Wind tunnel testing is the only source through which Computational Fluid Dynamics results can be ... more Wind tunnel testing is the only source through which Computational Fluid Dynamics results can be correlated and justified. Numerical simulation is easy to authenticate aerodynamics analysis and theories of Aerodynamics provided they are carried out in judicial manner. The research work is focused on testing of a scaled down model of store carrying rack in a Subsonic Wind Tunnel facility held at College of Aeronautical Engineering, National University of Sciences &Technology, Risalpur, Pakistan. Main theme of this novel work is to correlate Computational Fluid Dynamics results of store carrying rack with the experimental data of Subsonic Wind Tunnel for which 1:2 scale down model is manufactured using five axis milling machine held with Pakistan Aeronautical Complex, Kamra. The store carrying rack is tested at varying speeds and angles of attack. Non-dimensionalized aerodynamic performance parameters are calculated and compared with low turbulence level of wind tunnel tests. The rese...
Purpose of this research work is to model and analyze store carrying racks of a fighter aircraft ... more Purpose of this research work is to model and analyze store carrying racks of a fighter aircraft with a purpose of improving their aerodynamic performance. Two store carrying racks used in this research are originally designed to carry external payload of up to 3000lbs and are actively used in aviation industry. This research is focused towards obtaining aerodynamic performance parameters of both racks under actual flight conditions using computational fluid dynamics techniques (CFD). Later on design modifications, validated by CFD, will be suggested for improving aerodynamic performance of the racks. For analysis, geometry features of both racks were obtained using Laser Coordinate Measuring Machine (CMM). Lofted Protrusion technique was then used in available CAD software to convert sketches into smooth surface. The modeled geometries were imported and meshed in ICEM CFD.Prism layer is used to capture flow physics inside viscous boundary layer region. The optimized mesh has a 30 ≤...
The purpose of this research is to visualize, understand and analyze the flow physics around the ... more The purpose of this research is to visualize, understand and analyze the flow physics around the cantilevered wing of a small unmanned aerial vehicle. The aerodynamic performance parameters are evaluated for different configurations (with and without payload). Flow around the wing at cruise is considered to be steady, incompressible, fully turbulent and viscous, therefore same conditions have been imposed during flow analysis in commercially available software ANSYSInc. 13.0. The geometric data of the wing was acquired using manual measurement techniques. The data was imported in Solid Edge® software where after cleaning wing modeling was done. Surface and volume meshing was carried out using unstructured meshing scheme. Aerodynamic analysis is carried out in Fluent® software by declaring the wing surface as no slip wall. The inlet and outlet of the domain are modeled as pressure inlet/outlet. The wing is cantilevered from one of the domain boundary modeled as wall. The aerodynamic ...
Wind tunnel testing is the only source through which Computational Fluid Dynamics results can be ... more Wind tunnel testing is the only source through which Computational Fluid Dynamics results can be correlated and justified. Numerical simulation is easy to authenticate aerodynamics analysis and theories of Aerodynamics provided they are carried out in judicial manner. The research work is focused on testing of a scaled down model of store carrying rack in a Subsonic Wind Tunnel facility held at College of Aeronautical Engineering, National University of Sciences &Technology, Risalpur, Pakistan. Main theme of this novel work is to correlate Computational Fluid Dynamics results of store carrying rack with the experimental data of Subsonic Wind Tunnel for which 1:2 scale down model is manufactured using five axis milling machine held with Pakistan Aeronautical Complex, Kamra. The store carrying rack is tested at varying speeds and angles of attack. Non-dimensionalized aerodynamic performance parameters are calculated and compared with low turbulence level of wind tunnel tests. The rese...
Purpose of this research work is to model and analyze store carrying racks of a fighter aircraft ... more Purpose of this research work is to model and analyze store carrying racks of a fighter aircraft with a purpose of improving their aerodynamic performance. Two store carrying racks used in this research are originally designed to carry external payload of up to 3000lbs and are actively used in aviation industry. This research is focused towards obtaining aerodynamic performance parameters of both racks under actual flight conditions using computational fluid dynamics techniques (CFD). Later on design modifications, validated by CFD, will be suggested for improving aerodynamic performance of the racks. For analysis, geometry features of both racks were obtained using Laser Coordinate Measuring Machine (CMM). Lofted Protrusion technique was then used in available CAD software to convert sketches into smooth surface. The modeled geometries were imported and meshed in ICEM CFD.Prism layer is used to capture flow physics inside viscous boundary layer region. The optimized mesh has a 30 ≤...
The purpose of this research is to visualize, understand and analyze the flow physics around the ... more The purpose of this research is to visualize, understand and analyze the flow physics around the cantilevered wing of a small unmanned aerial vehicle. The aerodynamic performance parameters are evaluated for different configurations (with and without payload). Flow around the wing at cruise is considered to be steady, incompressible, fully turbulent and viscous, therefore same conditions have been imposed during flow analysis in commercially available software ANSYSInc. 13.0. The geometric data of the wing was acquired using manual measurement techniques. The data was imported in Solid Edge® software where after cleaning wing modeling was done. Surface and volume meshing was carried out using unstructured meshing scheme. Aerodynamic analysis is carried out in Fluent® software by declaring the wing surface as no slip wall. The inlet and outlet of the domain are modeled as pressure inlet/outlet. The wing is cantilevered from one of the domain boundary modeled as wall. The aerodynamic ...
Uploads
Papers by Kashif Mehmood