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    Nama: Ganda Tri Alam NPM: 17010051 TP B Tugas 2 Aerodinamika Ii

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    Tri Ganda
    This document contains calculations to determine the drag coefficient (Cd) of a wedge-shaped object at an altitude of 5500 ft. The following information is given: freestream pressure, density, and velocity. Integrals are used to calculate the pressure and skin friction drag components. The total drag is found to be 787898.99 N. Using this total drag value along with properties of the freestream flow, the drag coefficient is calculated to be 3.454.

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    Nama: Ganda Tri Alam NPM: 17010051 TP B Tugas 2 Aerodinamika Ii

    Uploaded by

    Tri Ganda
    20 views3 pages
    This document contains calculations to determine the drag coefficient (Cd) of a wedge-shaped object at an altitude of 5500 ft. The following information is given: freestream pressure, density, and velocity. Integrals are used to calculate the pressure and skin friction drag components. The total drag is found to be 787898.99 N. Using this total drag value along with properties of the freestream flow, the drag coefficient is calculated to be 3.454.

    Original Description:

    Aerodinamika

    Original Title

    AERODINAMIKA II

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    This document contains calculations to determine the drag coefficient (Cd) of a wedge-shaped object at an altitude of 5500 ft. The following information is given: freestream pressure, density, and velocity. Integrals are used to calculate the pressure and skin friction drag components. The total drag is found to be 787898.99 N. Using this total drag value along with properties of the freestream flow, the drag coefficient is calculated to be 3.454.

    Copyright:

    © All Rights Reserved
    Download as DOCX, PDF, TXT or read online from Scribd
    Download as docx, pdf, or txt
    20 views3 pages

    Nama: Ganda Tri Alam NPM: 17010051 TP B Tugas 2 Aerodinamika Ii

    Uploaded by

    Tri Ganda
    This document contains calculations to determine the drag coefficient (Cd) of a wedge-shaped object at an altitude of 5500 ft. The following information is given: freestream pressure, density, and velocity. Integrals are used to calculate the pressure and skin friction drag components. The total drag is found to be 787898.99 N. Using this total drag value along with properties of the freestream flow, the drag coefficient is calculated to be 3.454.

    Copyright:

    © All Rights Reserved
    Download as DOCX, PDF, TXT or read online from Scribd
    Download as docx, pdf, or txt
    of 3

    NAMA : GANDA TRI ALAM

    NPM : 17010051 TP B
    TUGAS 2 AERODINAMIKA II

    1). ALTITUDE =5500 ft


    Dik :
     P∞ = 0.83 x 105 N /m2
    Kg
     ρ=1.13 3 1.13Kg/m^3=1.13Kg/m^3=1.13Kg/m^3
    m
     Pu=Pl = 1,31 x 103 N /m2
     τu=τl=431 S−0,2=τl=431S^-0,2u=τl=431S^-0,2u=τl=431S^-0,2
     c=2m 2 mm

    : Calculate the drag coefficient


    for the wedge? (Cd?)

    Jawab :
     D' = A'
    TE
    D' =∫ ¿ ¿ +
    ¿
    TE

    ∫ ¿¿
    ¿
    TE

     ∫ ¿¿ +
    ¿
    s3

    ∫−( 0.08 x 105 ) sin ( 90 ° ) dsu


    s2

    =1,142 x104 (s2-s1)- 0,83x105(s3-s2)


    c
    =1,142 x104 ( cos 5 ° )- 0,83x105(c)(tan 5° ¿)
    = 1.142 × 104 (2.008) - 14523,11 = 8399,25 N
    TE

     ∫ ¿¿ +
    ¿
    s3

    ∫ ( 0.08 x 105 ) sin (−90 ° ) ds l


    s4

    =1,142 x104 (s4-s1)- 0,83x105(s3-s4)


    c
    = 1,142 x104 ( cos 5 ° )- 0,83x105(c)(tan 5° ¿)
    1.142 × 104 (2.008) -14523,11 = 8399,25 N
    TE

     ∫ ¿¿
    ¿

    s 20,8 −s 10,8
    = 429 ( ¿
    0,8
    c 0,8 1
    =429 (cos 5 °)( ) 0,8
    = 936.5 N

    TE

     ∫ ¿¿
    ¿

    s 20,8 −s 10,8
    = = 429 ( ¿
    0,8
    c 0,8 1
    =429 (
    cos 5 ° )( )
    0,8
    = 936.5 N
    TE TE

     D' =∫ ¿ ¿ + ∫ ¿ ¿
    ¿ ¿

    = 787898,99 N
     The drag coefficient is obtained as follows. The velocity of the
    freestream is twice
    the sonic speed, which is given by
    a∞ = √ γ RT ∞ = √ 1. 4 ¿(287)(288) ¿ = 340.2 m/s

     V∞ = 2(340.2) =680.4 m/s.


     q∞ = 1/2ρ∞V 2∞= (0.5)(1,32)(680.4)¿ 2= 555555 N / m2/m^2/m^2
     S = c(1) = 2 m2
    787898,99 N
    D'
     Cd = = N = 3.454
    q ∞ S 5555552 m x 2 m

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