An Experimental Study of the Effect of Pitch Rate on Delta Wing Aerodynamics and Stability - 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 An Experimental Study of the Effect of Pitch Rate on Delta Wing Aerodynamics and Stability write by National Aeronautics and Space Administration (NASA). This book was released on 2018-07-02. An Experimental Study of the Effect of Pitch Rate on Delta Wing Aerodynamics and Stability available in PDF, EPUB and Kindle. The final report for the research conducted under this grant (NAG1-641) are contained in the two documents attached as Apendices A and B. The first is the presentation made to NASA Langley personnel on 10 December, 1987, which gave a brief analysis of the experiments. The second is a copy of an AIAA paper given in June 1988, which describes in detail the test setup, data acquisition and reduction, and results obtained. Bragg, M. B. Unspecified Center...
Scientific and Technical Aerospace Reports
Scientific and Technical Aerospace Reports - 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 Scientific and Technical Aerospace Reports write by . This book was released on 1994. Scientific and Technical Aerospace Reports available in PDF, EPUB and Kindle.
Experimental Determination of Damping in Pitch of Swept and Delta Wings at Supersonic Mach Numbers
Experimental Determination of Damping in Pitch of Swept and Delta Wings at Supersonic Mach Numbers - 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 Experimental Determination of Damping in Pitch of Swept and Delta Wings at Supersonic Mach Numbers write by John A. Moore. This book was released on 1957. Experimental Determination of Damping in Pitch of Swept and Delta Wings at Supersonic Mach Numbers available in PDF, EPUB and Kindle. The damping-in-pitch derivative was determined experimentally at Mach numbers of 2.96 and 3.92 for two delta wings having aspect ratios of 2 and 3 and for one sweptback tapered wing having an aspect ratio of 3 by using a free-oscillation technique. The tests were made at Reynolds numbers based on mean aerodynamic chord from 4,000,000 to 12,000,000 for an angle-of-attack range of zero to 10 degrees. The reduced-frequency parameter ranged from 0.006 to 0.022.
NASA's University Program
NASA's University Program - 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's University Program write by United States. National Aeronautics and Space Administration. Office of University Affairs. This book was released on . NASA's University Program available in PDF, EPUB and Kindle.
NASA's University Program Active Projects
NASA's University Program Active Projects - 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's University Program Active Projects write by . This book was released on . NASA's University Program Active Projects available in PDF, EPUB and Kindle.
