Computational and Analytical Investigation of Aerodynamic Derivatives of Similitude Delta Wing Model at Hypersonic Speeds

Bashir, Musavir; Khan, Sher Afghan; Azam, Qummare; Janvekar, Ayub Ahmed

doi:10.14716/ijtech.v8i3.6319

Cited by 4 publications

(3 citation statements)

References 5 publications

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“…Batasan masalah yang saya ambil dalam penelitian ini adalah sudut serang airfoil NACA 0013 terhadap garis horizontal sebesar 0 o , 3 o , 6 o , 9 o , 12 o , 15 o , 18 o , 21 o , dan 24 o . Penelitian sebelumnya dilakukan Oleh Musavir Bashir, S.A. Khan, Qummare Azam, Ayub Ahmed Janvekar [11] yaitu tentang sudut serang sayap pesawat type NACA 4 Digit dengan seri yang berbeda. Penelitian terdahulu juga dilakukan oleh Kang Pyo Cho, Seung Hwan Jeong, Dany Perwita Sari [10] yang membahas pengaruh gaya Lift terhadap sudut serang Pesawat terbang NACA 4 Digit Seri yang berbeda juga.…”

Section: Pendahuluanunclassified

Pengaruh Gaya Lift Terhadap Sudut Serang Airfoil Naca 0013 dengan Ansys Fluent

Hidayat

Nofendri

2019

Prosid Sem Nas Teknoka

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Dunia Kedirgantaraan di Indonesia yang semakin lesu, butuh Peneliti-peneliti bertalenta di bidang Aerodinamika agar bisa mengangkat kembali nama baik dan harga diri Bangsa. Penelitian saya kali ini bertemakan studi bidang aerodinamika dari potongan melintang sayap pesawat terbang type Airfoil NACA 0013 dengan mencari sudut serang yang tepat untuk Take Off. Tujuan Penelitian ini adalah untuk menentukan sudut serang terbaik dari Pesawat saat Take Off. Metode yang saya gunakan dengan penerapan Simulasi CFD menggunakan Software ANSYS-Fluent versi 14.5 dengan Workbench. Hasil yang di dapat dari penelitian ini akan ditabulasikan dalam tabel dan grafik hubungan antara Gaya Lift terhadap Sudut Serang. Dengan mengambil variabel sudut serang sebanyak 9 variabel yaitu 0o, 3o, 6o, 9o, 12o, 15o, 18o, 21o, dan 24o. Dari hasil Simulasi didapat Sudut Serang terbaik untuk tipe NACA 0013 adalah 21o dengan harga Gaya Lift sebesar 61,650 N.

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Section: Pendahuluanunclassified

Pengaruh Gaya Lift Terhadap Sudut Serang Airfoil Naca 0013 dengan Ansys Fluent

Hidayat

Nofendri

2019

Prosid Sem Nas Teknoka

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“…Results have been achieved for a perfect gas moving at hypersonic and supersonic speeds over a wide range of incidences, sweep angles, and Mach numbers. Bashir et al, [10] studied the computational and analytical investigation of aerodynamic derivatives for the oscillating wedge. The CFD simulation with analytical and theoretical validation of various flow parameters for the wedge at supersonic Mach number was obtained by Khan et al, [11].…”

Section: Introductionmentioning

confidence: 99%

Influence of Sweep Angle on the Surface Pressure of Delta Wing Along Pivot Positions at Hypersonic Mach Numbers

Shamitha,

Asha Crasta,

Sher Afghan Khan

2024

ARFMTS

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This study focuses on analyzing pressure distribution across the wing surface under different flight conditions. The distribution of surface pressure plays a crucial role in determining the performance of a delta wing. The outcomes of this research will be beneficial for stability assessment and enhancing performance during the aircraft design phase. The paper illustrates the impact of high supersonic Mach numbers, angles of incidence, and specific locations along the three-dimensional delta wing. Strips located at various span-wise positions are treated independently based on a strip theory, which when combined with hypersonic similitude, results in a piston theory. It is important to note that the current theory is only valid when the shock wave remains attached. Viscosity and wave reflection effects have not been taken into account in this particular study. The parameters considered in the study are the Mach numbers (M) in the range 4 to 7. Furthermore, consideration is given to the Angle of Incidence (θ), which varies between 5° to 25°. Along the Wings chord from 0.2 to 1, different points (h) record the pressure results (P2/P1). For numerical simulations, CFD was used, and simulated results at hypersonic Mach numbers matched well with analytical results.

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“…The variation in surface pressure distribution at the large angle of incidence and high Mach numbers in the case of curved leading edge for the delta wing was studied by Crasta et al, [12]. Musavir et al, [13] studied the computational and analytical investigation of aerodynamic derivatives for the oscillating wedge. The CFD simulation with analytical and theoretical validation of various flow parameters for the wedge at supersonic Mach number was obtained by Khan et al, [14].…”

Section: Introductionmentioning

confidence: 99%

Effectiveness of Cone Angle on Surface Pressure Distribution along Slant Length of a Cone at Hypersonic Mach Numbers

Shaikh

Pathan²,

Kumar

et al. 2023

ARFMTS

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In the present study, the prime attention is to numerically simulate the surface pressure distribution over the slant length of the cone at the various Mach numbers and for the considerable range of semi-cone angles. The Computational Fluid Dynamics (CFD) analysis is used to simulate the surface pressure distribution numerically. The hypersonic Mach numbers, semi-cone angle, and various locations along the slant length of a cone are considered parameters for this research work. The Mach numbers (M) considered for the research work are 5, 7, 9, 11, 13, and 15. The cone angle (θ) from 5° to 25° is considered. The results of pressure (P/Pa) are recorded at various locations (x/L) along the slant length of the cone as 0.1 to 1. The pressure distribution results are obtained by CFD analysis and compared with the analytical results available in the literature for Mach number 5. The findings obtained by CFD analysis and analytical results show good agreement. In this investigation, it is observed that the Mach number, cone angle, and slant length of the cone are the highly influential parameters for the surface pressure distribution. The pressure distribution over the slant length of the cone increases with an increase in the Mach number and the semi-cone angle.

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Computational and Analytical Investigation of Aerodynamic Derivatives of Similitude Delta Wing Model at Hypersonic Speeds

Cited by 4 publications

References 5 publications

Pengaruh Gaya Lift Terhadap Sudut Serang Airfoil Naca 0013 dengan Ansys Fluent

Pengaruh Gaya Lift Terhadap Sudut Serang Airfoil Naca 0013 dengan Ansys Fluent

Influence of Sweep Angle on the Surface Pressure of Delta Wing Along Pivot Positions at Hypersonic Mach Numbers

Effectiveness of Cone Angle on Surface Pressure Distribution along Slant Length of a Cone at Hypersonic Mach Numbers

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