Span Load Distributions Resulting from Constant Angle of Attack, Steady Rolling Velocity, Steady Pitching Velocity, and Constant Vertical Acceleration for Tapered Sweptback Wings With Streamwise Tips Subsonic Leading Edges and Supersonic Trailing Edges PDF Download

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Span Load Distributions Resulting from Constant Angle of Attack, Steady Rolling Velocity, Steady Pitching Velocity, and Constant Vertical Acceleration for Tapered Sweptback Wings With Streamwise Tips Subsonic Leading Edges and Supersonic Trailing Edges

Span Load Distributions Resulting from Constant Angle of Attack, Steady Rolling Velocity, Steady Pitching Velocity, and Constant Vertical Acceleration for Tapered Sweptback Wings With Streamwise Tips Subsonic Leading Edges and Supersonic Trailing Edges PDF Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 224

Book Description
On the basis of linearized supersonic-flow theory, the theoretical spanwise distributions of circulation (which are proportional to the span load distributions) resulting from constant angle of attack, steady rolling velocity, steady pitching velocity, and constant vertical acceleration were calculated for a series of thin, sweptback, tapered wings with streamwise tips. The analysis is valid at those speeds for which the wing is wholly contained between the Mach cones springing from the wing apex and the trailing edge of the root section, that is, subsonic leading edges and supersonic trailing edges. An added restriction is that the Mach cones emanating from the leading edges of the wing tips must not intersect on the wing. Formulas for the spanwise distributions of circulation are given in closed form. Numerical results are presented as a series of design charts from which the desired loading may be obtained for given values of aspect ratio, taper ratio, Mach number, and leading-edge sweepback. The axis of pitch is taken at the wing apex although, by use of the calculated results and a simple transformation, span load distributions for steady pitching velocity may be readily obtained for arbitrary location of the pitch axis. Variations of the spanwise distributions of circulation with the various plan-form parameters, Mach number, and axis-of-pitch location are also presented for illustrative purposes.

Span Load Distributions Resulting from Constant Angle of Attack, Steady Rolling Velocity, Steady Pitching Velocity, and Constant Vertical Acceleration for Tapered Sweptback Wings With Streamwise Tips Subsonic Leading Edges and Supersonic Trailing Edges

Span Load Distributions Resulting from Constant Angle of Attack, Steady Rolling Velocity, Steady Pitching Velocity, and Constant Vertical Acceleration for Tapered Sweptback Wings With Streamwise Tips Subsonic Leading Edges and Supersonic Trailing Edges PDF Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 224

Book Description
On the basis of linearized supersonic-flow theory, the theoretical spanwise distributions of circulation (which are proportional to the span load distributions) resulting from constant angle of attack, steady rolling velocity, steady pitching velocity, and constant vertical acceleration were calculated for a series of thin, sweptback, tapered wings with streamwise tips. The analysis is valid at those speeds for which the wing is wholly contained between the Mach cones springing from the wing apex and the trailing edge of the root section, that is, subsonic leading edges and supersonic trailing edges. An added restriction is that the Mach cones emanating from the leading edges of the wing tips must not intersect on the wing. Formulas for the spanwise distributions of circulation are given in closed form. Numerical results are presented as a series of design charts from which the desired loading may be obtained for given values of aspect ratio, taper ratio, Mach number, and leading-edge sweepback. The axis of pitch is taken at the wing apex although, by use of the calculated results and a simple transformation, span load distributions for steady pitching velocity may be readily obtained for arbitrary location of the pitch axis. Variations of the spanwise distributions of circulation with the various plan-form parameters, Mach number, and axis-of-pitch location are also presented for illustrative purposes.

Span Load Distributions Resulting from Constant Angle of Attack, Steady Rolling Velocity, Steady Pitching Velocity, and Constant Vertical Acceleration for Tapered Sweptback Wings With Streamwise Tips Subsonic Leading Edges and Supersonic Trailing Edges

Span Load Distributions Resulting from Constant Angle of Attack, Steady Rolling Velocity, Steady Pitching Velocity, and Constant Vertical Acceleration for Tapered Sweptback Wings With Streamwise Tips Subsonic Leading Edges and Supersonic Trailing Edges PDF Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 0

Book Description
On the basis of linearized supersonic-flow theory, the theoretical spanwise distributions of circulation (which are proportional to the span load distributions) resulting from constant angle of attack, steady rolling velocity, steady pitching velocity, and constant vertical acceleration were calculated for a series of thin, sweptback, tapered wings with streamwise tips. The analysis is valid at those speeds for which the wing is wholly contained between the Mach cones springing from the wing apex and the trailing edge of the root section, that is, subsonic leading edges and supersonic trailing edges. An added restriction is that the Mach cones emanating from the leading edges of the wing tips must not intersect on the wing. Formulas for the spanwise distributions of circulation are given in closed form. Numerical results are presented as a series of design charts from which the desired loading may be obtained for given values of aspect ratio, taper ratio, Mach number, and leading-edge sweepback. The axis of pitch is taken at the wing apex although, by use of the calculated results and a simple transformation, span load distributions for steady pitching velocity may be readily obtained for arbitrary location of the pitch axis. Variations of the spanwise distributions of circulation with the various plan-form parameters, Mach number, and axis-of-pitch location are also presented for illustrative purposes.

Analysis of Multicell Delta Wings on Cal-Tech Analog Computer

Analysis of Multicell Delta Wings on Cal-Tech Analog Computer PDF Author: Richard H. MacNeal
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 786

Book Description
Deflections and all internal forces have been calculated for concentrated static loads. Vibration modes are also presented. The effects of neglecting shearing strains in the ribs and spars and also of assuming the ribs to be rigid have been investigated by modifying the electric circuits to correspond to these simplifications.

Technical Note - National Advisory Committee for Aeronautics

Technical Note - National Advisory Committee for Aeronautics PDF Author: United States. National Advisory Committee for Aeronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 994

Book Description

Technical Note

Technical Note PDF Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 446

Book Description

High Speed Wing Theory

High Speed Wing Theory PDF Author: Doris Cohen
Publisher: Princeton University Press
ISBN: 1400874947
Category : Technology & Engineering
Languages : en
Pages : 251

Book Description
Part of the Princeton Aeronautical Paperback series designed to bring to students and research engineers outstanding portions of the twelve-volume High Speed Aerodynamics and Jet Propulsion series. These books have been prepared by direct reproduction of the text from the original series and no attempt has been made to provide introductory material or to eliminate cross reference to other portions of the original volumes. Originally published in 1960. The Princeton Legacy Library uses the latest print-on-demand technology to again make available previously out-of-print books from the distinguished backlist of Princeton University Press. These editions preserve the original texts of these important books while presenting them in durable paperback and hardcover editions. The goal of the Princeton Legacy Library is to vastly increase access to the rich scholarly heritage found in the thousands of books published by Princeton University Press since its founding in 1905.

Gust-load and Airspeed Data from One Type of Four-engine Airplane on Five Routes from 1947 to 1954

Gust-load and Airspeed Data from One Type of Four-engine Airplane on Five Routes from 1947 to 1954 PDF Author: Walter G. Walker
Publisher:
ISBN:
Category : Acceleration (Mechanics)
Languages : en
Pages : 642

Book Description
This paper presents the results of an analysis of approximately 100,000 hours of V-G data from one type of four-engine civil transport airplane to determine the magnitude and frequency of occurrence of the gust loads and gusts. The data were obtained during routine operations from 1947 to 1954 on five different routes. The normal accelerations for each of the five operations may be expected to exceed the value corresponding to the limit-gust-load-factor increment, on the average, twice (once positive and once negative) within the range of 5,000,000 to 22,300,000 flight miles. A derived gust velocity of 50 feet per second was exceeded twice within the range of 600,000 to 1,900,000 flight miles. The gust loads of the present operations were less than the loads experienced by other four-engine civil transports previously investigated, but the differences are not significant. The present data indicated only small differences due to seasonal effects and different operational utilization.

NACA Conference on Aircraft Loads, Structures, and Flutter

NACA Conference on Aircraft Loads, Structures, and Flutter PDF Author:
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 702

Book Description

Aerodynamic Components of Aircraft at High Speeds

Aerodynamic Components of Aircraft at High Speeds PDF Author: Allen F. Donovan
Publisher: Princeton University Press
ISBN: 1400879906
Category : Science
Languages : en
Pages : 863

Book Description
Volume VII of the High Speed Aerodynamics and Jet Propulsion series. It deals with applications to specific components of the complete aircraft. Sections of the volume include: aerodynamics of wings at high speed, aerodynamics of bodies at high speed, interaction problems, propellers at high speed, diffusers and nozzles, and nonsteady wing characteristics. Originally published in 1957. The Princeton Legacy Library uses the latest print-on-demand technology to again make available previously out-of-print books from the distinguished backlist of Princeton University Press. These editions preserve the original texts of these important books while presenting them in durable paperback and hardcover editions. The goal of the Princeton Legacy Library is to vastly increase access to the rich scholarly heritage found in the thousands of books published by Princeton University Press since its founding in 1905.

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 PDF Author: Frankie Gale Moore
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 174

Book Description
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.
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