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  • AERODYNAMICS  (42)
  • AIRCRAFT PROPULSION AND POWER  (15)
  • 1
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    A method for measuring Reynolds number, viscosity, and atom concentration in hypervelocity nozzles. (1968)
    In:  Other Sources
    Details
    Publication Date: 2011-08-12
    Description: Reynolds number, viscosity and atom concentration in hypervelocity nozzles measured using stagnation point heat transfer
    Keywords: AERODYNAMICS
    Type: ; ADEMIE DES SCIENCES
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  • 2
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    Analysis of aircraft engine blade subject to ice impact (1992)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: The ice impact problem on an engine blade made of layered composite is simulated. The ice piece is modeled as an equivalent spherical object and has the velocity opposite to that of the aircraft with direction parallel to the engine axis. Near the impact region and along the leading edge, the blade is assumed to be fully stressed and undergoes large deflection. A specified portion of the blade around the impact region is modeled. The effect of ice size and velocity on the average leading edge strain are investigated for a modified SR-2 model unswept composite propfan blade. Parametric studies are performed to study the response due to ice impact at various locations along the span. Also, the effects of engine speed on the strain and impact displacements are discussed. It is found that for a given engine speed, a critical ice speed exists that corresponds to the maximum strain and this critical speed increases with increase in the engine speed.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: FAA, Ninth DOD(NASA)FAA Conference on Fibrous Composites in Structural Design, Volume 3; p 1319-1331
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  • 3
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    Viscous three-dimensional analyses for nozzles for hypersonic propulsion (1990)
    In:  CASI
    Details
    Publication Date: 2013-08-29
    Description: A Navier-Stokes computer code was validated using a number of two- and three-dimensional configurations for both laminar and turbulent flows. The validation data covers a range of freestream Mach numbers from 3 to 14, including wall pressures, velocity pressure, and skin friction. Nozzle flow fields computed for a generic scramjet nozzle from Mach 3 to 20, wall pressures, wall skin friction values, heat transfer values, and overall performance are presented. In addition, three-dimensional solutions obtained for two asymmetric, single expansion ramp nozzles at a pressure ratio of 10 consists of the internal expansion region in the converging/diverging sections and the external superonic exhaust in a quiescent ambient environment. The fundamental characteristics that were captured successfully include expansion fans; Mach wave reflections; mixing layers; and nonsymmetrical, multiple inviscid cell, supersonic exhausts. Comparison with experimental data for wall pressure distributions at the center planes shows good agreement.
    Keywords: AERODYNAMICS
    Type: AGARD, Hypersonic Combined Cycle Propulsion; 18 p
    Format: text
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  • 4
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    Ice-impact analysis of blades (1994)
    In:  CASI
    Details
    Publication Date: 2013-08-29
    Description: A computational capability is described for evaluating the ice-impact on engine blades made from composites. The ice block is modeled as an equivalent spherical object and has the velocity opposite to that of the aircraft with direction parallel to the engine axis. A finer finite element mesh is used for a portion of the blade near the impact region compared to the course mesh for the rest of the blade. The effects of ice size and velocity on the average leading edge strain are evaluated for a simulated unswept composite propfan blade. Parametric studies are performed to assess the blade structural responses due to the ice-impact at various locations along the span. It is found that: (1) for a given engine speed, a critical ice speed exists that corresponds to the maximum strain; and (2) the tip bending type frequencies increase after impact while the torsion frequencies decrease.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: AGARD, Erosion, Corrosion and Foreign Object Damage Effects in Gas Turbines; 12 p
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  • 5
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    Aerodynamic heating in hypersonic flows (1993)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: Aerodynamic heating in hypersonic space vehicles is an important factor to be considered in their design. Therefore the designers of such vehicles need reliable heat transfer data in this respect for a successful design. Such data is usually produced by testing the models of hypersonic surfaces in wind tunnels. Most of the hypersonic test facilities at present are conventional blow-down tunnels whose run times are of the order of several seconds. The surface temperatures on such models are obtained using standard techniques such as thin-film resistance gages, thin-skin transient calorimeter gages and coaxial thermocouple or video acquisition systems such as phosphor thermography and infrared thermography. The data are usually reduced assuming that the model behaves like a semi-infinite solid (SIS) with constant properties and that heat transfer is by one-dimensional conduction only. This simplifying assumption may be valid in cases where models are thick, run-times short, and thermal diffusivities small. In many instances, however, when these conditions are not met, the assumption may lead to significant errors in the heat transfer results. The purpose of the present paper is to investigate this aspect. Specifically, the objectives are as follows: (1) to determine the limiting conditions under which a model can be considered a semi-infinite body; (2) to estimate the extent of errors involved in the reduction of the data if the models violate the assumption; and (3) to come up with correlation factors which when multiplied by the results obtained under the SIS assumption will provide the results under the actual conditions.
    Keywords: AERODYNAMICS
    Type: Old Dominion Univ., The 1993 NASA-ODU American Society for Engineering Education (ASEE) Summer Faculty Fellowship Program; p 154-155
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  • 6
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    USB flow characteristics related to noise generation (1976)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The effects of nozzle and flap geometry on upper surface blown flow field characteristics related to noise generation were examined experimentally using static models. Flow attachment and spreading characteristics were observed using flow visualization techniques. Velocity and turbulence profiles in the trailing edge wake were measured using hot-wire anemometry, and the effects of the geometric variables on peak velocity and turbulence intensity were determined. It is shown that peak trailing edge velocity is a function of the ratio of flow length to modified hydraulic diameter.
    Keywords: AERODYNAMICS
    Type: NASA. Langley Res. Center Powered-Lift Aerodyn. and Acoustics; p 213-226
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  • 7
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    3-D Navier-Stokes analysis of crossing, glancing shocks/turbulent boundary layer interactions (1991)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Three dimensional viscous flow analysis is performed for a configuration where two crossing and glancing shocks interact with a turbulent boundary layer. A time marching 3-D full Navier-Stokes code, called PARC3D, is used to compute the flow field, and the solution is compared to the experimental data obtained at the NASA Lewis Research Center's 1 x 1 ft supersonic wind tunnel facility. The study is carried out as part of the continuing code assessment program in support of the generic hypersonic research at NASA Lewis. Detailed comparisons of static pressure fields and oil flow patterns are made with the corresponding solution on the wall containing the shock/boundary layer interaction in an effort to validate the code for hypersonic inlet applications.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 91-1758
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  • 8
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    Comparison of 3-D viscous flow computations of Mach 5 inlet with experimental data (1990)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: The accuracy of the time-marching three-dimensional Navier-Stokes code PARC3D (Cooper et al., 1987) is evaluated using experimental data on a Mach 5 mixed-compression inlet configuration, obtained in the 10 x 10-ft working section of the supersonic wind tunnel at NASA Lewis. The basic principles of the PARC3D computations (in which the inlet and tunnel geometry and the bleed conditions are fully modeled) and the experimental setup are described, and the results are presented in extensive graphs and characterized in detail. PARC3D is shown to give reasonably accurate predictions of the bleed-zone elimination of low-energy vortical flow due to shock/boundary-layer interaction; various possible improvements are briefly considered.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 90-0600
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  • 9
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    Application of an efficient hybrid scheme for aeroelastic analysis of advanced propellers (1990)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: An efficient 3-D hybrid scheme is applied for solving Euler equations to analyze advanced propellers. The scheme treats the spanwise direction semi-explicitly and the other two directions implicitly, without affecting the accuracy, as compared to a fully implicit scheme. This leads to a reduction in computer time and memory requirement. The calculated power coefficients for two advanced propellers, SR3 and SR7L, and various advanced ratios showed good correlation with experiment. Spanwise distribution of elemental power coefficient and steady pressure coefficient differences also showed good agreement with experiment. A study of the effect of structural flexibility on the performance of the advanced propellers showed that structural deformation due to centrifugal and aero loading should be included for better correlation.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 90-0028
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  • 10
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    Structural tailoring of aircraft engine blade subject to ice impact constraints (1992)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: In this paper, results are presented for the minimum weight design of SR2 unswept blade made of (Titanium/Graphite-Epoxy/Titanium)s fiber composite. The blade which is rotating at high RPM is subject to ice impact. The root chord length, blade thicknesses at five stations, and graphite-epoxy ply orientation are chosen as design variables. The design constraints are placed on the behavior variables: leading edge strain and root damage parameter due to ice impact, maximum post-impact bending stress at the root due to rotation, first three natural frequencies and resonance margin after impact. The method of feasible directions is employed to solve the inequality constrained minimization problem. The effect of ice speed and the ice impact location on the final design are discussed.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: AIAA PAPER 92-4710 , In: AIAA(USAF)NASA/OAI Symposium on Multidisciplinary Analysis and Optimization, 4th, Cleveland, OH, Sept. 21-23, 1992, Technical Papers. Pt. 1 (A93-20301 06-66); p. 197-206.
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