Body Alone Aerodynamics Of Guided And Unguide Projectiles At Subsonic Transonic And Supersonic Mach Numbers PDF Download

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Body Alone Aerodynamics of Guided and Unguided Projectiles at Subsonic, Transonic and Supersonic Mach Numbers

Body Alone Aerodynamics of Guided and Unguided Projectiles at Subsonic, Transonic and Supersonic Mach Numbers
Author:
Publisher:
Total Pages: 121
Release: 1972
Genre:
ISBN:

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Several theoretical and empirical methods are combined into a single computer program to predict lift, drag, and center of pressure on bodies of revolution at subsonic, transonic, and supersonic Mach numbers. The body geometries can be quite general in that pointed, spherically blunt, or truncated noses are allowed as well as discontinuities in nose shape. Particular emphasis is placed on methods which yield accuracies of ninety percent or better for most configurations but yet are computationally fast. Theoretical and experimental results are presented for several projectiles and a computer program listing is included as an appendix.


Body Alone Aerodynamics of Guided and Unguide Projectiles at Subsonic, Transonic and Supersonic Mach Numbers

Body Alone Aerodynamics of Guided and Unguide Projectiles at Subsonic, Transonic and Supersonic Mach Numbers
Author: Frankie Gale Moore
Publisher:
Total Pages: 146
Release: 1972
Genre: Aerodynamics
ISBN:

Download Body Alone Aerodynamics of Guided and Unguide Projectiles at Subsonic, Transonic and Supersonic Mach Numbers Book in PDF, ePub and Kindle

Several theoretical and empirical methods are comgined into a single computer program to predict lift, drag, and center of pressure on bodies of revolution at subsonic, transonic, and supersonic Mach numbers. The body geometries can be quite general in that pointed, spherically blunt, or truncated noses are allowed as well as discontinuities in nose shape. Particular emphasis is placed on methods which yield accuracies of ninety percent or better for most configurations but yet are computationally fast. theoretical and experimental results are presented for several projectiles and a computer program listing is included an an appendix.


Aerodynamics of Guided and Unguided Weapons

Aerodynamics of Guided and Unguided Weapons
Author: Frankie Gale Moore
Publisher:
Total Pages: 218
Release: 1973
Genre: Guided missiles
ISBN:

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Several theoretical and empirical procedures are combined into a single computer program to predict lift, drag, and center of pressure on quite general wing-body geometries. The method is applicable for Mach number zero to three and angle-of-attack zero to about fifteen degrees. Computed results for several configurations compare well with experimental and other analytical results. It costs about five dollars per Mach number to compute the static aerodynamics of a typical wing-body shape on the CDC 6700 computer.


State-of-the-art Engineering Aeroprediction Methods with Emphasis on New Semiempirical Techniques for Predicting Nonlinear Aerodynamics on Complete Missile Configurations

State-of-the-art Engineering Aeroprediction Methods with Emphasis on New Semiempirical Techniques for Predicting Nonlinear Aerodynamics on Complete Missile Configurations
Author: Frankie Gale Moore
Publisher:
Total Pages: 174
Release: 1993
Genre: Aerodynamics
ISBN:

Download State-of-the-art Engineering Aeroprediction Methods with Emphasis on New Semiempirical Techniques for Predicting Nonlinear Aerodynamics on Complete Missile Configurations Book in PDF, ePub and Kindle

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.


The 2002 Version of the Aeroprediction Code

The 2002 Version of the Aeroprediction Code
Author: Frankie Gale Moore
Publisher:
Total Pages: 232
Release: 2002
Genre: Aerodynamics
ISBN:

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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.


Aerodynamic Characteristics of a Series of Bodies with and Without Tails at Mach Numbers from 0.8 to 3.0 and Angles of Attack from 0 to 45 Degrees

Aerodynamic Characteristics of a Series of Bodies with and Without Tails at Mach Numbers from 0.8 to 3.0 and Angles of Attack from 0 to 45 Degrees
Author: Jimmie N. Derrick
Publisher:
Total Pages: 896
Release: 1976
Genre: Aerodynamics, Transonic
ISBN:

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Wind tunnel tests were conducted in a 16 ft. transonic tunnel, a supersonic tunnel, A and a trisonic tunnel to establish a bank of systematic data for body and body-tail configurations at high angles of attack. The configurations were tested at Mach numbers between 0.8 and 3.0, angles of attack from -2 to 45 degrees, and roll angles from 0 to 90 degrees. The aerodynamic characteristics were obtained for the total configuration as well as each of the four undeflected tail fins.