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Aircraft Configurations Developing High Lift-drag Ratios at High Supersonic Speeds

1956 Aerodynamics
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Release : 1956
Genre : Aerodynamics
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Book Synopsis Aircraft Configurations Developing High Lift-drag Ratios at High Supersonic Speeds by : A. J. Eggers (Jr.)

Download or read book Aircraft Configurations Developing High Lift-drag Ratios at High Supersonic Speeds written by A. J. Eggers (Jr.). This book was released on 1956. Available in PDF, EPUB and Kindle. Book excerpt: Summary: The problem of designing an aircraft which will develop high lift-drag ratios in flight at high supersonic speeds is attacked using the elementary principle that the components of the aircraft should be individually and collectively arranged to impart the maximum downward and the minimum forward momentum to the surrounding air. This principle in conjunction with other practical considerations of hypersonic flight leads to the study of configurations for which the body is situated entirely below the wing; that is, flat-top wing-body combinations. Theory indicates that sensibly complete aircraft of this type can be designed to develop lift-drag ratios well in excess of 6.

Aircraft Configurations Developed High Lift-drag Ratios at High Supersonic Speeds

1956
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Release : 1956
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Book Synopsis Aircraft Configurations Developed High Lift-drag Ratios at High Supersonic Speeds by : A.J. Jr Eggers

Download or read book Aircraft Configurations Developed High Lift-drag Ratios at High Supersonic Speeds written by A.J. Jr Eggers. This book was released on 1956. Available in PDF, EPUB and Kindle. Book excerpt:

Aircraft Configurations Developing High Lift-drag Ratios at High Supersonic Speeds

2023-07-18
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Release : 2023-07-18
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Book Rating : 656/5 ( reviews)

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Book Synopsis Aircraft Configurations Developing High Lift-drag Ratios at High Supersonic Speeds by : Ames Research Center

Download or read book Aircraft Configurations Developing High Lift-drag Ratios at High Supersonic Speeds written by Ames Research Center. This book was released on 2023-07-18. Available in PDF, EPUB and Kindle. Book excerpt: Aircraft Configurations is a comprehensive guide to the design and testing of supersonic aircraft. Based on research conducted at the Ames Research Center, it provides valuable insights into the aerodynamics of high-speed flight and the challenges of designing aircraft that can operate at these speeds. This book is an essential resource for anyone interested in the science of aviation. This work has been selected by scholars as being culturally important, and is part of the knowledge base of civilization as we know it. This work is in the "public domain in the United States of America, and possibly other nations. Within the United States, you may freely copy and distribute this work, as no entity (individual or corporate) has a copyright on the body of the work. Scholars believe, and we concur, that this work is important enough to be preserved, reproduced, and made generally available to the public. We appreciate your support of the preservation process, and thank you for being an important part of keeping this knowledge alive and relevant.

A Supersonic Area Rule and an Application to the Design of a Wing-body Combination with High Lift-drag Ratios

1960 Airplanes
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Release : 1960
Genre : Airplanes
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Book Synopsis A Supersonic Area Rule and an Application to the Design of a Wing-body Combination with High Lift-drag Ratios by : Richard T. Whitcomb

Download or read book A Supersonic Area Rule and an Application to the Design of a Wing-body Combination with High Lift-drag Ratios written by Richard T. Whitcomb. This book was released on 1960. Available in PDF, EPUB and Kindle. Book excerpt: Summary: As an extension of the transonic area rule, a concept for interrelating the wave drags of wing-body combinations at moderate supersonic speeds with axial developments of cross-sectional area has been derived. The wave drag of a combination at a given supersonic speed is related to a number of developments of cross-sectional areas as intersected by Mach planes. On the basis of this concept and other design procedures, a structurally feasible, swept-wing--indented-body combination has been designed to have relatively high maximum lift-drag ratios over a range of transonic and moderate supersonic Mach numbers. The wing of the combination has been designed to have reduced drag associated with lift and, when used with an indented body, to have low zero-lift wave drag. Experimental results have been obtained for this configuration at Mach numbers from 0.80 to 2.01. Maximum lift-drag ratios of approximately 14 and 9 were measured at Mach numbers of 1.15 and 1.41, respectively.

Aerodynamic Performance and Static Stability at Mach Number 3.3 of an Aircraft Configuration Employing Three Triangular Wing Panels and a Body Equal Length

1960 Aerodynamics, Supersonic
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Release : 1960
Genre : Aerodynamics, Supersonic
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Book Synopsis Aerodynamic Performance and Static Stability at Mach Number 3.3 of an Aircraft Configuration Employing Three Triangular Wing Panels and a Body Equal Length by : Carlton S. James

Download or read book Aerodynamic Performance and Static Stability at Mach Number 3.3 of an Aircraft Configuration Employing Three Triangular Wing Panels and a Body Equal Length written by Carlton S. James. This book was released on 1960. Available in PDF, EPUB and Kindle. Book excerpt: An aircraft configuration, previously conceived as a means to achieve favorable aerodynamic stability characteristics., high lift-drag ratio, and low heating rates at high supersonic speeds., was modified in an attempt to increase further the lift-drag ratio without adversely affecting the other desirable characteristics. The original configuration consisted of three identical triangular wing panels symmetrically disposed about an ogive-cylinder body equal in length to the root chord of the panels. This configuration was modified by altering the angular disposition of the wing panels, by reducing the area of the panel forming the vertical fin, and by reshaping the body to produce interference lift. Six-component force and moment tests of the modified configuration at combined angles of attack and sideslip were made at a Mach number of 3.3 and a Reynolds number of 5.46 million. A maximum lift-drag ratio of 6.65 (excluding base drag) was measured at a lift coefficient of 0.100 and an angle of attack of 3.60. The lift-drag ratio remained greater than 3 up to lift coefficient of 0.35. Performance estimates, which predicted a maximum lift-drag ratio for the modified configuration 27 percent greater than that of the original configuration, agreed well with experiment. The modified configuration exhibited favorable static stability characteristics within the test range. Longitudinal and directional centers of pressure were slightly aft of the respective centroids of projected plan-form and side area.

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