The book documents Glenn's many research specialties over those 75 years. Among them are early jet engines and rockets; flight safety and fuel efficiency tested in premier icing and wind tunnels; liquid hydrogen fuel which, despite skeptics like aerospace engineer Wernher von Braun, helped the U.S. win the race to the moon; and electric propulsion, considered key to future space flight. Space enthusiasts, aviation personnel, aerospace engineers, and inventors may be interested in this comprehensive and milestone volume. Other related products: NASA at 50: Interviews With NASA\'s Senior Leadership can be found here: https: //bookstore.gpo.gov/products/sku/033-000-01360-4 Other products published by National Aeronautical and Space Administration (NASA) can be found here: https: //bookstore.gpo.gov/agency/550

This computational aerodynamics textbook is written at the undergraduate level, based on years of teaching focused on developing the engineering skills required to become an intelligent user of aerodynamic codes. This is done by taking advantage of CA codes that are now available and doing projects to learn the basic numerical and aerodynamic concepts required. This book includes a number of unique features to make studying computational aerodynamics more enjoyable. These include: • The computer programs used in the book's projects are all open source and accessible to students and practicing engineers alike on the book's website, www.cambridge.org/aerodynamics. The site includes access to images, movies, programs, and more • The computational aerodynamics concepts are given relevance by CA Concept Boxes integrated into the chapters to provide realistic asides to the concepts • Readers can see fluids in motion with the Flow Visualization Boxes carefully integrated into the text.

This manual describes the NASA Glenn Research Center's 1 - by 1 -Foot Supersonic Wind Tunnel and provides information for customers who wish to conduct experiments in this facility. Tunnel performance envelopes of total pressure, total temperature, and dynamic pressure as a function of test section Mach number are presented. For each Mach number, maps are presented of Reynolds number per foot as a function of the total air temperature at the test section inlet for constant total air pressure at the inlet. General support systems-such as the service air, combustion air, altitude exhaust system, auxiliary bleed system, model hydraulic system, schlieren system, model pressure-sensitive paint, and laser sheet system are discussed. In addition, instrumentation and data processing, acquisition systems are described, pretest meeting formats and schedules are outlined, and customer responsibilities and personnel safety are addressed.Seablom, Kirk D. and Soeder, Ronald H. and Stark, David E. and Leone, John F. X. and Henry, Michael W.Glenn Research CenterMACH NUMBER; REYNOLDS NUMBER; SUPERSONIC WIND TUNNELS; SUPERSONIC FLOW; TEST CHAMBERS; DATA ACQUISITION; MANUALS; WIND TUNNEL NOZZLES; DYNAMIC PRESSURE; WIND TUNNEL TESTS

Learn the design and analysis of numerical algorithms for aerodynamics. Ideal for graduates, researchers, and professionals in the field.

A large-scale, variable-geometry inlet model with a design Mach number of 3.0 was tested at Mach numbers from 1.55 to 3.2. Variable features of the inlet for off-design operation are an adjustable-height ramp system and a translating cowl. This report presents experimental results for a diffuser and boundary-layer bleed configuration which was optimized at the design Mach number. Overall performance was high with throat-mounted vortex generators, which were effective in reducing flow distortion in the subsonic diffuser at the higher Mach numbers.