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Book NASA s Contributions to Aeronautics Flight environment operations flight testing and research

Download or read book NASA s Contributions to Aeronautics Flight environment operations flight testing and research written by and published by . This book was released on 2010 with total page 1064 pages. Available in PDF, EPUB and Kindle. Book excerpt: Two-volume collection of case studies on aspects of NACA-NASA research by noted engineers, airmen, historians, museum curators, journalists, and independent scholars. Explores various aspects of how NACA-NASA research took aeronautics from the subsonic to the hypersonic era.-publisher description.

Book Fifty Years of Flight Research

Download or read book Fifty Years of Flight Research written by David F. Fisher and published by . This book was released on 1999 with total page 526 pages. Available in PDF, EPUB and Kindle. Book excerpt: A bibliography of Technical Reports from Dryden Research Center, 1946-1996. Dryden was a National Advisory Committee for Aeronautics (NACA) facility from to 1946-1958, when NACA became NASA (National Aeronautics and Space Administration). This bibliography encompasses both NACA and NASA publications. Illustrated with diagrams and photos. Black and white version.

Book NASA s Contributions to Aeronautics

Download or read book NASA s Contributions to Aeronautics written by Richard Hallion and published by National Aeronautics and Space Administration Headquarters. This book was released on 2010 with total page 1064 pages. Available in PDF, EPUB and Kindle. Book excerpt: Two-volume collection of case studies on aspects of NACA-NASA research by noted engineers, airmen, historians, museum curators, journalists, and independent scholars. Explores various aspects of how NACA-NASA research took aeronautics from the subsonic to the hypersonic era.-publisher description.

Book Static and Rotational Aerodynamic Data from O to 90 Angle of Attack for a Series of Basic and Altered Forebody Shapes

Download or read book Static and Rotational Aerodynamic Data from O to 90 Angle of Attack for a Series of Basic and Altered Forebody Shapes written by William Bihrle (Jr) and published by . This book was released on 1989 with total page 372 pages. Available in PDF, EPUB and Kindle. Book excerpt: The loss of airplanes and occupants attributable to departures from controlled flight and ensuing spins has been a problem since the earliest days of aviation. These losses have plagued both the military and general aviation communities. The phenomena responsible for such losses take on added significance because, in the past ten years, high angle-of-attack capability in the post-stall region has been shown to significantly enhance the air combat maneuvering effectiveness of fighter airplanes and, therefore, this is not a region to be avoided, but rather exploited, if possible. Fortunately, the aerodynamic characteristics that produce departures and spins have been identified within the past few years through rotary balance tests, which identify an airplane's aerodynamic characteristics in a steady rotational flow environment. It was demonstrated in the Phase I that the high angle-of-attack aerodynamic characteristics are very configuration dependent and that forebody geometry can have a significant influence on these characteristics. In the extreme case, an aircraft's undesirable aerodynamics can be completely attributable to the forebody. In this instance, autorotative yawing and rolling moments, as well as increasing nose-up pitching moments with increasing rotation rate, are realized.

Book Results of a 0 1 scale B 1 Inlet Model Test at Transonic and Supersonic Mach Numbers

Download or read book Results of a 0 1 scale B 1 Inlet Model Test at Transonic and Supersonic Mach Numbers written by F. J. Graham and published by . This book was released on 1971 with total page 150 pages. Available in PDF, EPUB and Kindle. Book excerpt: Results are presented of a wind tunnel investigation of a 0.1-scale model of the left-hand dual inlet air induction system of the B-1 aircraft. The test was conducted from Mach number 0.55 to 2.2 over an angle-of-attack range from -4 to 13 deg and yaw angles of -8 to 5 deg. Inlet performance in terms of compressor-face total-pressure recovery, total-pressure distortion, and turbulence index is presented as a function of inlet mass-flow ratios for various inlet geometries and model attitudes. The total-pressure recovery of the mixed-compression inlet was very good, but the total-pressure distortion at critical massflow ratios was higher than normally desired for satisfactory turbine engine operation. Best performance was realized with ramp and throat height schedules determined from previous testing. Effects of angle of attack and yaw were seen as general sidewash effects. The addition of canard-type fins had negligible effect on inlet performance. (Author).

Book Static and Rotational Aerodynamic Data from O to 90 Angle of Attack for a Series of Basic and Altered Forebody Shapes

Download or read book Static and Rotational Aerodynamic Data from O to 90 Angle of Attack for a Series of Basic and Altered Forebody Shapes written by William Bihrle (Jr) and published by . This book was released on 1989 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt: The loss of airplanes and occupants attributable to departures from controlled flight and ensuing spins has been a problem since the earliest days of aviation. These losses have plagued both the military and general aviation communities. The phenomena responsible for such losses take on added significance because, in the past ten years, high angle-of-attack capability in the post-stall region has been shown to significantly enhance the air combat maneuvering effectiveness of fighter airplanes and, therefore, this is not a region to be avoided, but rather exploited, if possible. Fortunately, the aerodynamic characteristics that produce departures and spins have been identified within the past few years through rotary balance tests, which identify an airplane's aerodynamic characteristics in a steady rotational flow environment. It was demonstrated in the Phase I that the high angle-of-attack aerodynamic characteristics are very configuration dependent and that forebody geometry can have a significant influence on these characteristics. In the extreme case, an aircraft's undesirable aerodynamics can be completely attributable to the forebody. In this instance, autorotative yawing and rolling moments, as well as increasing nose-up pitching moments with increasing rotation rate, are realized.

Book Dynamic Ground Effects Flight Test of an F 15 Aircraft

Download or read book Dynamic Ground Effects Flight Test of an F 15 Aircraft written by Stephen Corda and published by . This book was released on 1994 with total page 32 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Book An Algorithm for Computing the Range of Trimable Angle of Attack for Aircraft Experiencing Effector Failures

Download or read book An Algorithm for Computing the Range of Trimable Angle of Attack for Aircraft Experiencing Effector Failures written by Joseph Kaloust and published by . This book was released on 2002 with total page 14 pages. Available in PDF, EPUB and Kindle. Book excerpt: This paper presents a method for computing the range of angle of attack for which an air vehicle can be rotationally trimmed when experiencing control effector failures. The algorithms are applied to an unpowered reentry vehicle as an example. Types of failures considered include floating effectors that do not contribute to the aerodynamic forces and moments or effectors that are locked at a given position within the effector displacement range. The algorithm can provide critical information to online trajectory generators or path planners for autonomous air vehicles.

Book Calculation of High Angle of Attack Aerodynamics of Fighter Configurations

Download or read book Calculation of High Angle of Attack Aerodynamics of Fighter Configurations written by Chuan-Tau Edward Lan and published by . This book was released on 1991 with total page 90 pages. Available in PDF, EPUB and Kindle. Book excerpt: A computational method for lateral-directional aerodynamics of fighter configuration is developed. The leading edge vortices are represented by free vortex filaments which are adjusted iteratively to satisfy the force-free condition. The forebody vortex separation, both symmetrical and asymmetrical, is calculated using slender body theory. Effect of boundary layer separation on lifting surfaces is accounted for using the effective sectional angles of attack. The latter are obtained iteratively by matching the nonlinear sectional lift with the computed resulted based on lifting surface theory. Results for several fighter configurations are employed for comparison with available data. It is shown that the present method produces resonable results in predicting sideslip derivatives, while role and yaw rate derivatives do not compare very well with forced oscillation test data at high angles of attack. Industrial usage of this has produced mixed results. At this time, the use of these methods in a production manner is not recommended.

Book Comparisons of In flight F 111A Inlet Performance for On and Off scheduled Inlet Geometry at Mach Numbers of 0 68 to 2 18

Download or read book Comparisons of In flight F 111A Inlet Performance for On and Off scheduled Inlet Geometry at Mach Numbers of 0 68 to 2 18 written by Richard A. Martin and published by . This book was released on 1971 with total page 52 pages. Available in PDF, EPUB and Kindle. Book excerpt: In-flight F-111 data on total and static pressure from left inlet during automatically scheduled and manually controlled off-schedule positioning of spike at Mach 0.68 to 2.18.