標(biāo)題: Titlebook: Design and Development of Aerospace Vehicles and Propulsion Systems; Proceedings of SAROD S. Kishore Kumar,Indira Narayanaswamy,V. Ramesh C [打印本頁] 作者: Coenzyme 時間: 2025-3-21 19:15
書目名稱Design and Development of Aerospace Vehicles and Propulsion Systems影響因子(影響力)
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書目名稱Design and Development of Aerospace Vehicles and Propulsion Systems讀者反饋
書目名稱Design and Development of Aerospace Vehicles and Propulsion Systems讀者反饋學(xué)科排名
作者: bacteria 時間: 2025-3-21 20:50 作者: Rankle 時間: 2025-3-22 04:02 作者: Isometric 時間: 2025-3-22 08:35
Wechselspannung und Wechselstrom, been advantageous in the study of aero-elastic behavior of lifting surfaces. Preliminary design of an UAV requires detailed understanding of aerodynamic and structural operational boundaries; to arrive at an optimal wing. High aspect ratio wings are being employed in Medium Altitude Long Endurance 作者: 痛苦一生 時間: 2025-3-22 10:23
,Feldeffekttransistor, MOSFET und R?hren,tion for the study arises from aeroelastic studies of turbomachinery blades, where the unsteady forces acting on a blade due to different sources is examined. In order to identify the root cause of the various phenomena affecting the aeroelastic stability, it is necessary to observe the effect of on作者: 預(yù)示 時間: 2025-3-22 15:10 作者: 預(yù)示 時間: 2025-3-22 19:04
https://doi.org/10.1007/978-3-658-07874-4ltered external flow contributes to an additional force on the vehicle in addition to the jet thrust thereby effecting its performance. In this study, numerical simulations were carried out to estimate the effect of injection location and body attitude on the overall performance of a Reaction Contro作者: Infirm 時間: 2025-3-23 01:07
Ermittlung von Zinsstrukturkurven retaining the same gap and aspect ratio to explicitly decipher the role of chord on grid fin aerodynamics through numerical analysis. Solver validation is followed by comprehensive examination of the pertinent aerodynamic coefficient results associated with different grid fin chord variants. The st作者: 殺人 時間: 2025-3-23 03:14 作者: nauseate 時間: 2025-3-23 08:21 作者: periodontitis 時間: 2025-3-23 13:03 作者: Oration 時間: 2025-3-23 17:38
https://doi.org/10.1007/978-3-658-28614-9 in group I showed normal shock train oscillations and its structures at different duct locations. Group II studied about the shock oscillation when it stands on a hybrid micro vortex generator, while group III studied moving normal shock train. The shock structures have been visualized using high-s作者: 公司 時間: 2025-3-23 21:17 作者: 未開化 時間: 2025-3-24 00:50 作者: atopic 時間: 2025-3-24 03:28
Ermittlung von Zinsstrukturkurvenis often carried out using low speed wind tunnel tests. Presence of tunnel walls affect aerodynamic coefficients due to the blockage introduced by the model to the flow. The effect of blockage is investigated in the current study through CFD simulations with and without wind tunnel walls on a launch作者: 仲裁者 時間: 2025-3-24 08:20 作者: 狗窩 時間: 2025-3-24 12:58
Mathematische Zeichen und Symbole,undary layer. The local intensification of heat transfer rates in the vicinity of the protuberance is considered as the main focus of the study. The effect of separated and unseparated boundary layer is considered by varying the protuberance angle. The results are compared with available experimenta作者: 代理人 時間: 2025-3-24 16:58 作者: Accrue 時間: 2025-3-24 21:41
Formelsammlung Wirtschaftsmathematik Light jets often cruise at high subsonic Mach numbers enabling greater range. Consequently, the drawback associated with high Mach number flight is that it leads to the deterioration of the aircraft’s aerodynamic characteristics. Aerodynamic optimization of a typical transonic wing was performed to作者: 引起 時間: 2025-3-25 01:52
Design and Development of Aerospace Vehicles and Propulsion Systems978-981-15-9601-8Series ISSN 2195-4356 Series E-ISSN 2195-4364 作者: 津貼 時間: 2025-3-25 03:40
https://doi.org/10.1007/978-981-15-9601-8Aerodynamics of Aerospace Vehicles; Conceptual Design of Aircraft; Turbomachinery Flows; Intake Aerodyn作者: Interregnum 時間: 2025-3-25 11:01 作者: DRAFT 時間: 2025-3-25 13:45
S. Kishore Kumar,Indira Narayanaswamy,V. RameshCovers aerodynamics of aerospace vehicles.Special focus on Stealth in Aerospace Design.Looks at all aspects vehicle and propulsion system design作者: elucidate 時間: 2025-3-25 16:56 作者: Innocence 時間: 2025-3-26 00:03
2195-4356 signThis book presents selected papers presented in the Symposium on Applied Aerodynamics and Design of Aerospace Vehicles (SAROD 2018), which was? jointly organized? by Aeronautical Development Agency (the nodal agency for the design and development of combat aircraft in India),? Gas-Turbine Resear作者: Firefly 時間: 2025-3-26 04:04
https://doi.org/10.1007/978-3-8348-8116-8etric study is carried out for supersonic flow past a compression–decompression ramp (CDR), to determine the ramp inclination angle that minimizes the adverse effect of separated flow. The inclination angle below which weak interaction occurs is obtained from the numerical simulations.作者: 我不重要 時間: 2025-3-26 07:32
,Parametric Study of Turbulent Flow Past a Compression–Decompression Ramp,etric study is carried out for supersonic flow past a compression–decompression ramp (CDR), to determine the ramp inclination angle that minimizes the adverse effect of separated flow. The inclination angle below which weak interaction occurs is obtained from the numerical simulations.作者: CORD 時間: 2025-3-26 09:26
Ermittlung von Zinsstrukturkurventitude variation on the aerodynamics of the launch vehicle during hot separation. Two different trajectories (or altitudes) are studied and the effect on the aerodynamic coefficients is quantified. The paper presents in detail about the simulated conditions, the variation in aerodynamic coefficients and the complex flow-field involved.作者: Ointment 時間: 2025-3-26 12:55 作者: 披肩 時間: 2025-3-26 16:53
Ermittlung von Zinsstrukturkurven vehicle configuration in the presence of launch pad and umbilical tower (UT). It is seen that the aerodynamic characteristics are significantly influenced by the presence of wind tunnel walls. Even though the model blockage is 4%, variation of 8.5% is seen in?total force coefficients.作者: Magnitude 時間: 2025-3-27 00:32 作者: MUMP 時間: 2025-3-27 01:55 作者: Bph773 時間: 2025-3-27 05:46
https://doi.org/10.1007/978-3-662-64836-0e search of optima. Expected improvement strategy is used to update the surrogate at every iteration, and optimization is terminated once the convergence criterion is met. The objective function improvement for maximizing . and maximizing (./.) is 18.08% and 38.70%, respectively.作者: 廢墟 時間: 2025-3-27 09:48 作者: Optic-Disk 時間: 2025-3-27 15:12 作者: 座右銘 時間: 2025-3-27 17:55
Conference proceedings 2021y organized? by Aeronautical Development Agency (the nodal agency for the design and development of combat aircraft in India),? Gas-Turbine Research Establishment (responsible for design and development of gas turbine engines for military applications), and CSIR-National Aerospace Laboratories (invo作者: evaculate 時間: 2025-3-28 00:05
Sensitivity of Altitude Variation on Aerodynamics of a Typical Launch Vehicle During Hot Separationtitude variation on the aerodynamics of the launch vehicle during hot separation. Two different trajectories (or altitudes) are studied and the effect on the aerodynamic coefficients is quantified. The paper presents in detail about the simulated conditions, the variation in aerodynamic coefficients and the complex flow-field involved.作者: 機械 時間: 2025-3-28 02:08 作者: pulmonary 時間: 2025-3-28 10:02
Investigation of Wind Tunnel Blockage Effect on Liftoff Aerodynamics of a Launch Vehicle Through Op vehicle configuration in the presence of launch pad and umbilical tower (UT). It is seen that the aerodynamic characteristics are significantly influenced by the presence of wind tunnel walls. Even though the model blockage is 4%, variation of 8.5% is seen in?total force coefficients.作者: Anemia 時間: 2025-3-28 13:32
RANS Computations of Hypersonic Interference Heating on Flat Surface with Protuberances,l data. The maximum heat transfer rate, a major design parameter, is found to be fairly predicted by computations. However, accurate prediction of parameters such as upstream separation length and heat flux distribution requires further research and calibration of available turbulence models.作者: hyperuricemia 時間: 2025-3-28 17:56
Conference proceedings 2021of aerodynamicists in India as well as abroad in Aerospace Vehicle Design, Gas Turbine Engines, Missiles and related areas. It is a useful volume for researchers, professionals and students interested in diversified areas of aerospace engineering.作者: 值得贊賞 時間: 2025-3-28 20:19
Wolfgang Grundmann,Bernd Ludereroming boundary layer velocity fluctuations (upstream parameter) is corelated to the shock foot oscillation and the separation bubble (downstream parameter) is correlated to the shock motion for the forward-facing step of step height equals twice the incoming boundary thickness.作者: LAY 時間: 2025-3-28 23:02
Observation of Low-Frequency Shock Oscillation Over a Forward-Facing Step,oming boundary layer velocity fluctuations (upstream parameter) is corelated to the shock foot oscillation and the separation bubble (downstream parameter) is correlated to the shock motion for the forward-facing step of step height equals twice the incoming boundary thickness.作者: Ordnance 時間: 2025-3-29 04:06 作者: 平靜生活 時間: 2025-3-29 08:00 作者: atopic 時間: 2025-3-29 13:31
Validation of Numerical Analysis Results for Pusher Configured Turboprop Engine Air Intake,sses particular to the engine installation. These installation losses must be determined in order to create the final aircraft power setting charts. During the course of configuration development, design analysis is a must to ensure that the proposed design will perform the intended operation within作者: 常到 時間: 2025-3-29 15:49
,Aero-elastic Analysis of High Aspect Ratio UAV Wing—Based on Two-Way Fluid Structure Interaction, been advantageous in the study of aero-elastic behavior of lifting surfaces. Preliminary design of an UAV requires detailed understanding of aerodynamic and structural operational boundaries; to arrive at an optimal wing. High aspect ratio wings are being employed in Medium Altitude Long Endurance 作者: Coma704 時間: 2025-3-29 20:29 作者: 樂章 時間: 2025-3-30 00:19
Effect of Incoming Wakes on Losses of a Low-Pressure Turbine of a Gas Turbine Engine,in J Turbomach 135/011010, [.]). LPT can contribute as much as 30% of the weight of an aero engine (Sondergaard et al. in Toward the expansion of low-pressure turbine airfoil design space, [.]; Curtis et al. in J Turbomach 119(3), [.]). Aerofoils of modern LPT blades are subjected to increasingly st作者: scrape 時間: 2025-3-30 04:22 作者: 四海為家的人 時間: 2025-3-30 10:40
Effect of Chord Variation on Subsonic Aerodynamics of Grid Fins, retaining the same gap and aspect ratio to explicitly decipher the role of chord on grid fin aerodynamics through numerical analysis. Solver validation is followed by comprehensive examination of the pertinent aerodynamic coefficient results associated with different grid fin chord variants. The st作者: Demonstrate 時間: 2025-3-30 14:35 作者: Jacket 時間: 2025-3-30 17:24
Theoretical Design and Performance Evaluation of a Two-Ramp and a Three-Ramp Rectangular Mixed Compr the theoretical design stage, a 1D optimization criterion has been used to fix the ramp angles for theoretical maximum total pressure recovery (TPR), at on-design M 2.9 (shock-on-lip). Two different ramp designs (two and three ramps) have been considered for optimization, to find their effect on t作者: 不如屎殼郎 時間: 2025-3-30 22:57 作者: PLUMP 時間: 2025-3-31 01:12
Normal Shock Dynamics in Internal Supersonic Flows, in group I showed normal shock train oscillations and its structures at different duct locations. Group II studied about the shock oscillation when it stands on a hybrid micro vortex generator, while group III studied moving normal shock train. The shock structures have been visualized using high-s作者: AER 時間: 2025-3-31 07:58 作者: incision 時間: 2025-3-31 13:05
3D Computational Studies of Flapping Wing in Frontal Gusty Shear Flow, A rigid wing with semi-elliptical wing planform with asymmetric 1 DoF flapping kinematics was exposed to a gusty shear flow. The shear gradient of the flow was varied from ?10 to +10 in steps of 5. Computation studies were carried out for Re?=?150 which lies in the typical flight Reynolds number ra作者: FLAIL 時間: 2025-3-31 13:40
Investigation of Wind Tunnel Blockage Effect on Liftoff Aerodynamics of a Launch Vehicle Through Opis often carried out using low speed wind tunnel tests. Presence of tunnel walls affect aerodynamic coefficients due to the blockage introduced by the model to the flow. The effect of blockage is investigated in the current study through CFD simulations with and without wind tunnel walls on a launch作者: 無節(jié)奏 時間: 2025-3-31 19:11
Observation of Low-Frequency Shock Oscillation Over a Forward-Facing Step, (FFS) of step height equals twice the oncoming boundary layer thickness. Particle Image Velocimetry (PIV) is the primary methodology used to study the unsteady shock oscillation phenomena. Prior studies show shock oscillates one or two orders smaller than the characteristics frequency of the incomi作者: BANAL 時間: 2025-3-31 23:08 作者: Eeg332 時間: 2025-4-1 05:01
Multi-fidelity Aerodynamic Optimization of an Airfoil at a Transitional Low Reynolds Number,sitional low Reynolds number (Re?=?5?×?10.) using surrogate-based optimization technique. Bezier curves are used to parameterize the airfoil. Latin hypercube sampling (LHS) technique is used to sample the initial set of samples. The aerodynamic response is estimated using low- and high-fidelity data作者: 獸群 時間: 2025-4-1 06:52
Aerodynamic Optimization of Transonic Wing for Light Jet Aircraft, Light jets often cruise at high subsonic Mach numbers enabling greater range. Consequently, the drawback associated with high Mach number flight is that it leads to the deterioration of the aircraft’s aerodynamic characteristics. Aerodynamic optimization of a typical transonic wing was performed to作者: 舊石器 時間: 2025-4-1 13:20 作者: Intercept 時間: 2025-4-1 14:47
