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Author: Z. Popinski
Publisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 282
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Book Description
Design methods are developed for determining aerodynamic control effectiveness at hypersonic speeds along body surface. Pressure and heat transfer distributions in separated regions due to aerodynamic control deflection are described in terms of characteristic magnitudes and distance parameters by semiempirical correlations. The forms of these correlations are inferred from theory and experimental data. Using these correlations, pressure distribution in the separated region over a deflected flap is approximated and expressions for force and moment coefficients are determined. General charts are developed which present separation and flow parameters over a range of flight conditions for a typical hypersonic vehicle. Flow separation over a fin-plate configuration is presented using experimental measurements. Also, characteristics of flow over a flat plate, flat delta wing, and delta with dihedral are analyzed using visual flow records and pressure measurements from the point of view of two-dimensional flow. Applicability of the correlation expressions to separated flow on various configurations is discussed and calculated aerodynamic coefficients are compared with measured values.
Author: Z. Popinski
Publisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 282
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Book Description
Design methods are developed for determining aerodynamic control effectiveness at hypersonic speeds along body surface. Pressure and heat transfer distributions in separated regions due to aerodynamic control deflection are described in terms of characteristic magnitudes and distance parameters by semiempirical correlations. The forms of these correlations are inferred from theory and experimental data. Using these correlations, pressure distribution in the separated region over a deflected flap is approximated and expressions for force and moment coefficients are determined. General charts are developed which present separation and flow parameters over a range of flight conditions for a typical hypersonic vehicle. Flow separation over a fin-plate configuration is presented using experimental measurements. Also, characteristics of flow over a flat plate, flat delta wing, and delta with dihedral are analyzed using visual flow records and pressure measurements from the point of view of two-dimensional flow. Applicability of the correlation expressions to separated flow on various configurations is discussed and calculated aerodynamic coefficients are compared with measured values.
Author: National Aeronautics and Space Adm Nasa
Publisher: Independently Published
ISBN: 9781731281333
Category : Science
Languages : en
Pages : 140
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Book Description
Many types of hypersonic aircraft configurations are currently being studied for feasibility of future development. Since the control of the hypersonic configurations throughout the speed range has a major impact on acceptable designs, it must be considered in the conceptual design stage. The ability of the aerodynamic analysis methods contained in an industry standard conceptual design system, APAS II, to estimate the forces and moments generated through control surface deflections from low subsonic to high hypersonic speeds is considered. Predicted control forces and moments generated by various control effectors are compared with previously published wind tunnel and flight test data for three configurations: the North American X-15, the Space Shuttle Orbiter, and a hypersonic research airplane concept. Qualitative summaries of the results are given for each longitudinal force and moment and each control derivative in the various speed ranges. Results show that all predictions of longitudinal stability and control derivatives are acceptable for use at the conceptual design stage. Results for most lateral/directional control derivatives are acceptable for conceptual design purposes; however, predictions at supersonic Mach numbers for the change in yawing moment due to aileron deflection and the change in rolling moment due to rudder deflection are found to be unacceptable. Including shielding effects in the analysis is shown to have little effect on lift and pitching moment predictions while improving drag predictions. Maughmer, Mark D. and Ozoroski, L. and Ozoroski, T. and Straussfogel, D. Unspecified Center AERODYNAMIC CHARACTERISTICS; AERODYNAMIC CONFIGURATIONS; AILERONS; AIRCRAFT CONFIGURATIONS; CONTROL EQUIPMENT; CONTROL SURFACES; HYPERSONIC AIRCRAFT; HYPERSONICS; PREDICTIONS; RUDDERS; SPACE SHUTTLE ORBITERS; X-15 AIRCRAFT; DEFLECTION; DESIGN ANALYSIS; DRAG; FLIGHT TESTS; INDUSTRIES; LONGITUDINAL CONTROL; LONGITUDINAL STABILITY; PITCHING MOMENTS; ROLLING MOMEN...
Author:
Publisher:
ISBN:
Category : Astronautics
Languages : en
Pages : 804
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Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 600
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Author: Michael J Werle
Publisher:
ISBN:
Category : Boundary layer
Languages : en
Pages : 124
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Book Description
The problem discussed is that of theoretically predicting the normal force induced in the boundary layer separation region immediately ahead of a secondary injection port. Attention was limited to the two-dimensional problem of sonic or supersonic normal injection into supersonic or hypersonic mainstreams. A critical review of available experimental studies was conducted in order to isolate those data best representing a two-dimensional state. The resulting compilation of experimental results was thereafter employed as a basis of comparison for available theoretical and empirical flow models. As a result it was found that analytical means are only capable of rough quantitative estimates of control jet effectiveness and that a more detailed flow model is needed to further explain observed phenomenon. The basic features of such a model are formulated and its conceptual validity demonstrated through comparison with experimental results. Problem areas requiring further research are also discussed in detail. (Author).
Author:
Publisher:
ISBN:
Category : Science
Languages : en
Pages : 828
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Author:
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 758
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Author:
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 590
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Book Description
Author: W. H. Loh
Publisher: Springer Science & Business Media
ISBN: 1461586240
Category : Technology & Engineering
Languages : en
Pages : 394
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Book Description
During the last decade, the rapid growth of knowledge in the field of fluid mechanics and heat transfer has resulted in many significant ad vances of interest to students, engineers, and scientists. Accordingly, a course entitled "Modern Developments in Fluid Mechanics and Heat Transfer" was given at the University of California to present significant recent theoretical and experimental work. The course consisted of seven parts: I-Introduction; II-Hydraulic Analogy for Gas Dynamics; 111- Turbulence and Unsteady Gas Dynamics; IV-Rarefied and Radiation Gas Dynamics; V-Biological Fluid Mechanics; VI-Hypersonic and Plasma Gas Dynamics; and VII-Heat Transfer in Hypersonic Flows. The material, presented by the undersigned as course instructor and by various guest lecturers, could easily be adapted by other universities for use as a text for a one-semester senior or graduate course on the subject. Due to the extensive notes developed during the University of California course, it was decided to publish the material in three volumes, of which the present is the first. The succeeding volumes will be entitled "Selected Topics in Fluid and Bio-Fluid Mechanics" and "Introduction to Steady and Unsteady Gas Dynamics." Finally, I must express a word of appreciation to my wife Irene and to my children, Wellington Jr. and Victoria, who made it possible for me to write and edit this book in the very quiet atmosphere of our home.
Author: E. C. Lemmon
Publisher:
ISBN:
Category : Space vehicles
Languages : en
Pages : 64
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Book Description
