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Wahyu Kuntjoro Wirachman Wisnoe - One of the best experts on this subject based on the ideXlab platform.

  • Wind Tunnel experiments of UiTM's blended wing body (BWB) Baseline-II unmanned aerial vehicle (UAV) at low subsonic speed
    CSSR 2010 - 2010 International Conference on Science and Social Research, 2010
    Co-Authors: Firdaus Mohamad, Zurriati Mohd. Ali, Rizal Effendy M Nasir, Wahyu Kuntjoro Wirachman Wisnoe, Wahyu Kuntjoro, Nor F. Reduan
    Abstract:

    An experimental investigation is conducted to obtain aerodynamic characteristics and performance of a blended wing- body aircraft (BWB) under study by UiTM. The BWB design for unmanned aerial vehicle (UAV) known as “Baseline-II” is actually a completely-revised, redesigned version of “Baseline-I” BWB. The Baseline-II features have introduced a canard, a simpler planform, and slimmer body compared to its predecessor while maintaining wingspan. All tests are carried out in UiTM Low Speed Wind Tunnel using 1/6 scaled model of BWB at around 0.1 Mach number. The lift Coefficient (CL), the drag Coefficient (CD), the Pitching Moment Coefficient (CM), and the Lift-to-Drag (L/D) ratio curves are then plotted at various angles of attack, including CL versus CD polar to show the performance of the BWB. The results obtained will show the aerodynamic

  • Experimental results analysis for UiTM BWB baseline-I and baseline-II UAV running at 0.1 mach number
    International Journal of Mechanics, 2010
    Co-Authors: Wahyu Kuntjoro Wirachman Wisnoe, Firdaus Mohamad, Rizal Effendy Mohd Nasir, Nor F. Reduan, Wahyu Kuntjoro, Zurriati Ali
    Abstract:

    This paper presents results analysis for two models of UiTM Blended Wing Body (BWB) UAV tested in UiTM Low Speed Wind Tunnel. The first model is known as the BWB Baseline-I and the new model known as BWB Baseline-II. The Baseline-II has a simpler planform, broader-chord wing and slimmer body compared to its predecessor while maintaining wingspan. The wind-tunnel experiments were executed at around 0.1 Mach number or about 35m/s with 1/6 scaled down model. Baseline-I is designed with centre elevator while Baseline-II uses canard for Pitching motion purpose. The experiments were carried out at various elevator and canard deflection angles. The lift Coefficient, drag Coefficient, Pitching Moment Coefficient, L/D ratio and drag polar curves were plotted to show the performance of aircraft at various angle of attack. For zero elevator and canard deflection the results show similar trends in terms of lift curve, drag curve and Pitching Moment curves for both aircrafts.

  • Aerodynamics characteristic of UiTM's BWB UAV Baseline-II at different canard deflection angles at low Pitching angle
    CSSR 2010 - 2010 International Conference on Science and Social Research, 2010
    Co-Authors: Nor F. Reduan, Firdaus Mohamad, Wahyu Kuntjoro Wirachman Wisnoe, Rizal Effendy Mohd Nasir, Wahyu Kuntjoro, Zurriati Ali
    Abstract:

    This paper discusses the influence of canard deflection angle on the aerodynamics characteristic of a Blended Wing Body (BWB) Baseline-II aircraft obtained from wind tunnel test. Canard is added as longitudinal control. All tests are carried out in UiTM Low Speed Wind Tunnel using 1/6 scaled model at around 0.1 Mach number at several canard angle. The result of the lift Coefficient (CL), the drag Coefficient (CD), and the Pitching Moment Coefficient (CM), are plotted and analyze to show the characteristics of the BWB with different canard deflection angles.

  • Wind tunnel experiments and CFD analysis of Blended Wing Body (BWB) Unmanned Aerial Vehicle (UAV) at mach 0.1 and mach 0.3
    13th International Conference on Aerospace Sciences & Aviation Technology, 2009
    Co-Authors: Wahyu Kuntjoro Wirachman Wisnoe, Rizal Effendy Mohd Nasir, Rizal Effendy, Aman Mohd, Mohd Nasir, Wahyu Kuntjoro, A.m.i. Mamat
    Abstract:

    Tel : +(202) 24025292 – 24036138, Fax: +(202) 22621908 Abstract: This paper discusses the aerodynamics behavior of a baseline design of a Blended Wing Body (BWB) aircraft developed at MARA University of Technology (UiTM). Two methods of analysis are presented, i.e. Steady-state, three-dimensional Computational Fluid Dynamics (CFD) of the BWB at Mach 0.3 and Wind Tunnel experiments on 1/6 scaled half model of the BWB at Mach 0.1. In both methods of analysis, Lift Coefficient (CL), Drag Coefficient (CD) and Pitching Moment Coefficient (CM) are measured and compared at respective Mach numbers with respect to variation of angle of attack. Pressure contours and Mach number contours are plotted and the turbulence area is predicted, both extracted from CFD analysis. Visualization using mini tuft during wind tunnel tests is also executed to complete the analysis where the stall progression patterns can be clearly observed. The presented BWB UAV design here has achieved an unprecedented capability in terms of sustainability of flight at high angle of attack, low parasite drag Coefficient and decent maximum lift Coefficient. Some recommendations for future improvement of the BWB are given.

  • Aerodynamics of Blended Wing Body (BWB) Unmanned Aerial Vehicle (UAV) Using Computational Fluid Dynamics (CFD)
    Journal of Mechanical Engineering, 2008
    Co-Authors: A.m.i. Mamat, Wahyu Kuntjoro Wirachman Wisnoe, Rizal Effendy Mohd Nasir, Zulkiflee Ngah, Ramzyzan Ramly
    Abstract:

    A thorough understanding of the aerodynamic behaviour of Blended Wing Body (BWB) aircraft is important because of its high lift to drag ratio. The use of Computational Fluids Dynamics (CFD) has accelerated aerodynamic analysis of BWB aircraft. Steady-state, three-dimensional CFD calculations were made of the BWB model using the Spalart-Allmaras turbulence model. Comparisons of aerodynamic characteristics such as lift Coefficient, drag Coefficient, Pitching Moment Coefficient, pressure contours and Mach number contours were made both of two-dimensional aerofoil sections in the BWB model and a complete three-dimensional model. The lift Coefficient distributions along the body and wing span were analyzed. The effect of changing the angles of attack and aerofoil profiles were investigated. The BWB design presented here has achieved an unprecedented capability in terms of sustainability of flight at high angle of attack, low parasite drag Coefficient, efficient thrust required at optimum flight speed and acceptable margin of centre of gravity for trimmed flight at optimum speed without control surface interference

Nor F. Reduan - One of the best experts on this subject based on the ideXlab platform.

  • Wind Tunnel experiments of UiTM's blended wing body (BWB) Baseline-II unmanned aerial vehicle (UAV) at low subsonic speed
    CSSR 2010 - 2010 International Conference on Science and Social Research, 2010
    Co-Authors: Firdaus Mohamad, Zurriati Mohd. Ali, Rizal Effendy M Nasir, Wahyu Kuntjoro Wirachman Wisnoe, Wahyu Kuntjoro, Nor F. Reduan
    Abstract:

    An experimental investigation is conducted to obtain aerodynamic characteristics and performance of a blended wing- body aircraft (BWB) under study by UiTM. The BWB design for unmanned aerial vehicle (UAV) known as “Baseline-II” is actually a completely-revised, redesigned version of “Baseline-I” BWB. The Baseline-II features have introduced a canard, a simpler planform, and slimmer body compared to its predecessor while maintaining wingspan. All tests are carried out in UiTM Low Speed Wind Tunnel using 1/6 scaled model of BWB at around 0.1 Mach number. The lift Coefficient (CL), the drag Coefficient (CD), the Pitching Moment Coefficient (CM), and the Lift-to-Drag (L/D) ratio curves are then plotted at various angles of attack, including CL versus CD polar to show the performance of the BWB. The results obtained will show the aerodynamic

  • Experimental results analysis for UiTM BWB baseline-I and baseline-II UAV running at 0.1 mach number
    International Journal of Mechanics, 2010
    Co-Authors: Wahyu Kuntjoro Wirachman Wisnoe, Firdaus Mohamad, Rizal Effendy Mohd Nasir, Nor F. Reduan, Wahyu Kuntjoro, Zurriati Ali
    Abstract:

    This paper presents results analysis for two models of UiTM Blended Wing Body (BWB) UAV tested in UiTM Low Speed Wind Tunnel. The first model is known as the BWB Baseline-I and the new model known as BWB Baseline-II. The Baseline-II has a simpler planform, broader-chord wing and slimmer body compared to its predecessor while maintaining wingspan. The wind-tunnel experiments were executed at around 0.1 Mach number or about 35m/s with 1/6 scaled down model. Baseline-I is designed with centre elevator while Baseline-II uses canard for Pitching motion purpose. The experiments were carried out at various elevator and canard deflection angles. The lift Coefficient, drag Coefficient, Pitching Moment Coefficient, L/D ratio and drag polar curves were plotted to show the performance of aircraft at various angle of attack. For zero elevator and canard deflection the results show similar trends in terms of lift curve, drag curve and Pitching Moment curves for both aircrafts.

  • Aerodynamics characteristic of UiTM's BWB UAV Baseline-II at different canard deflection angles at low Pitching angle
    CSSR 2010 - 2010 International Conference on Science and Social Research, 2010
    Co-Authors: Nor F. Reduan, Firdaus Mohamad, Wahyu Kuntjoro Wirachman Wisnoe, Rizal Effendy Mohd Nasir, Wahyu Kuntjoro, Zurriati Ali
    Abstract:

    This paper discusses the influence of canard deflection angle on the aerodynamics characteristic of a Blended Wing Body (BWB) Baseline-II aircraft obtained from wind tunnel test. Canard is added as longitudinal control. All tests are carried out in UiTM Low Speed Wind Tunnel using 1/6 scaled model at around 0.1 Mach number at several canard angle. The result of the lift Coefficient (CL), the drag Coefficient (CD), and the Pitching Moment Coefficient (CM), are plotted and analyze to show the characteristics of the BWB with different canard deflection angles.

Wahyu Kuntjoro - One of the best experts on this subject based on the ideXlab platform.

  • Wind Tunnel experiments of UiTM's blended wing body (BWB) Baseline-II unmanned aerial vehicle (UAV) at low subsonic speed
    CSSR 2010 - 2010 International Conference on Science and Social Research, 2010
    Co-Authors: Firdaus Mohamad, Zurriati Mohd. Ali, Rizal Effendy M Nasir, Wahyu Kuntjoro Wirachman Wisnoe, Wahyu Kuntjoro, Nor F. Reduan
    Abstract:

    An experimental investigation is conducted to obtain aerodynamic characteristics and performance of a blended wing- body aircraft (BWB) under study by UiTM. The BWB design for unmanned aerial vehicle (UAV) known as “Baseline-II” is actually a completely-revised, redesigned version of “Baseline-I” BWB. The Baseline-II features have introduced a canard, a simpler planform, and slimmer body compared to its predecessor while maintaining wingspan. All tests are carried out in UiTM Low Speed Wind Tunnel using 1/6 scaled model of BWB at around 0.1 Mach number. The lift Coefficient (CL), the drag Coefficient (CD), the Pitching Moment Coefficient (CM), and the Lift-to-Drag (L/D) ratio curves are then plotted at various angles of attack, including CL versus CD polar to show the performance of the BWB. The results obtained will show the aerodynamic

  • Experimental results analysis for UiTM BWB baseline-I and baseline-II UAV running at 0.1 mach number
    International Journal of Mechanics, 2010
    Co-Authors: Wahyu Kuntjoro Wirachman Wisnoe, Firdaus Mohamad, Rizal Effendy Mohd Nasir, Nor F. Reduan, Wahyu Kuntjoro, Zurriati Ali
    Abstract:

    This paper presents results analysis for two models of UiTM Blended Wing Body (BWB) UAV tested in UiTM Low Speed Wind Tunnel. The first model is known as the BWB Baseline-I and the new model known as BWB Baseline-II. The Baseline-II has a simpler planform, broader-chord wing and slimmer body compared to its predecessor while maintaining wingspan. The wind-tunnel experiments were executed at around 0.1 Mach number or about 35m/s with 1/6 scaled down model. Baseline-I is designed with centre elevator while Baseline-II uses canard for Pitching motion purpose. The experiments were carried out at various elevator and canard deflection angles. The lift Coefficient, drag Coefficient, Pitching Moment Coefficient, L/D ratio and drag polar curves were plotted to show the performance of aircraft at various angle of attack. For zero elevator and canard deflection the results show similar trends in terms of lift curve, drag curve and Pitching Moment curves for both aircrafts.

  • Aerodynamics characteristic of UiTM's BWB UAV Baseline-II at different canard deflection angles at low Pitching angle
    CSSR 2010 - 2010 International Conference on Science and Social Research, 2010
    Co-Authors: Nor F. Reduan, Firdaus Mohamad, Wahyu Kuntjoro Wirachman Wisnoe, Rizal Effendy Mohd Nasir, Wahyu Kuntjoro, Zurriati Ali
    Abstract:

    This paper discusses the influence of canard deflection angle on the aerodynamics characteristic of a Blended Wing Body (BWB) Baseline-II aircraft obtained from wind tunnel test. Canard is added as longitudinal control. All tests are carried out in UiTM Low Speed Wind Tunnel using 1/6 scaled model at around 0.1 Mach number at several canard angle. The result of the lift Coefficient (CL), the drag Coefficient (CD), and the Pitching Moment Coefficient (CM), are plotted and analyze to show the characteristics of the BWB with different canard deflection angles.

  • Wind tunnel experiments and CFD analysis of Blended Wing Body (BWB) Unmanned Aerial Vehicle (UAV) at mach 0.1 and mach 0.3
    13th International Conference on Aerospace Sciences & Aviation Technology, 2009
    Co-Authors: Wahyu Kuntjoro Wirachman Wisnoe, Rizal Effendy Mohd Nasir, Rizal Effendy, Aman Mohd, Mohd Nasir, Wahyu Kuntjoro, A.m.i. Mamat
    Abstract:

    Tel : +(202) 24025292 – 24036138, Fax: +(202) 22621908 Abstract: This paper discusses the aerodynamics behavior of a baseline design of a Blended Wing Body (BWB) aircraft developed at MARA University of Technology (UiTM). Two methods of analysis are presented, i.e. Steady-state, three-dimensional Computational Fluid Dynamics (CFD) of the BWB at Mach 0.3 and Wind Tunnel experiments on 1/6 scaled half model of the BWB at Mach 0.1. In both methods of analysis, Lift Coefficient (CL), Drag Coefficient (CD) and Pitching Moment Coefficient (CM) are measured and compared at respective Mach numbers with respect to variation of angle of attack. Pressure contours and Mach number contours are plotted and the turbulence area is predicted, both extracted from CFD analysis. Visualization using mini tuft during wind tunnel tests is also executed to complete the analysis where the stall progression patterns can be clearly observed. The presented BWB UAV design here has achieved an unprecedented capability in terms of sustainability of flight at high angle of attack, low parasite drag Coefficient and decent maximum lift Coefficient. Some recommendations for future improvement of the BWB are given.

A.m.i. Mamat - One of the best experts on this subject based on the ideXlab platform.

  • Wind tunnel experiments and CFD analysis of Blended Wing Body (BWB) Unmanned Aerial Vehicle (UAV) at mach 0.1 and mach 0.3
    13th International Conference on Aerospace Sciences & Aviation Technology, 2009
    Co-Authors: Wahyu Kuntjoro Wirachman Wisnoe, Rizal Effendy Mohd Nasir, Rizal Effendy, Aman Mohd, Mohd Nasir, Wahyu Kuntjoro, A.m.i. Mamat
    Abstract:

    Tel : +(202) 24025292 – 24036138, Fax: +(202) 22621908 Abstract: This paper discusses the aerodynamics behavior of a baseline design of a Blended Wing Body (BWB) aircraft developed at MARA University of Technology (UiTM). Two methods of analysis are presented, i.e. Steady-state, three-dimensional Computational Fluid Dynamics (CFD) of the BWB at Mach 0.3 and Wind Tunnel experiments on 1/6 scaled half model of the BWB at Mach 0.1. In both methods of analysis, Lift Coefficient (CL), Drag Coefficient (CD) and Pitching Moment Coefficient (CM) are measured and compared at respective Mach numbers with respect to variation of angle of attack. Pressure contours and Mach number contours are plotted and the turbulence area is predicted, both extracted from CFD analysis. Visualization using mini tuft during wind tunnel tests is also executed to complete the analysis where the stall progression patterns can be clearly observed. The presented BWB UAV design here has achieved an unprecedented capability in terms of sustainability of flight at high angle of attack, low parasite drag Coefficient and decent maximum lift Coefficient. Some recommendations for future improvement of the BWB are given.

  • Aerodynamics of Blended Wing Body (BWB) Unmanned Aerial Vehicle (UAV) Using Computational Fluid Dynamics (CFD)
    Journal of Mechanical Engineering, 2008
    Co-Authors: A.m.i. Mamat, Wahyu Kuntjoro Wirachman Wisnoe, Rizal Effendy Mohd Nasir, Zulkiflee Ngah, Ramzyzan Ramly
    Abstract:

    A thorough understanding of the aerodynamic behaviour of Blended Wing Body (BWB) aircraft is important because of its high lift to drag ratio. The use of Computational Fluids Dynamics (CFD) has accelerated aerodynamic analysis of BWB aircraft. Steady-state, three-dimensional CFD calculations were made of the BWB model using the Spalart-Allmaras turbulence model. Comparisons of aerodynamic characteristics such as lift Coefficient, drag Coefficient, Pitching Moment Coefficient, pressure contours and Mach number contours were made both of two-dimensional aerofoil sections in the BWB model and a complete three-dimensional model. The lift Coefficient distributions along the body and wing span were analyzed. The effect of changing the angles of attack and aerofoil profiles were investigated. The BWB design presented here has achieved an unprecedented capability in terms of sustainability of flight at high angle of attack, low parasite drag Coefficient, efficient thrust required at optimum flight speed and acceptable margin of centre of gravity for trimmed flight at optimum speed without control surface interference

Firdaus Mohamad - One of the best experts on this subject based on the ideXlab platform.

  • Wind Tunnel experiments of UiTM's blended wing body (BWB) Baseline-II unmanned aerial vehicle (UAV) at low subsonic speed
    CSSR 2010 - 2010 International Conference on Science and Social Research, 2010
    Co-Authors: Firdaus Mohamad, Zurriati Mohd. Ali, Rizal Effendy M Nasir, Wahyu Kuntjoro Wirachman Wisnoe, Wahyu Kuntjoro, Nor F. Reduan
    Abstract:

    An experimental investigation is conducted to obtain aerodynamic characteristics and performance of a blended wing- body aircraft (BWB) under study by UiTM. The BWB design for unmanned aerial vehicle (UAV) known as “Baseline-II” is actually a completely-revised, redesigned version of “Baseline-I” BWB. The Baseline-II features have introduced a canard, a simpler planform, and slimmer body compared to its predecessor while maintaining wingspan. All tests are carried out in UiTM Low Speed Wind Tunnel using 1/6 scaled model of BWB at around 0.1 Mach number. The lift Coefficient (CL), the drag Coefficient (CD), the Pitching Moment Coefficient (CM), and the Lift-to-Drag (L/D) ratio curves are then plotted at various angles of attack, including CL versus CD polar to show the performance of the BWB. The results obtained will show the aerodynamic

  • Experimental results analysis for UiTM BWB baseline-I and baseline-II UAV running at 0.1 mach number
    International Journal of Mechanics, 2010
    Co-Authors: Wahyu Kuntjoro Wirachman Wisnoe, Firdaus Mohamad, Rizal Effendy Mohd Nasir, Nor F. Reduan, Wahyu Kuntjoro, Zurriati Ali
    Abstract:

    This paper presents results analysis for two models of UiTM Blended Wing Body (BWB) UAV tested in UiTM Low Speed Wind Tunnel. The first model is known as the BWB Baseline-I and the new model known as BWB Baseline-II. The Baseline-II has a simpler planform, broader-chord wing and slimmer body compared to its predecessor while maintaining wingspan. The wind-tunnel experiments were executed at around 0.1 Mach number or about 35m/s with 1/6 scaled down model. Baseline-I is designed with centre elevator while Baseline-II uses canard for Pitching motion purpose. The experiments were carried out at various elevator and canard deflection angles. The lift Coefficient, drag Coefficient, Pitching Moment Coefficient, L/D ratio and drag polar curves were plotted to show the performance of aircraft at various angle of attack. For zero elevator and canard deflection the results show similar trends in terms of lift curve, drag curve and Pitching Moment curves for both aircrafts.

  • Aerodynamics characteristic of UiTM's BWB UAV Baseline-II at different canard deflection angles at low Pitching angle
    CSSR 2010 - 2010 International Conference on Science and Social Research, 2010
    Co-Authors: Nor F. Reduan, Firdaus Mohamad, Wahyu Kuntjoro Wirachman Wisnoe, Rizal Effendy Mohd Nasir, Wahyu Kuntjoro, Zurriati Ali
    Abstract:

    This paper discusses the influence of canard deflection angle on the aerodynamics characteristic of a Blended Wing Body (BWB) Baseline-II aircraft obtained from wind tunnel test. Canard is added as longitudinal control. All tests are carried out in UiTM Low Speed Wind Tunnel using 1/6 scaled model at around 0.1 Mach number at several canard angle. The result of the lift Coefficient (CL), the drag Coefficient (CD), and the Pitching Moment Coefficient (CM), are plotted and analyze to show the characteristics of the BWB with different canard deflection angles.