عنوان

Airfoil Design and Data

شابک

3662026465

شابک

9783662026465

شماره

b579225

عنوان اصلي

Airfoil Design and Data

نام عام مواد

[Book]

نام نخستين پديدآور

by Richard Eppler.

محل نشرو پخش و غیره

Berlin, Heidelberg

نام ناشر، پخش کننده و غيره

Springer Berlin Heidelberg

تاریخ نشرو بخش و غیره

1990

نام خاص و کميت اثر

1 ressource en ligne (VIII, 562 pages)

متن يادداشت

1 Introduction --; 2 Potential Flow, Analysis Mode --; 3 Potential Flow, Design Mode --; 3.1 General Considerations --; 3.2 The Complex Planes --; 3.3 The Velocity Specification on the Unit Circle --; 3.4 Specification of the Velocity Distribution in Segments --; 3.5 Main Pressure Recovery Functions --; 3.6 Conditions for Continous Velocity Distributions --; 3.7 The Closure Conditions --; 3.8 The Trailing Edge and the Leading Edge --; 3.9 The Computation of the Airfoil Coordinates --; 3.10 Common Features of the Input Data Lines --; 3.11 The Input Lines for the Airfoil Design --; 3.12 The Trailing Edge Iteration --; 3.13 General Remarks --; 4 Boundary Layer Theory --; 4.1 Fundamentals --; 4.2 The Computation of Laminar and Turbulent Boundary Layers --; 4.3 Boundary Layer Transition --; 4.4 The Laminar Separation Bubble --; 4.5 Total Lift, Drag, and Moment --; 4.6 The Bubble Warning --; 4.7 Single Roughness Elements --; 5 General Considerations for the Selection of the Design Parameters --; 5.1 The Laminar Region of the Airfoils --; 5.2 The Critical Reynolds Number --; 5.3 The Main Pressure Recovery --; 5.4 Airfoils with Flaps --; 5.5 Profiles for Maritime Applications (Hydrofoils) --; 6 Airfoil Data --; 6.1 Directory --; 6.2 Older, Successfully Applied Airfoils for Different Reynolds Number Ranges --; 6.3 Airfoils for Low Reynolds Numbers --; 6.4 Airfoils for Manpowered Aircraft --; 6.5 Airfoils without Flaps for the Reynolds Number Range of Sailplanes --; 6.6 Airfoils with Flaps for Sailplanes (Gliders) --; 6.7 High lift Airfoils --; 6.8 Airfoils for General Aviation Aircrafts --; 6.9 Airfoils for Acrobatic Aircraft --; 6.10 Airfoils for Tailless Airplanes --; 6.11 Airfoils for Vertical and Horizontal Tails --; 6.12 Airfoils for Propellers --; 6.13 Airfoils for Helicopter Rotor Blades --; 6.14 Hydrofoils --; 6.15 Airfoils for Non-Lifting Struts --; Appendix I: The Mathematics of the Inverse Potential Flow Method --; Appendix II: Airfoil Coordinates --; Appendix III: Airfoil Input Data --; References.

متن يادداشت

This book represents the latest state of my work on airfoils which began more than 30 years ago. The major subject of this work was the continous development of a computer program which allows to solve the potential flow problem for given airfoils and to design airfoils from the properties of their velocity distributions. After the solution of these potential flow analysis and design problems the boundary layers can be computed and the total lift. drag and moment coefficients can be evaluated. Several short and unpublished notes on this program were promoted by the US Airforce Academy in Colorado Springs with the support of R. Gallington and W. Smith. A first complete description was published by the NASA Langley Research Center. Ref. [1]. after had been invited to visit this center for four weeks in 1978. This was the beginnning of a very fruitful coorperation with Dan M. Somers. It led to another visit to the NASA Langley Center in 1979. during which several new options were added to the program and described in Ref. [2]. The NASA TM [1] contains a listing of the program which invited some smart people to retype it. Obviously they've been selling it for a lot of money. However. this early 1979 version should not be used anymore. because it's missing ten years of development and improvements. The latest version of the program is available from Universitat Stuttgart. Inst.

موضوع مستند نشده

Electric power production.

موضوع مستند نشده

Engineering.

موضوع مستند نشده

Mechanics.

شماره رده

نشانه اثر

مستند نام اشخاص تاييد نشده

by Richard Eppler.

مستند نام اشخاص تاييد نشده

Richard Eppler

نام الکترونيکي

نوع ماده

[Book]

تكميل شده

Y