A PRESSURE ANALYSIS ON V-TAIL SURFACE UAV MALE (UNMANNED AERIAL VEHICLE MEDIUM ALTITUDE LONG ENDURANCE) DUE TO CHANGES OF AIRFLOW VELOCITY USING COMPUTATIONAL FLUID DYNAMIC (CFD) METHOD

CHARLES, MARIO SUKMANA (2018) A PRESSURE ANALYSIS ON V-TAIL SURFACE UAV MALE (UNMANNED AERIAL VEHICLE MEDIUM ALTITUDE LONG ENDURANCE) DUE TO CHANGES OF AIRFLOW VELOCITY USING COMPUTATIONAL FLUID DYNAMIC (CFD) METHOD. Tugas Akhir thesis, SEKOLAH TINGGI TEKNOLOGI KEDIRGANTARAAN YOGYAKARTA.

	Text (ABSTRAK) abstrak.pdf Restricted to Registered users only Download (54kB)
	Text (BAB 1) bab 1.pdf Restricted to Registered users only Download (201kB)
	Text (BAB 2) bab 2.pdf Restricted to Registered users only Download (1MB)
	Text (BAB 3) bab 3.pdf Restricted to Registered users only Download (346kB)
	Text (DAFTAR PUSTAKA) daftar pustaka.pdf Restricted to Registered users only Download (89kB)

Official URL: http://digilib.sttkd.ac.id

Abstract | Intisari

ABSTRACT The characteristics of each airfoil are different in the aircraft tail wing design, requiring different wing modeling of tail-sections that are proper for their function. However with advances in technology, tail-section developing model can used by computation, one of which is by using the CFD (Computational Fluid Dynamic) method. In this research simulation on MALE UAV with V-tail wing shape. This simulation used the CFD method in solidwork 2017 software by varying the different velocity of the v-tail wing, the velocity used in this simulation is 145 km/h up to 235 km/h at 5 km/h intervals. Where in this velocity variation can be determined the type of flow that occurs on surface V-tail using the Reynolds Number equation. The results of this research the highest and lowest values of the pressure contours that occur on the surface wing of the V-tail are at speeds of 235 km / h, the maximum pressure is 108369.83 Pa and the minimum is 98025.27Pa at velocity of 230km/h where the higher the speed the greater the pressure range. Then from the calculation using the Reynolds Number equation obtained the type of flow that occurs on the wing V-tail with different speed variations shows the value of Re> 2x105 to Re <3x106 which is a type of transition flow. With a Re <3x106 value, the flow pattern that occurs was not too large is more effective to be used in acrobatic aircraft, such as UAV MALE (Unmanned Aerial Vehicle Medium Altitude Long Endurance). Keywords: V-tail wing, CFD (Computational Fluid Dynamic), Pressure Range, Reynolds Number.

Tipe Koleksi:

Thesis (Tugas Akhir)

Subjek:

UAV (Unmanned Aerial Vehicle)

Contributors: