Recent content by Cassius1n
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Heat loss in a conductor based on Fourier's law
Thank you for the help!- Cassius1n
- Post #7
- Forum: Engineering and Comp Sci Homework Help
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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...- Cassius1n
- Thread
- Conductor Elecricity Fourier Heat Heat loss Law Loss Thermal Wire
- Replies: 6
- Forum: Engineering and Comp Sci Homework Help
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MATLAB Does anyone had this plotting problem with MATLAB?
It's still plotting with the line from 0.- Cassius1n
- Post #5
- Forum: MATLAB, Maple, Mathematica, LaTeX
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MATLAB Does anyone had this plotting problem with MATLAB?
That would be at at y(: tspan(end)/h).- Cassius1n
- Post #3
- Forum: MATLAB, Maple, Mathematica, LaTeX
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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 ...- Cassius1n
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- Matlab Matlab programming Plotting
- Replies: 4
- Forum: MATLAB, Maple, Mathematica, LaTeX
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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.- Cassius1n
- Post #8
- Forum: Introductory Physics Homework Help
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Solving Satellite Orbit & Eccentric Anomaly Calculations
Gneill, thank you for the advice, I didn't know about the LaTeX!- Cassius1n
- Post #6
- Forum: Introductory Physics Homework Help
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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)...- Cassius1n
- Post #5
- Forum: Introductory Physics Homework Help
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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...- Cassius1n
- Post #3
- Forum: Introductory Physics Homework Help
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Fortran Verifying Fortran MacCormack Algorithm at t=50*dt
Thank you for your response!- Cassius1n
- Post #5
- Forum: Programming and Computer Science
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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...- Cassius1n
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- Anomaly Calculations Orbit Satellite
- Replies: 7
- Forum: Introductory Physics Homework Help
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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...- Cassius1n
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- Fortran
- Replies: 4
- Forum: Programming and Computer Science