed effect on base drag estimation, improved axial force of nonaxisymmetric bodies and trailing-edge flap capability. Other improvements and productivity enhancements include an aerodynamic smoother, ballistic and three degree-of-freedom simulation modules as well as refinements for the pre- and post-processor for inputs and outputs of the AP02. Comparison of the predicted aerodynamics of the AP02 to AP98 and experimental data showed the AP02 to be slightly better than the AP98 in most cases that both codes would handle. However, due to the additional new technology incorporated into the AP02, many new options are available in the AP02 that are not available in the AP98. Therefore, the AP02 is more robust and, on average, is slightly more accurate than the AP98 in predicting aerodynamics of weapons.
Author : Naval Surface Warfare Center (U.S.). Dahlgren Division
Publisher : Unknown
Page : 180 pages
File Size : 50,7 Mb
Release : 1998
Category : Naval research
ISBN : OSU:32435059913616
Author : Frankie Gale Moore
Publisher : Unknown
Page : 174 pages
File Size : 40,9 Mb
Release : 1993
Category : Aerodynamics
ISBN : UOM:39015095341817
This report discusses the pros and cons of numerical, semiempirical and empirical aeroprediction codes and lists many state-of-the-art codes in use today. It then summarizes many of the more popular approximate analytical methods used in State-of-the-Art (SOTA) semiempirical aeroprediction codes. It also summarizes some recent new nonlinear semiempirical methods that allow more accurate calculation of static aerodynamics on complete missile configurations to higher angles of attack. Results of static aerodynamic calculations on complete missile configurations compared to wind tunnel data are shown for several configurations at various flight conditions. Calculations show the new nonlinear methods being far superior to some of the former linear technology when used at angles of attack greater than about 15 degrees. Aeroprediction codes, Nonlinear semiempirical methods, State-of-the-Art (SOTA) semiempirical aeroprediction codes, Static aerodynamic calculations.
Author : Theodore Simos,George Maroulis
Publisher : CRC Press
Page : 1192 pages
File Size : 45,7 Mb
Release : 2019-04-29
Category : Computers
ISBN : 9781482284201
The International Conference of Computational Methods in Sciences and Engineering (ICCMSE) is unique in its kind. It regroups original contributions from all fields of the traditional Sciences, Mathematics, Physics, Chemistry, Biology, Medicine and all branches of Engineering. The aim of the conference is to bring together computational scientists from several disciplines in order to share methods and ideas. More than 370 extended abstracts have been submitted for consideration for presentation in ICCMSE 2004. From these, 289 extended abstracts have been selected after international peer review by at least two independent reviewers.
Author : Anonim
Publisher : Unknown
Page : 520 pages
File Size : 49,8 Mb
Release : 1991
Category : Aeronautics
ISBN : MINN:31951P000409415
Author : Anonim
Publisher : Unknown
Page : 1530 pages
File Size : 47,7 Mb
Release : 1991
Category : Science
ISBN : MINN:31951P001783127
Author : Anonim
Publisher : Unknown
Page : 356 pages
File Size : 45,9 Mb
Release : 1974
Category : Aerodynamics
ISBN : PSU:000017295017
Author : Frank G. Moore,Roy M. McInville,David I. Robinson,Naval Surface Warfare Center (U.S.). Dahlgren Division
Publisher : Unknown
Page : 78 pages
File Size : 53,7 Mb
Release : 1999-03-01
Category : Aerodynamics
ISBN : 1423545591
A new semiempirical method was developed to compute aerodynamics of multi-fin missile configurations using cruciform missile aerodynamics as a baseline. The method was developed using full Euler Computational Fluid Dynamics codes to compare computations with wind tunnel data bases for cruciform missiles as a function of Mach number, angle of attack, and aspect ratio. The Euler codes were then used for the same free stream conditions and missile configurations except the number of fins were increased from four to six and eight respectively. A table of coefficients was then formed for the aerodynamics of six- and eight-fin configurations compared to that of four-fin cases for use in the aeroprediction code or other semiempirical codes. It was concluded that this approach worked well except for subsonic Mach numbers at moderate to large angles of attack, where the Euler codes failed to predict the leeward plane flow field adequately. It is believed that full Navier-Stokes solutions could be used to improve upon this semiempirical model. Engineering judgement, in conjunction with low angle-of-attack Euler solutions were used in the regions where Euler solutions were suspect. In comparing the new semiempirical method to a limited amount of wind tunnel data on several configurations, it was concluded that the model worked well at all the conditions where data was available. However, additional wind tunnel data at higher angles of attack on six- and eight-fin configurations is needed before the method can be truly validated.
Author : Anonim
Publisher : Unknown
Page : 980 pages
File Size : 47,5 Mb
Release : 1998
Category : Aeronautics
ISBN : STANFORD:36105021106690
Author : North Atlantic Treaty Organization. Advisory Group for Aerospace Research and Development. Fluid Dynamics Panel. Symposium
Publisher : Unknown
Page : 306 pages
File Size : 43,9 Mb
Release : 1996
Category : Aerodynamic load
ISBN : UIUC:30112018018231
Author : Frank G. Moore,Tom Hymer,Naval Surface Warfare Center (U.S.). Dahlgren Division
Publisher : Unknown
Page : 63 pages
File Size : 55,7 Mb
Release : 1997-02-01
Category : Aerodynamic load
ISBN : 1423567161
An improved semiempirical method for axial force calculation on missile configurations has been developed. The method uses the theoretical methods currently used in the Naval Surface Warfare Center Aeroprediction Code for zero angle-of-attack (AOA) axial force computations and several wind tunnel data bases to compute changes in axial force at AOA. The method is applicable to bodies alone, wing-body, and wing-body-tail configurations for both zero and non-zero control deflections. It has been developed to allow computation for AOA to 90 deg at any Mach number. However, it has been validated against data only to Mach number of 4.6 and AOA to 40 deg for all configurations. For body alone and wing-body cases, it has been validated to 90 deg AOA. Additional test data or Navier Stokes computations would allow refinement of the improved method. The new method has been compared to several existing techniques. The method was found to be as good as or better than existing techniques, but more general than existing methods in terms of configurations and Mach numbers allowed for the method to be used.
Author : M. R. Mendenhall
Publisher : Unknown
Page : 806 pages
File Size : 45,8 Mb
Release : 1992
Category : Guided missiles
ISBN : UOM:39015028414491