Download or read book Dynamic Stability Characteristics of A10 deg Cone at Mach Number 10 written by A. E. Hodapp (Jr.) and published by . This book was released on 1964 with total page 32 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Dynamic Stability Characteristics of a 10 deg Cone at Mach Number 20 written by R. H. Urban and published by . This book was released on 1965 with total page 28 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Hypersonic Dynamic Stability Summary by L A Marshall written by General Electric Company and published by . This book was released on 1967 with total page 108 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 1982 with total page 1282 pages. Available in PDF, EPUB and Kindle. Book excerpt: Lists citations with abstracts for aerospace related reports obtained from world wide sources and announces documents that have recently been entered into the NASA Scientific and Technical Information Database.
Download or read book Technical Abstract Bulletin written by and published by . This book was released on with total page 760 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Government wide Index to Federal Research Development Reports written by and published by . This book was released on 1967 with total page 1352 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Sting Interference Effects as Determined by Measurements of Dynamic Stability Derivatives Surface Pressure and Base Pressure for Mach Numbers 2 Through 8 written by Bob L. Uselton and published by . This book was released on 1980 with total page 154 pages. Available in PDF, EPUB and Kindle. Book excerpt: Wind tunnel tests were conducted to provide support interference information for planning and directing wind tunnel tests at supersonic and hypersonic Mach numbers. Sting-length and sting-diameter effects on base and surface pressures of a blunt 6-deg cone with a sliced base were investigated at Mach numbers 2, 3, 5, and 8. Dynamic stability tests on a blunt 7-deg cone were also conducted at Mach numbers 2, 5, and 8. The objectives of the 7-deg cone tests were to define critical sting lengths as determined by the measurement of dynamic stability derivatives, static pitching moment, and base pressure. Two frequencies of oscillation were investigated, and data were obtained for laminar, transitional, and turbulent boundary-layer conditions at the model base. The data from the 6- and 7-deg cone tests showed that the critical sting length depended on the interference indicator, Mach number, angle of attack, state of the model boundary layer, and frequency of oscillation. The critical sting length was generally less for models with turbulent boundary layers than for those with laminar boundary layers. A critical sting length of 2.5 model diameters was determined to be suitable for all test conditions that produced a turbulent boundary layer at or ahead of the model base.
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 Experimental Determination of Aerodynamic Drag on a Blunted 10 deg Cone at Angles of Attack in Hypersonic Rarefied Flow written by David E. Boylan and published by . This book was released on 1964 with total page 40 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Hypersonic Dynamic Stability written by L. A. Marshall and published by . This book was released on 1967 with total page 98 pages. Available in PDF, EPUB and Kindle. Book excerpt: The report presents a summary of the important results obtained on a combined analytical and experimental program for investigation of the hypersonic dynamic stability of re-entry vehicles. An unsteady flow field solution is described which predicts the static and dynamic stability characteristics for vehicles which are executing small amplitude oscillations about zero angle of attack. Solutions were obtained for sharp and blunted, axisymmetric and two-dimensional shapes in real gas equilibrium flow. The experimental program was conducted in AEDC tunnel 'C' at Mach 10 and in the Ling-Temco-Vought Hot Shot tunnel at Mach 14 and 20 to obtain dynamic stability characteristics of a 10 degree cone. Data are presented to show the effect of bluntness ratio, reduced frequency, center of gravity location, Reynolds number and Mach number. Comparisons are made with various theoretical results and limited correlations are shown which establish significant trends.
Download or read book Evaluation of Critical Sting Length on a 7 deg Cone as Determined by Measurements of Dynamic Stability Derivatives and Base Pressure for Mach Numbers 0 2 Through 1 3 written by Frederick B. Cyran and published by . This book was released on 1981 with total page 58 pages. Available in PDF, EPUB and Kindle. Book excerpt: Wind tunnel tests were conducted to provide sting-support interference information for planning and directing wind tunnel tests at subsonic and transonic Mach numbers. Sting-length effects on dynamic stability derivatives, static pitching moment, and base pressure of a blunt, flat-base 7- deg cone were investigated at Mach numbers 0.2 to 1.3 in the Arnold Engineering Development Center (AEDC) Propulsion Wind Tunnel Facility (PWT). Two frequencies of oscillation, nominally 5.3 and 2.9 Hz, were investigated. The boundary-layer state at the model base was turbulent for all Mach numbers greater than 0.2. The interference effects of two types of model-wake splitter plates were also investigated. The results showed that the critical sting length depended on the Mach number, angle of attack, and type of data used as the interference indicator. A critical sting length of three model diameters was determined to be suitable for all test conditions for the ratio of sting-diameter-to-model-base- diameter (0.22) for this test.
Download or read book Hypersonic Dynamic Stability written by R. B. Hobbs (Jr.) and published by . This book was released on 1967 with total page 118 pages. Available in PDF, EPUB and Kindle. Book excerpt: Wind tunnel tests were conducted at M = 10 and at M = 14 and 20 to obtain experimental data on the hypersonic dynamic stability characteristics of a 10-degree half-angle cone. These data were generated to support dynamic stability studies and to evaluate the effects of many geometric and environmental variables, which influence the oscillatory motion of re-entry vehicles. The state-of-the-art of experimental ground testing in hypersonic dynamic stability is reviewed in detail with respect to simulation and data measuring capabilities. Data correlations were obtained to compare facilities and to evaluate the degree of consistency of results using different techniques in measuring and reducing the data. The confidence level for the data is established by means of these correlations, and conclusive interpretations of the data for application in flight estimates can only be made when the significance of these correlations are fully realized. The data correlations do bring out definite inconsistencies in test results and demonstrate the more obvious shortcomings of ground test simulation in this type of experiment research. Test results indicate that the 10-degree cone configuration is dynamically stable over the entire scope of matrix variables covered in the experimental program. Dynamic instabilities observed in flight remain unconfirmed by these ground test results.
Download or read book Applied Mechanics Reviews written by and published by . This book was released on 1970 with total page 796 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book An Investigation of Sting Interference Effects on an Oscillating Cone in Transonic Flow written by Frederick B. Cyran and published by . This book was released on 1981 with total page 92 pages. Available in PDF, EPUB and Kindle. Book excerpt: Wind tunnel sting support interference effects on dynamic stability derivatives, static pitching moment and base pressure of a blunt, 7-deg cone were investigated at subsonic and transonic Mach numbers. The cone was tested with sting configurations having a variable effective sting length ranging from 1 to 3.3 model base diameters, at angles of attack ranging from 0 to 30 deg. A forced-oscillation system was utilized to obtain data at a frequency of oscillation of approximately 5.3 Hz, and at an amplitude of 1 deg. The Reynolds number, based on model base diameter, was nominally 1.8 million, which produced a turbulent boundary layer over the aft portion of the model. The nature of the causes of these interference effects is discussed and analyzed with respect to sting length, type of measurement, and Mach number, with emphasis on defining critical sting length and on predicting minimal interference sting configurations for dynamic stability testing. The results showed that the critical sting length depended on the type of measurement used as the interference indicator, Mach number, and angle of attack. A critical sting length of three model diameters was determined to be suitable for all test conditions for the ratio of sting diameter-to-model base diameter (0.22) investigated. (Author).
Download or read book Critical Sting Length as Determined by the Measurement of Pitch damping Derivatives for Laminar Transitional and Turbulent Boundary Layers at Mach Number 3 for Reduced Frequencies of 0 0033 and 0 0056 written by Bob L. Uselton and published by . This book was released on 1977 with total page 72 pages. Available in PDF, EPUB and Kindle. Book excerpt: A research program was initiated for the purpose of investigating some of the problem areas in regard to support interference in supersonic wind tunnels. The critical sting length at alpha = 0 was determined by the measurement of pitch-damping derivatives for laminar, transitional, and turbulent boundary layers at the model base. The effect of wedge splitter plates on sting interference was also investigated. By utilizing the small amplitude forced oscillation technique, data were obtained at Mach number 3 on a blunt 7-deg cone for reduced frequencies of 0.0033 and 0.0056. The results showed that the critical sting length with respect to sting interference on pitch-damping data was two model diameters for the two reduced frequencies investigated and was independent of the type of boundary layer at the model base. Decreasing the effective sting length from 3.3 to one model diameter increased the model base pressure substantially and the model surface pressure slightly. The critical sting length for minimal base pressure interference is 2.5 model diameters for this model and these test conditions.
Download or read book Technical Report Jet Propulsion Laboratory California Institute of Technology written by Jet Propulsion Laboratory (U.S.) and published by . This book was released on 1964 with total page 16 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book U S Government Research Reports written by and published by . This book was released on 1962 with total page 182 pages. Available in PDF, EPUB and Kindle. Book excerpt:
