Aerodynamics Practicum
LAPORAN
PRAKTIKUM AERODINAMIKA II
Kelompok
Angogota:
Ahmad Adrian 111221001
Erict Ilyas S 111221004
M. Yusup A 111221019
Oki Hidayat N 111221021
Yusuf Adiwinata 111221031
PROGRAM STUDI AERONAUTIKA
JURUSAN TEKNIK MESIN
POLITEKNIK NEGERI BANDUNG I. JUDUL
“Flying Wing Paper Model” II. TUJUAN a. Mencari CL dan CDi dari berbagai jenis sayap b. Mencari efek weight terhadap CL dan CDi c. Mengetahui efek head wind dan tail wind terhadap CL dan CDi III. LANDASAN TEORI
3.1 Parameter – parameter 1. Wing reference (or planform) area (SW or Sref or S)
The wing is measured from the centerline to the last rib to get the half-span of the wing. The wing area is calculated by multiplying the half-span by 2 to get the full span and multiplying by the chord to get the area.
The definition of wing area is not obvious and different companies define the areas differently. Here, we always take the reference wing area to be that of the trapezoidal portion of the wing projected into the centerline. The leading and trailing edge chord extensions are not included in this definition and for some airplanes, such as Boeing's Blended Wing Body, the difference can be almost a factor of two between the "real" wing area and the "trap area". Some companies use reference wing areas that include portions of the chord extensions, and in some studies, even tail area is included as part of the reference area. For simplicity, we use the trapezoidal area in this text. | | | Reference Wing Area | Exposed Wing Area | Area Affected by Flaps |
In addition to the reference area, we use the exposed planform area depicted above in the calculation of skin friction drag and the wetted area which is a bit more than twice the exposed planform area.
2. Number of the wings
3. Vertical position relative to the fuselage (high, mid, or low wing)
4. Horizontal position relative to the fuselage
5. Cross section (or airfoil)
6. Aspect ratio (AR)
The
PRAKTIKUM AERODINAMIKA II
Kelompok
Angogota:
Ahmad Adrian 111221001
Erict Ilyas S 111221004
M. Yusup A 111221019
Oki Hidayat N 111221021
Yusuf Adiwinata 111221031
PROGRAM STUDI AERONAUTIKA
JURUSAN TEKNIK MESIN
POLITEKNIK NEGERI BANDUNG I. JUDUL
“Flying Wing Paper Model” II. TUJUAN a. Mencari CL dan CDi dari berbagai jenis sayap b. Mencari efek weight terhadap CL dan CDi c. Mengetahui efek head wind dan tail wind terhadap CL dan CDi III. LANDASAN TEORI
3.1 Parameter – parameter 1. Wing reference (or planform) area (SW or Sref or S)
The wing is measured from the centerline to the last rib to get the half-span of the wing. The wing area is calculated by multiplying the half-span by 2 to get the full span and multiplying by the chord to get the area.
The definition of wing area is not obvious and different companies define the areas differently. Here, we always take the reference wing area to be that of the trapezoidal portion of the wing projected into the centerline. The leading and trailing edge chord extensions are not included in this definition and for some airplanes, such as Boeing's Blended Wing Body, the difference can be almost a factor of two between the "real" wing area and the "trap area". Some companies use reference wing areas that include portions of the chord extensions, and in some studies, even tail area is included as part of the reference area. For simplicity, we use the trapezoidal area in this text. | | | Reference Wing Area | Exposed Wing Area | Area Affected by Flaps |
In addition to the reference area, we use the exposed planform area depicted above in the calculation of skin friction drag and the wetted area which is a bit more than twice the exposed planform area.
2. Number of the wings
3. Vertical position relative to the fuselage (high, mid, or low wing)
4. Horizontal position relative to the fuselage
5. Cross section (or airfoil)
6. Aspect ratio (AR)
The