Download or read book Nose Bluntness Cone Angle and Mach Number Effects on the Stability Derivatives of Slender Cones written by James T. Clay and published by . This book was released on 1967 with total page 0 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 Effects of Nose Bluntness Fineness Ratio Cone Angle and Model Base on the Static Aerodynamic Characteristics of Blunt Bodies at Mach Numbers of 1 57 1 80 and 2 16 and Angles of Attack Up to 180 written by David S. Shaw and published by . This book was released on 1963 with total page 88 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Effect of Unsymmetrical Nose bluntness on the Stability Derivatives of a 10 Degree Cone at Mach 14 written by Otto Walchner and published by . This book was released on 1970 with total page 27 pages. Available in PDF, EPUB and Kindle. Book excerpt: In the analysis of the free flight motion of bodies of revolution, the tricyclic theory assumes that a small configurational asymmetry does not violate the rotational symmetry of the stability derivatives in pitch and yaw but does produce a non-zero trim angle. Tests at Mach 14 show that a small unsymmetric nose bluntness destroys the rotational symmetry of the stability derivatives of a slender cone at hypersonic Mach numbers and therefore severely violates the assumptions of the tricyclic theory. Restoring and damping derivatives in pitch and yaw are reported for a 10 deg cone with symmetric and unsymmetrically blunted noses. The effect of non-equal stability derivatives on the motion are shown for a simplified case. (Author).
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 Research on Hypersonic Stability Problems written by O. Walchner and published by . This book was released on 1974 with total page 20 pages. Available in PDF, EPUB and Kindle. Book excerpt: This final report summarizes the in-house research work on hypersonic stability problems, applicable to reentry dynamics. During the period 1963 to 1974 research contributions were made in the following areas: (1) Static and dynamic stability in pitch; (2) hypersonic roll damping; (3) asymmetric nose effects; (4) non linear aerodynamics; (5) stability coefficients in nonplanar motions. This in-house research effort was terminated as of 1 July 1974.
Download or read book Static Aerodynamic Characteristics of Short Blunt Cones with Various Nose and Base Cone Angles at Mach Numbers from 0 6 to 5 5 and Angles of Attack to 180 Degrees written by Stuart L. Treon and published by . This book was released on 1961 with total page 40 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Effect of Unit Reynolds Number Nose Bluntness Angle of Attack and Roughness on Transition on a 5 Half angle Cone at Mach 8 written by P. Calvin Stainback and published by . This book was released on 1969 with total page 82 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Effect of Unsymmetrical Nose bluntness of the Pressure Distribution Over a 10 Cone at Mach 14 written by Otto Walchner and published by . This book was released on 1970 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt: In the analysis of the free flight motion of bodies of revolution, the tricyclic theory assumes that a small configurational asymmetry does not violate the rotational symmetry of the stability derivatives in pitch and yaw but does produce a non-zero trim angle. Tests at Mach 14 show that a small unsymmetric nose bluntness destroys the rotational symmetry of the stability derivatives of a slender cone at hypersonic Mach numbers and therefore severely violates the assumptions of the tricyclic theory. Restoring and damping derivatives in pitch and yaw are reported for a 10 deg cone with symmetric and unsymmetrically blunted noses. The effect of non-equal stability derivatives on the motion are shown for a simplified case. (Author).
Download or read book Research Review written by United States. Air Force. Office of Aerospace Research and published by . This book was released on 1968 with total page 368 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Research Review written by and published by . This book was released on 1968 with total page 360 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 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 0 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book OAR Research Review written by United States. Air Force. Office of Aerospace Research and published by . This book was released on 1968 with total page 528 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).
Download or read book Effects of Nose Bluntness Fineness Ratio Cone Angle and Model Base on the Static Aerodynamic Characteristics of Blunt Bodies at Mach Numbers of 1 57 1 80 and 2 16 and Angles of Attack Up to 180 Degrees written by David S. Shaw and published by . This book was released on 1963 with total page 77 pages. Available in PDF, EPUB and Kindle. Book excerpt:
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:
