Application intended for 'A Basic' by Aviation Lecturer Writer Martin Hollmann

I think I copied it right and it seems to run but a few bugs might show up requiring correction

SPAR

10 PRINT "SPAR SIZING PROGRAM, by M  Hollmann"
16 DIM WS(11), V(11), M(11), M1(10), WL(11)
20 REM ---------INPUT DATA---------------
25 REM Enter Gross Weight Less Wing Weight, lbs = W
30 W = 829
35 LoadFactor = 4.4
40 WingSpan = 20
45 RootChord = 4
50 TipChord = 2
55 REM --------SPAR PROGRAM--------------
60 PRINT""
65 LF = LoadFactor
70 S=WingSpan
75 CR=RootChord
80 CT=TipChord
85 WS(1)=0
90 WL(1)=2*W*LF*CR/(S*(CR+CT))
95 V(1)=W*LF/2
100 M(1)=W*LF*S/4-W*LF*S*(2*CR+CT)/(12*(CR+CT))
105 FOR C=1 TO 10
110 WS(C+1)=WS(C)+S/20
115 WL(C+1)=WL(1)+4*W*LF*(CT-CR)*WS(C+1)/(S^2*(CR+CT))
120 V(C+1)=V(1)-2*W*LF*(CR*WS(C+1)-CR*WS(C+1)^2/S+CT*WS(C+1)^2/S)/(S*(CR+CT))
125 M1(C)=CR*WS(C+1)^2/2-CR*WS(C+1)^3/(3*S)+CT*WS(C+1)^3/(3*S)
130 M(C+1)=M(1)+2*W*LF*M1(C)/(S*(CR+CT))-W*LF*WS(C+1)/2
135 NEXT C
140 PRINT "WING STA,ft.","AIR LOAD,lb/ft","SHEAR,lb","MOMENT,ft.lbs."
145 FOR Z=1 TO 11
150 PRINT WS(Z),INT(WL(Z)),INT(V(Z)),INT(M(Z))
155 NEXT Z
160 REM --------------------------------
165 PRINT"SPAR  SIZING"
170 DIM H(11), T1(11), T2(11)
175 INPUT"Enter Tensile or Compressive  Strength of Cap,psi:";FS
180 INPUT"Enter Shear Strength of Shear Web,psi:";FS
185 INPUT"Enter Spar Width,Inches:";A
190 INPUT"Enter Chord Thickness, % Chord:";CD
195 PRINT""
200 WS(1)=0
205 H(1)=.096*CD*CR
210 T1(1)=24*M(1)/(H(1)*A*FT)
215 T2(1)=V(1)/(H(1)*FS)
220 FOR C=1 TO 10
225 WS(C+1)=WS(C)+S/20
230 H(C+1)=H(1)+.096*CD*2*(CT-CR)*WS(C+1)/S
235 T1(C+1)=24*M(C+1)/(H(C+1)*A*FT)
240 T2(C+1)=V(C+1)/(H(C+1)*FS)
245 NEXT C
250 PRINT"WING STA,ft.","SPAR HEIGHT,in.","CAP  THICK,in.","WEB THICK,in."
255 FOR Z=1 TO 11
260 PRINT WS(Z), H(Z), T1(Z), T2(Z)
265 NEXT Z
270 INPUT"Hit Return to Quit";a$
280 END