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All Journal Warta Ardhia : Jurnal Perhubungan Udara
Sayuti Syamsuar
Pusat Teknologi Industri dan Sistem Transportasi, Badan Pengkajian dan Penerapan Teknologi (BPPT)
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Metoda Short Takeoff Landing (Studi Kasus Prestasi Terbang Takeoff-Landing Pesawat Udara Turbo Prop CN235) Sayuti Syamsuar
WARTA ARDHIA Vol 41, No 2 (2015)
Publisher : Research and Development Agency of The Ministry of Transportation

Show Abstract | Download Original | Original Source | Check in Google Scholar | Full PDF (1019.733 KB) | DOI: 10.25104/wa.v41i2.144.49-58

Abstract

Pesawat dengan kategori Short Take-Off Landing pada umumnya adalah pesawat ringan yang mempunyai berat take-off antara 20.000 lb (9.072 kg) hingga 50.000 lb (22.680 kg) dengan kemampuan melewat irintangan setinggi 50 ft (15 m) untuk jarak take-off dan landing sejauh 1.500 ft (450 m). Pengembangan pesawat dengan kategori tersebut perlu memperhatikan tiga persyaratan umum yaitu kemampuan aerodinamika yang tinggi, tenaga mesin yang besar, dan teknik pilot yang baik yang disertai dengan kekuatan struktur yang mampu menahan beban berat. Pada studi kasus ini, penulis menggunakan data prestasi terbang Short Field Landing pesawat CN235-100 (serial N-16) dengan menggunakan flap 230 pada saat pengujian performance trade-off di PT Dirgantara Indonesia pada tahun 1996. Pengujian tersebut juga termasuk uji rejected take-off atau accelerate stop distance dengan menggunakan flap 100 pada tenaga penuh dimana kemudian salah satu mesin dimatikan untuk mencapai kondisi kritis dan pilot mengurangi daya propulsi mesin lainnya untuk dapat berhenti di ujung landasan. Beberapa rekomendasi pilot diberikan pada bagian kesimpulan. [The Short Takeoff Landing Method (CN235 Turbo Prop Field Performance Test Case Study)] The aircraft category of Short Take-Off Landing, in general, including lightweight aircrafts with take-off weight between 20.000 lb (9.072 kg) and 50.000 lb (22.680 kg) and capable in exceeding 50 ft (15 m) obstacle height with only 1.500 ft (450 m) of take-off and landing distance. Thera are, at least, three general requirements that have to be considered in order to develop this category of aircraft; high aerodynamic performance, powerful engine, qualified skill of pilot, and also the strength of aircraft structure that can sustain heavy load.As for the study case, the author used the flight performance data of CN235-100 (serial N-16) Short Field Landing with 230 flap that was tested in Indonesian Aerospace Industry in 1996 for its trade-off performance. There was also rejected take-off or accelerate stop distance test with 100 flap and full throttle where one of the engine, then suddenly, shut down in order to achieve critical condition and later the power of the another engine being reduced by the pilot so that the aircraft can stop at the end of the runway. Several pilot recommendations are given in the conclusion chapter.
Simulasi dan Verifikasi Prestasi Terbang Model Remote Control Flying Boat Saat Hidroplaning Sayuti Syamsuar
WARTA ARDHIA Vol 42, No 1 (2016)
Publisher : Research and Development Agency of The Ministry of Transportation

Show Abstract | Download Original | Original Source | Check in Google Scholar | Full PDF (1147.299 KB) | DOI: 10.25104/wa.v42i1.294.1-6

Abstract

Pesawat Wing In Surface Effect A2B tipe B konfigurasi Lippisch mempunyai hambatan air yang cukup besar dibandingkan tenaga mesin saat hydroplaning. Makalah ini berisikan bagian dari analisis dalam perancangan untuk mengetahui karakteristik aerodinamika dan hidrodinamika dari remote control model jenis Flying Boat pada fase hydroplaning. Pada awalnya, dilakukan pemotretan 3D terhadap pesawat model Flying Boat menggunakan kamera laser untuk menghasilkan solid drawing pada program CATIA. Model 3D dianalisis dengan menggunakan piranti lunak CFx pada program AnSys. Planform sayap, memiliki dihedral dan menggunakan airfoil jenis NACA 23012. Karakteristik aerodinamika dan hidrodinamika untuk model 3 D dipresentasikan pada posisi sudut alpha =00. Sedangkan kecepatan yang digunakan adalah 0 sampai25 knots. Untuk memverifikasi data hasil simulasi, digunakan data uji terbang pesawat udara tanpa awak Alap-alap yang mempunyai T/W rasio yang sama, yaitu sudut pitch, kecepatan arah sumbu Z pada sumbu benda, ketinggian dan kecepatan. Gaya angkat aerodimaka arah sumbu Z pada simulasi RC model Flying Boat sebanding dengan gaya angkat aerodinamika arah sumbu Z pada UAV Alap-alap saat take off. [The Hydroplaning Flight Performance Simulation and Verfication of a Flying Boat Remote Control Model] The Wing in Surface Effect Aircraft A2B type B with Lippisch configuration has higher hydrodynamics drag compared to engine powered aircraft during hydroplaning. This paper explains parts of analysis in aircraft design to identify the aerodynamics and hydrodynamics characteristics of flying boat remote control model during hydroplaning phase. At first, flying boat model was three dimensional photographed using laser camera in order to produce solid drawing for CATIA program. The three dimensional model, later, analyzed by using CFx software in AnSys program. The wing planform has dihedral angle while the airfoil used is NACA 23012. The aerodynamics and hydrodynamics characteristics of this three-dimensional model is represented for alpha =00. Whilst the speed used in simulation was 0 to 25 knots. In verifying the data of the simulation results, the Unmanned Aerial Vehicle UAV Alap-alap flight test data was used in which it has the same T/W ratio for the pitch angle, acceleration in Z body axis, altitude, and speed. The aerodynamics lift in Z axis of flying boat model during simulation is proportional to the aerodynamics lift in Z axis of UAV Alap-alap during take-off.
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