我想通过复制和粘贴我想要的代码来插入 matlab 代码，我希望它是黑色的，没有颜色，如果可能的话，我希望在文本框中输入行数，但如果太难的话就没有必要了。以下是我想出的办法：
\documentclass[a4paper,12pt]{book}
\usepackage[T1]{fontenc}
\usepackage[utf8]{inputenc}
\usepackage[english,italian]{babel}
\usepackage{url,amsfonts,epsfig}
\usepackage{amsmath}
\usepackage{caption}
\usepackage{subcaption}
\usepackage[backend=biber]{biblatex}
\addbibresource{capitoli/bibliografia/bibliografia.bib}
\usepackage{matlab-prettifier}
\usepackage{fancyhdr}
\pagestyle{fancy}
\renewcommand{\footrulewidth}{0.5pt}
\fancyhead[]{}
\fancyhead[LO]{\nouppercase{\rightmark}}
\fancyhead[RE]{\nouppercase{\leftmark}}
\fancyfoot{}
\fancyfoot[LO,RE]{\thepage}
\renewcommand{\sectionmark}[1]{\markright{#1}}
\parindent 0ex %serve per l'indentadure dei paragrafi
\usepackage{tikz}
\usepgflibrary{arrows.meta}
\usetikzlibrary{calc,quotes,angles}
\usepackage{pgfplots}
\pgfplotsset{compat=1.16}
\usepgfplotslibrary{groupplots}
\usetikzlibrary{calc}
\usepackage{hyperref}
\begin{document}
\section{Greitzer per steady-flow}
`\begin{lstlisting}
clear
clc
close all
%% Gas properties
a01 = 340; %speed of sound in gas(m/s)
p01 = 1e5; %Compressor inlet pressure(Pa)
P.T01 = 303.35; %Compressor inlet temperature(K)
P.cp = 1005; %specific heat capacity for constant pressure, property of gas(J/(kg*K))
P.ro1 = 1.15; %Gas density(kg/m^3)
Re = 100000; %Reynolds number()
P.k = 1.4; %Gas constant ratio, cp/cv()
%% Compressor characteristics
Lc = 0.53; %Length of compressor and duct(m)
Vp = 0.01; %Plenum volume(m^3)
Ac = 0.0026;
% kl = 0.0008; %Throttle gain, proportional to the throttle opening
Dt1 = 0.074; %Impeller diameter at inducer tip(m)
Dh1 = 0.032; %Impeller diameter at hub casing(m)
P.D1 = 1/sqrt(2)*sqrt((Dt1)^2+(Dh1)^2); %Average diameter(m)
Di = 0.02; %Mean hydraulic diameter of impeller(m)
Dd = 0.02; %Mean hydraulic diameter of impeller(m)
I = 0.001; %Moment of inertia for the compressor spool(kg*m^2)
alfa1 = pi/2; %Flow angle at inducer, for alpha1 = pi/2 rad, assumed no pre-whirl
A = ((pi*P.D1^2)/4)*4;
P.Ai = ((pi*P.D1^2)/4); % Cross section area impeller(m^2)
P.Ad = ((pi*P.D1^2)/4); % Cross section area diffuser(m^2)
li = 0.053; %Mean channel length(m)
ld = 0.053; %Mean channel length(m)
P.beta1b = 0.61; %Impeller blade inlet angle()
Ch = 4*0.3164*(Re)^-0.25; %Friction loss coefficient()
P.kf = (Ch*li)/(2*Di*P.ro1^2*P.Ai^2*(sin(P.beta1b))^2)*4; %Friction loss impeller
P.kfd = (Ch*ld)/(2*Dd*P.ro1^2*P.Ad^2*(sin(P.beta1b))^2)*4; %Friction loss diffuser
P.sigma = 0.9; %Slip factor()
P.D2 = 0.128; %Diameter of impeller tip(m)
P.alfa2b = atan((P.D1*tan(P.beta1b))/(P.sigma*P.D2));
m = [-0.2:0.001:0.8]; %[kg/s] Mass Flow
cn=10;
%% Speed
giri = 55000;
P.U1 = (P.D1*pi.*giri)/60;
P.U2 = (P.D2*pi.*giri)/60;
%% Greitzer's parameters
wh = a01*(Ac/Vp*Lc)^0.5; %Helmotz's frequency
P.B = P.U1/(2*wh*Lc); %Greitzer's parameter
%% Efficency Losses
deltanbf = 0.02; %Back flow loss() 0.02 annular diffuser - 0,03 medium volume - 0.05 vaned diffuser
deltanv = 0.035; %Volute loss()
deltanc = 0.00; %Clearance loss()
deltand = 0.00; %Diffusion loss()
P.deltan = deltanbf+deltanv+deltanc+deltand;
%% Energy Losses
deltahfi = P.kf.*(m.^2); %Impeller Friction losses
deltahfd = P.kfd.*(m.^2); %Diffuser Friction losses
%% Throttle valve's parameters
%% con lo stesso Delta da una parte e dall'altra
deltaideal = P.sigma*(P.U2^2); %Deltah0c,ideal
%% Lossees
deltahii = 0.5.*((P.U1-...
((cot(P.beta1b).*m)/(P.ro1*P.Ai))).^2); %Impeller Incidence Loss
deltahid = 0.5.*(((P.sigma*P.D2*P.U1)/P.D1)-...
((m.*cot(P.alfa2b))/(P.ro1*P.Ad))).^2; %Diffuser Incidence Loss
deltaloss = deltahii+...
deltahid+deltahfi+deltahfd;
deltah0c = deltaideal-...
deltaloss-P.deltan; %deltah0c
%% Efficiency
eta = deltaideal./(deltaideal+deltaloss)-P.deltan;
%% Pressure Rise in the Compressor
psi_c =((1+((eta.*deltaideal)/(P.T01*P.cp))).^(P.k/(P.k-1)));
%% Throttle valve's parameters
gamma_T = .17; %throttle valve aperture
Delta_gamma_T = .06; %range between your gamma_T_max e gamma_T_min
gamma_T_max = gamma_T+(Delta_gamma_T/2); %maximum aperture
gamma_T_min = gamma_T-(Delta_gamma_T/2); %minimum aperture
P.Amplitude = (gamma_T_max - gamma_T_min)/2; %amplitude
P.b = (gamma_T_max + gamma_T_min)/2;
%% Compressor's frequency (only frequency)
compressor_frequency = 10; %engine's frequency [Hz]
P.w = compressor_frequency*2*pi; %engine's frequency [radiants/s]
% save main_parameters.mat
%% Ode's parameters
t0 = 0; %simulation's start [s]
tf = 200; %simulation's finish [s]
y1 = 0; %initial condition 1
y2 = 0; %initial condition 2
init = [y1 y2]'; %initial conditions vector
sample_frequency = 400; %sample frequency [Hz] (choose at least a frequency
% 10-12 times the one being analyzed
% for a good definition. Just 2-3 times for a quick try)
maximum_time_step = 1/sample_frequency;
options= odeset('MaxStep',maximum_time_step); %maximum time-step size
[t,y]=ode113(@(t,y)greitzer(t,y,P),[t0,tf],init,options); %I found ode113 is way more efficient
psi_c_y = ((1+((eta.*deltaideal)/(P.T01*P.cp))).^(P.k/(P.k-1)));
valve = (1/gamma_T.^2).*y(:,1).^2;
%% Plots
subplot(2,2,1) %compressor map quadrant
plot(m,psi_c,y(:,1),y(:,2),y(:,1),valve)
legend('compressor characteristic','\Phi vs \Psi')
grid on
grid minor
xlabel('\Phi')
ylabel('\Psi')
axis([0 0.8 0 3]);
subplot(2,2,2) %compressor map quadrant
plot(m,psi_c_y,y(:,1),y(:,2))
hold on
plot(y(:,1),valve)
legend('compressor characteristic','\Phi vs \Psi')
grid on
grid minor
xlabel('\Phi')
ylabel('\Psi')
axis([0 0.8 0 3]);
subplot(2,2,3) % mass flow quadrant
plot(t,y(:,1))
grid on
grid minor
xlabel('t [s]')
ylabel('\Phi')
subplot(2,2,4) %pressure oscillations quadrant
plot(t,y(:,2))
grid on
grid minor
xlabel('t [s]')
ylabel('\Psi')
\end{lstlisting}
`
\end{document}
通过此代码我得到如图所示的结果：
