table from the variable from the loop

Hello everyone, could you please help me how to calculate the table from the generated variables from the loop

For example, from the second loop, the table with a colums of V, D, F, W, t

my code is :

clear all; close all

W_takeoff = 10000;
W_landing=6000;
S = 20;
AR = 5;
cd0 = 0.02;
k = 1/pi/AR;
RC=0.51;
clalpha = 2*pi;
amin=2;
astall=12;
rho=1;
ct=0.001;
figure(1);hold on; xlabel('V');ylabel('D')
figure(2);hold on; xlabel('V');ylabel('D')
figure(3);hold on; xlabel('V');ylabel('P')
figure(4);hold on; xlabel('V');ylabel('P')
figure(5);hold on; xlabel('\alpha');ylabel('c_l/c_d^2')
    i=0;
    for alpha = amin:0.25:astall
        i=i+1;
        cl(i) = clalpha * alpha * pi/180;
        V_takeoff(i) = sqrt(2*W_takeoff/rho/S/cl(i));
        V_landing(i) = sqrt(2*W_landing/rho/S/cl(i));
        cd(i) = cd0 + k * cl(i) * cl(i);
        D_takeoff(i) = 0.5 * rho * V_takeoff(i) * V_takeoff(i) * S * cd(i);
        D_landing(i) = 0.5 * rho * V_landing(i) * V_landing(i) * S * cd(i);
        p_takeoff(i) = D_takeoff(i)*V_takeoff(i);
        p_landing(i) = D_landing(i)*V_landing(i);
        P_takeoff(i)=20000+500*V_takeoff(i);
        T_takeoff(i)=20000/V_takeoff(i)+500;
        P_landing(i)=20000+500*V_landing(i);
        T_landing(i)=20000/V_landing(i)+500;
        cl_cd2(i)=cl(i)/(cd(i)*cd(i));
        ang(i)=alpha;
    end  
    figure(1); plot(V_takeoff,D_takeoff)
    hold on 
    plot(V_takeoff,T_takeoff)
    title(['Takeoff'])
    figure(2); plot(V_landing,D_landing)
    hold on 
    plot(V_landing,T_landing)
    title(['Landing'])
    figure(3); plot(V_takeoff,p_takeoff)
    hold on 
    plot(V_takeoff,P_takeoff)
    title(['Takeoff'])
    figure(4); plot(V_landing,p_landing)
    hold on 
    plot(V_landing,P_landing)
    title(['Landing'])
    figure(5); plot(ang,cl_cd2);

alpha_max=3;
cl_max=clalpha*alpha_max*pi/180;
cd_max = cd0 + k * cl_max * cl_max;
j=0;
  for w=W_takeoff:-50:W_landing
      j=j+1;
      V(j) = sqrt(2*w/rho/S/cl_max); 
      D(j) = 0.5 * rho * V(j) * V(j) * S * cd_max;
      T(j)=D(j); %for steady level flight condition
      F(j)=ct*T(j); %fuel consumption
      Weight(j)=w;
      t(j)=abs((Weight(j)-10000))/F(j);
      R(j)=V(j)*t(j);
  end
  [max_delta,idelta] = max(abs(D_takeoff-T_takeoff));
  figure(6); plot(t,V)
  figure(7); plot(t,F);
  figure(8); plot(t,R);

Answer 1

[Matt J]

j=0;
  for w=W_takeoff:-50:W_landing
      j=j+1;
      V(j,1) = sqrt(2*w/rho/S/cl_max); 
      D(j,1) = 0.5 * rho * V(j) * V(j) * S * cd_max;
      T(j,1)=D(j); %for steady level flight condition
      F(j,1)=ct*T(j); %fuel consumption
      Weight(j,1)=w;
      t(j,1)=abs((Weight(j)-10000))/F(j);
      R(j,1)=V(j)*t(j);
  end

  W=Weight;
  T=table(V, D, F, W, t)

T =

81×5 table

V D F W t

______ ______ _______ _____ ______

55.133 817.37 0.81737 10000 0

54.995 813.28 0.81328 9950 61.479

54.857 809.19 0.80919 9900 123.58

54.718 805.11 0.80511 9850 186.31

54.579 801.02 0.80102 9800 249.68

: : : : :

43.412 506.77 0.50677 6200 7498.5

43.236 502.68 0.50268 6150 7658.9

43.06 498.59 0.49859 6100 7822

42.883 494.51 0.49451 6050 7987.8

42.706 490.42 0.49042 6000 8156.3