Recent content by Cassius1n

  1. Cassius1n

    Heat loss in a conductor based on Fourier's law

    Homework Statement Find the admissible current density Jadm for a wire that has no insulation and also for a wire that has two layers of insulation and compare it to Jadm for the case when the wire has only one layer of insulation.2. The attempt at a solution and equations In the image I've...
  2. Cassius1n

    MATLAB Does anyone had this plotting problem with MATLAB?

    It's still plotting with the line from 0.
  3. Cassius1n

    MATLAB Does anyone had this plotting problem with MATLAB?

    That would be at at y(: tspan(end)/h).
  4. Cassius1n

    MATLAB Does anyone had this plotting problem with MATLAB?

    I have finsihed my work on an orbit propagator in MATLAB and now I'm trying to simulate the orbit with the help of the main script. tspan=[0 :860]; Position and velocity y0(1,1)= 743322.3616 ; y0(2,1)= -6346021.219 ...
  5. Cassius1n

    Solving Satellite Orbit & Eccentric Anomaly Calculations

    Sorry for that. For position and a we have km and for velocity km/s while T and t are in seconds.
  6. Cassius1n

    Solving Satellite Orbit & Eccentric Anomaly Calculations

    Gneill, thank you for the advice, I didn't know about the LaTeX!
  7. Cassius1n

    Solving Satellite Orbit & Eccentric Anomaly Calculations

    t=270; miu= 398600.5; Position values Rx=1.120260101155629e+03; Ry=-5.997082966407411e+03; Rz=-3.919879916453886e+03; Rxyz=[Rx Ry Rz]; Velocity values Vx=5.0702; Vy=4.9659; Vz=-6.9805; Vxyz=[Vx Vy Vz]; Angular momentum hez = cross(Rxyz,Vxyz); N = cross([0,0,1],hez); hx=hez(1,1); hy=hez(1,2)...
  8. Cassius1n

    Solving Satellite Orbit & Eccentric Anomaly Calculations

    First of all, thank you for your response, it has been very helpful.As for the second problem I've written the above MATLAB code. It uses the values of position vector and velocity vector to determine the orbital elements.As you can see the values for a and e and other elements are correct so I...
  9. Cassius1n

    Solving Satellite Orbit & Eccentric Anomaly Calculations

    Hi, everyone! I'm trying to find the period of a satellite orbiting the Earth by the next formulas with: miu= 398600.5; a=36770.48 km; I. 2*pi*(a^3/miu)^1/2 II. 84.489*(a/Re)^(3/2)min III. 0.00016587*a^(3/2)min And I got aprox. 19 hours from both formulas (I. and III.) which is correct. Can...
  10. Cassius1n

    Fortran Verifying Fortran MacCormack Algorithm at t=50*dt

    Hi i have a problem in solving the maccormack algorithm for the following : ∂p/∂t+8*∂p/∂x=0,x∈(-10,10) p(x,t=0)=e**-3x the exact solution is u exact(x,t)=e**-3(x-8t) I have to verify the solution with the exact solution at t=50* dt This is what I've done so far: implicit none...
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