initial commit / add all books

9 files changed, 147 insertions, 0 deletions

diff --git a/1457/CH10/EX10.1/10_1.sce b/1457/CH10/EX10.1/10_1.sce
new file mode 100755
index 000000000..aabd2db05
--- /dev/null
+++ b/1457/CH10/EX10.1/10_1.sce
@@ -0,0 +1,19 @@
+clc

+//Initialization of variables

+nu=0.001 //ft^2 /s

+L=1.5 //ft

+U=2 //ft/s

+s=0.925

+ro=1.94

+b=6

+//calculations

+R=L*U/nu

+Cf=1.328/sqrt(R)

+Ff=Cf*s*ro*U*b/12 *L

+delta=4.91 *L/sqrt(R)

+T0=0.332*nu*s*ro*U/L *sqrt(R)

+//results

+printf("Friction drag = %.3f lb",Ff)

+printf("\n Thickness of boundary layer = %.4f ft",delta)

+printf("\n Shear stress = %.4f lb/ft^2",T0)

+//Similar calculations are done for SI units case

diff --git a/1457/CH10/EX10.2/10_2.sce b/1457/CH10/EX10.2/10_2.sce
new file mode 100755
index 000000000..9fcc94943
--- /dev/null
+++ b/1457/CH10/EX10.2/10_2.sce
@@ -0,0 +1,21 @@
+clc

+//Initialization of variables

+nu=0.00015 //ft^2/s

+L=35 //ft

+U=88 //fps

+g=32.2 //ft/s^2

+b=10 //ft

+w=8 //ft

+rho=0.0725

+//calculations

+R=L*U/nu

+Cf=0.455 /(log10(R))^2.58

+B=2*b + w

+Ff=Cf*rho/g *U^2 /2 *L*B

+Rx=R/10^5

+delta=L*0.377 /(b* Rx^(0.2))

+T0=0.0587 *rho/g *U^2 /2 *(nu/(L*U))^(0.2)

+//results

+printf("Frictional drag = %.1f lb",Ff)

+printf("\n Thickness of  boundary layer = %.3f ft",delta)

+printf("\n Shear stress = %.4f lb/ft^2",T0)

diff --git a/1457/CH10/EX10.3/10_3.sce b/1457/CH10/EX10.3/10_3.sce
new file mode 100755
index 000000000..4503611f2
--- /dev/null
+++ b/1457/CH10/EX10.3/10_3.sce
@@ -0,0 +1,20 @@
+clc

+//Initialization of variables

+nu=0.0000166 //ft^2 /s

+U=5.06 //fps

+L=50 //ft

+g=32.2

+dia=10 //ft

+//calculations

+R=L*U/nu

+Cf=0.0028

+Ff=Cf*64/g *U^2 /2 *%pi*dia*L

+Rx=R/L

+ec=26*nu/U *Rx^(0.25)

+Rx2=Rx*L/2

+T02=0.0587*U^2 /2 /(Rx2)^(0.2)

+delta2=60*nu/sqrt(T02)

+//results

+printf("Friction drag = %d lb",Ff)

+printf("\n Critical roughness = %.4f ft",ec)

+printf("\n height of roughness = %.4f ft",delta2)

diff --git a/1457/CH10/EX10.4/10_4.sce b/1457/CH10/EX10.4/10_4.sce
new file mode 100755
index 000000000..7edd22f47
--- /dev/null
+++ b/1457/CH10/EX10.4/10_4.sce
@@ -0,0 +1,12 @@
+clc

+//Initialization of variables

+Cd=0.45

+rho=0.0725/32.2

+V=88 //fps

+A=8*10

+//calculations

+Fd=Cd*rho*V^2 /2 *A

+Drag2=23

+D=Fd-Drag2

+//results

+printf("Pressure drag = %d lb",D)

diff --git a/1457/CH10/EX10.5/10_5.sce b/1457/CH10/EX10.5/10_5.sce
new file mode 100755
index 000000000..4b847be5e
--- /dev/null
+++ b/1457/CH10/EX10.5/10_5.sce
@@ -0,0 +1,10 @@
+clc

+//Initialization of variables

+Cd=0.2

+D=8.5 //in

+V=412 //fps

+nu=1.57*10^-4 

+//calculations

+Vt=480 //fps

+//results

+printf("Free fall velocity = %d fps",Vt)

diff --git a/1457/CH10/EX10.6/10_6.sce b/1457/CH10/EX10.6/10_6.sce
new file mode 100755
index 000000000..9b6107a60
--- /dev/null
+++ b/1457/CH10/EX10.6/10_6.sce
@@ -0,0 +1,11 @@
+clc

+//Initialization of variables

+nu=1.15*10^-5 //m^2/s

+D=2*10^-3 //m

+V=15 //m/s

+T=-20 //C

+//calculations

+R=D*V/nu

+f=0.2 *V/D *(1+T/R)

+//results

+printf("Frequency of oscillation = %d Hz",f)

diff --git a/1457/CH10/EX10.7/10_7.sce b/1457/CH10/EX10.7/10_7.sce
new file mode 100755
index 000000000..363fed0ba
--- /dev/null
+++ b/1457/CH10/EX10.7/10_7.sce
@@ -0,0 +1,16 @@
+clc

+//Initialization of variables

+n=90 //rpm

+R=2 

+rho=0.0765/32.2

+B=25

+U=120 //fps

+//calculations

+vt=2*%pi*R*n/60

+T=2*%pi*R*vt

+Fl=rho*B*U*T

+theta=asind(-T/(4*%pi*R*U))

+//results

+printf("Value of circulation = %d ft62/s",T)

+printf("\n Transverse or lift force = %d lb",Fl)

+printf("\n Position of stagnation points = %.1f",180-theta)

diff --git a/1457/CH10/EX10.8/10_8.sce b/1457/CH10/EX10.8/10_8.sce
new file mode 100755
index 000000000..7598cb98d
--- /dev/null
+++ b/1457/CH10/EX10.8/10_8.sce
@@ -0,0 +1,23 @@
+clc

+//Initialization of variables

+B=36 //ft

+c=6 //ft

+Cl=0.8

+tau=0.175 

+rho=0.001756

+V=300 //fps

+//calculations

+alphai=Cl/(%pi*B/c) *(1+tau) *180/%pi

+alpha=5.4 

+lift=-5.6 //degrees

+alphao=alpha-alphai

+alphaod=alphao-lift

+alphaor=alphaod*%pi/180

+eta=Cl/(2*%pi*alphaor)

+Fl=Cl*rho*V^2 /2 *B*c

+Fd=0.047/Cl *13680

+HP=Fd*V/550

+//results

+printf("Friction coefficient = %.3f ",eta)

+printf("\n weight of the wing = %d lb",Fl)

+printf("\n Horsepower required = %d hp",HP)

diff --git a/1457/CH10/EX10.9/10_9.sce b/1457/CH10/EX10.9/10_9.sce
new file mode 100755
index 000000000..5a6350c6d
--- /dev/null
+++ b/1457/CH10/EX10.9/10_9.sce
@@ -0,0 +1,15 @@
+clc

+//Initialization of variables

+k=1.4

+R=287

+T=249 //K

+v=600 //m/s

+d=0.2 //m

+//calculations

+c=sqrt(k*R*T)

+M=v/c

+Cd=0.62

+rho=47.22*10^3 /(R*T)

+Fd=Cd*rho*v^2 /2 *%pi*d^2 /4

+//results

+printf("Drag = %d N",Fd)