Download or read book Effects of Nose Bluntness Angle of Attack and Oscillation Amplitude on Hypersonic Unsteady Aerodynamics of Slender Cones written by Lars Eric Ericsson and published by . This book was released on 1970 with total page 13 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Investigation of Nose Bluntness and Angle of Attack Effects on Slender Bodies in Viscous Hypersonic Flows written by National Aeronautics and Space Adm Nasa and published by Independently Published. This book was released on 2018-11-13 with total page 126 pages. Available in PDF, EPUB and Kindle. Book excerpt: Hypersonic flows over cones and straight biconic configurations are calculated for a wide range of free stream conditions in which the gas behind the shock is treated as perfect. Effect of angle of attack and nose bluntness on these slender cones in air is studied extensively. The numerical procedures are based on the solution of complete Navier-Stokes equations at the nose section and parabolized Navier-Stokes equations further downstream. The flow field variables and surface quantities show significant differences when the angle of attack and nose bluntness are varied. The complete flow field is thoroughly analyzed with respect to velocity, temperature, pressure, and entropy profiles. The post shock flow field is studied in detail from the contour plots of Mach number, density, pressure, and temperature. The effect of nose bluntness for slender cones persists as far as 200 nose radii downstream. Sehgal, A. K. and Tiwari, S. N. and Singh, D. J. Unspecified Center ANGLE OF ATTACK; BLUNT BODIES; FLOW DISTRIBUTION; HYPERSONIC FLOW; NOSE CONES; SLENDER CONES; VISCOUS FLOW; AERODYNAMIC CONFIGURATIONS; AIR FLOW; ENTROPY; FLOW VELOCITY; FREE FLOW; MACH NUMBER; NAVIER-STOKES EQUATION; PRESSURE EFFECTS; TEMPERATURE EFFECTS; TEMPERATURE PROFILES...
Download or read book Effects of Angle of Attack and Bluntness on the Hypersonic Flow Over a 15 semiapex Cone in Helium written by Joseph W. Cleary and published by . This book was released on 1970 with total page 52 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Transonic Investigation of the Effects of Nose Bluntness Fineness Ratio Cone Angle and Base Shape on the Static Aerodynamic Characteristics of Short Blunt Cones at Angles of Attack to 1800 written by Cuyler W. Brooks and published by . This book was released on 1963 with total page 48 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Applied Mechanics Reviews written by and published by . This book was released on 1972 with total page 520 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Unsteady Aerodynamic Analysis of Space Shuttle Vehicles Part 1 Summary Report written by and published by . This book was released on 1973 with total page 92 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book NASA SP written by and published by . This book was released on 1970 with total page 1166 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Asymmetric Nose Bluntness Effects on the Aerodynamics of a Slender Cone at Mach 14 written by and published by . This book was released on 1973 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt: Experiments were performed in ARL's 20-inch hypersonic wind tunnel on a 10 degree half-angle circular cone model whose pointed tip was removed by one or more planar slanted cuts. The projected frontal nose area was 1/2 percent of the base area. The configurational asymmetry of this moderate bluntness destroys the rotational symmetry of the shock wave over the entire model. In turn, the rotational symmetry of the surface pressure distribution is also lost. Depending on the nose configuration, asymmetric sideloads were observed at axial flow conditions which may or may not cause the vehicle to trim in free flight. Nose asymmetry combined with mass asymmetry, therefore, may produce a rolling moment even at zero trim. The stability derivatives are not identical in pitch and yaw, as would be expected for a body of revolution, and vary differently as functions of the angle of attack and angle of sideslip. (Modified author abstract).
Download or read book AIAA 70 200 AIAA 70 238 With omissions in numbering written by and published by . This book was released on 1970 with total page 540 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Angle of attack Analysis of a Spinning Slender Cone with Slight Aerodynamic and Mass Asymmetries Reentry F written by Gerard E. Woodbury and published by . This book was released on 1970 with total page 44 pages. Available in PDF, EPUB and Kindle. Book excerpt: An analysis of the flight motions of the Reentry F spacecraft was made by using a combination of a force method and an application of the angular-rate solution of the linearized equations of motion since a trim buildup due to flight-induced asymmetries introduced an error into the ordinarily determined angle of attack. The analysis revealed that the spacecraft had little or no asymmetries prior to and during pitch-roll resonance. However, as the spacecraft emerged from resonance, a slight trim angle of attack was noted which shortly thereafter experienced a reversal in orientation and a subsequent rapid growth in the same general direction to a maximum of 0.87 (degrees).
Download or read book The Effect of Severe Nose Bluntness on the Stability of Slender Cones in Hypersonic Flow written by Brian Quinn and published by . This book was released on 1967 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt: The flow around a blunted slender cone performing pitching oscillations is theoretically analyzed by means of Chernyi's blast-wave piston analogy. Stationary and transient shock shapes and pressure distributions are presented in power series form. Within the region of applicability, the stationary pressure agrees well with Chernyi's numerical integration. Normal force and pitching moment coefficient derivatives are presented and the results are plotted for a 10 degree cone. The theoretical static and dynamic stability derivatives agree satisfactorily with recent experiments in a Mach 14 wind tunnel. It is concluded that the experimentally observed reduction in static and dynamic stability due to increased nose bluntness may be attributed to blast wave effects. (Author).
Download or read book AIAA 84 0351 84 0400 written by and published by . This book was released on 1984 with total page 528 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Real gas Effects on the Aerodynamics of Blunt Cones as Measured in a Hypervelocity Range written by C. J. Welsh and published by . This book was released on 1979 with total page 32 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Hypersonic Dynamic Stability Conical body experimental program by R B Hobbs Jr written by General Electric Company and published by . This book was released on 1967 with total page 128 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Effects of Nose Bluntness and Angle of Attack on Slender Bodies in Hypersonic Flows written by S. N. Tiwari and published by . This book was released on 1992 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Scientific and Technical Aerospace Reports written by and published by . This book was released on 1970 with total page 1338 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Asymmetric Nose Bluntness Effect on the Aerodynamics of a Slender Cone at Mach 14 written by Otto Walchner and published by . This book was released on 1973 with total page 32 pages. Available in PDF, EPUB and Kindle. Book excerpt: Experiments were performed in ARL's 20-inch hypersonic wind tunnel on a 10 degree half-angle circular cone model whose pointed tip was removed by one or more planar slanted cuts. The projected frontal nose area was 1/2 percent of the base area. The configurational asymmetry of this moderate bluntness destroys the rotational symmetry of the shock wave over the entire model. In turn, the rotational symmetry of the surface pressure distribution is also lost. Depending on the nose configuration, asymmetric sideloads were observed at axial flow conditions which may or may not cause the vehicle to trim in free flight. Nose asymmetry combined with mass asymmetry, therefore, may produce a rolling moment even at zero trim. The stability derivatives are not identical in pitch and yaw, as would be expected for a body of revolution, and vary differently as functions of the angle of attack and angle of sideslip. (Modified author abstract).
