Slender-body Theory Based on Approximate Solution of the Transonic Flow Equation - read free eBook in online reader or directly download on the web page. Select files or add your book in reader. Download and read online ebook Slender-body Theory Based on Approximate Solution of the Transonic Flow Equation write by John R. Spreiter. This book was released on 1959. Slender-body Theory Based on Approximate Solution of the Transonic Flow Equation available in PDF, EPUB and Kindle. Approximate solutions of the nonlinear equations of the small disturbance theory of transonic flow are found for the pressure distribution on pointed slender bodies of revolution for flows with free-stream Mach number 1, and for flows that are either purely subsonic or purely supersonic. These results are obtained by application of a method based on local linearization that was introduced recently in the analysis of similar problems in low-dimensional flows. The theory is developed for bodies of arbitrary shapes, and specific results are given for cone-cylinders and for parabolic-arc bodies at zero angle of attack. All results are compared either with existing theoretical results or with experimental data.
Slender-body Theory Based on Approximate Solution of the Transonic Flow Equation
Slender-body Theory Based on Approximate Solution of the Transonic Flow Equation - read free eBook in online reader or directly download on the web page. Select files or add your book in reader. Download and read online ebook Slender-body Theory Based on Approximate Solution of the Transonic Flow Equation write by John R. Spreiter. This book was released on 1959. Slender-body Theory Based on Approximate Solution of the Transonic Flow Equation available in PDF, EPUB and Kindle. Summary: Approximate solutions of the nonlinear equations of the small disturbance theory of transonic flow are found for the pressure distribution on pointed slender bodies of revolution for flows with free-stream Mach number 1, and for flows that are either purely subsonic or purely supersonic. These results are obtained by application of a method based on local linearization that was introduced recently in the analysis of similar problems in low-dimensional flows. The theory is developed for bodies of arbitrary shapes, and specific results are given for cone-cylinders and for parabolic-arc bodies at zero angle of attack. All results are compared either with existing theoretical results or with experimental data.
NASA Technical Report
NASA Technical Report - read free eBook in online reader or directly download on the web page. Select files or add your book in reader. Download and read online ebook NASA Technical Report write by . This book was released on 1961. NASA Technical Report available in PDF, EPUB and Kindle.
Slender-body Theory Based on Approximate Solution of Transonic Flow Equation [with List of References]
Slender-body Theory Based on Approximate Solution of Transonic Flow Equation [with List of References] - read free eBook in online reader or directly download on the web page. Select files or add your book in reader. Download and read online ebook Slender-body Theory Based on Approximate Solution of Transonic Flow Equation [with List of References] write by . This book was released on 1959. Slender-body Theory Based on Approximate Solution of Transonic Flow Equation [with List of References] available in PDF, EPUB and Kindle.
Numerical Calculation of Transonic Flow about Slender Bodies of Revolution
Numerical Calculation of Transonic Flow about Slender Bodies of Revolution - read free eBook in online reader or directly download on the web page. Select files or add your book in reader. Download and read online ebook Numerical Calculation of Transonic Flow about Slender Bodies of Revolution write by Frank R. Bailey. This book was released on 1971. Numerical Calculation of Transonic Flow about Slender Bodies of Revolution available in PDF, EPUB and Kindle. A relaxation method is described for the numerical solution of the transonic small disturbance equation for flow about a slender body of revolution. Results for parabolic arc bodies, both with and without an attached sting, are compared with wind-tunnel measurements for a free-stream Mach number range from 0.90 to 1.20. The method is also used to show the effects of wind-tunnel wall interference by including boundary conditions representing porous-wall and open-jet wind-tunnel test sections.
