SRM-Aerospace
SRM-AEROSPACE
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MCQ test
GATE
AIR BREATHING PROPULSION
Students attendance
Syllabus
Thermodynamics
Chapter-1
Chapter-2
Chapter-3
Chapter-4
>
Impulse and reaction blading of gas turbines
Velocity triangles and power output by elementary theory
Free Vortex theory
Choice of blade profile, pitch and chord
Matching of turbine and compressor
Example problem
Question Bank
RC modelling workshop
ROCKET PROPULSION
Syllabus
History and evolution of rockets
CHAPTER-1
CHAPTER-2
CHAPTER-3
CHAPTER-4
CHAPTER-5
Question Bank
Propulsion 2 question bank
Aero Fluid Mechanics LAB
Aerospace CAD Laboratory
Sketcher Tutorial
Materials Technology
Syllabus
Chapter-1
Chapter-2
Chapter-3
Chapter-4
Chapter-5
Question Bank
Manufacturing Technology
Syllabus
Chapter-1
>
Casting
Special Welding Process
Chapter-2
>
Mechanical working of Metals
Sheet Metal Operation
Chapter-3
>
Theory of Metal Cutting
Chapter-4
>
Gear Manufacturing Process
Surface Finishing Process
Question Bank
Chapter-5
>
Milling Machine & Indexing
Shaping, Planning and Slotting Machine
Boring and Jig Boring Machine
Broaching Machine
Work and Tool Holding Devices
Question Bank
Flight Dynamics
Syllabus
Chapter-1
Question Bank
About
Contact
ONLINE TEST
CALCULATOR
ATMOSPHERIC PROPERTIES CALCULATOR
AERODYNAMICS CALCULATOR
RC CALCULATOR
Program
Compressible Aerodynamics Calculator
Isentropic Flow Relations
Perfect Gas, Gamma =
, angles in degrees.
INPUT:
Mach number
T/T0
p/p0
rho/rho0
A/A* (sub)
A/A* (sup)
Mach angle (deg.)
P-M angle (deg.)
=
Mach number=
Mach angle=
P-M angle=
p/p
0
=
rho/rho
0
=
T/T
0
=
p/p*=
rho/rho*=
T/T*=
A/A*=
Normal Shock Relations
Perfect Gas, Gamma =
INPUT:
M1
M2
p2/p1
rho2/rho1
T2/T1
p02/p01
p1/p02
=
M
1
=
M
2
=
p
02
/p
01
=
p
1
/p
02
=
p
2
/p
1
=
rho
2
/rho
1
=
T
2
/T
1
=
Oblique Shock Relations
Perfect Gas, Gamma =
, angles in degrees.
INPUT:
M1 =
Turn angle (weak shock)
Turn angle (strong shock)
Wave angle
M1n
=
M
2
=
Turn ang.=
Wave ang.=
p
2
/p
1
=
rho
2
/rho
1
=
T
2
/T
1
=
p
02
/p
01
=
M
1n
=
M
2n
=
Conical Shock Relations
Perfect Gas, Gamma =
, angles in degrees.
INPUT:
M1 =
Cone angle
Wave angle
Mc
=
M
c
=
Cone ang.=
Wave ang.=
Shock turn ang.=
p
2
/p
1
=
p
02
/p
01
=
rho
2
/rho
1
=
T
2
/T
1
=
p
c
/p
1
=
p
0c
/p
01
=
rho
c
/rho
1
=
T
c
/T
1
=
Fanno Flow
Perfect Gas, Gamma =
INPUT:
Mach number
T/T*
P/P*
Po/Po* (sub)
Po/Po* (sup)
U/U*
4fL*/D (sub)
4fL*/D (sup)
(s*-s)/R (sub)
(s*-s)/R (sup)
=
M=
T/T*=
P/P*=
P
o
/P
o
*=
U/U*=
4fL*/D=
(s*-s)/R=
Rayleigh Flow
Perfect Gas, Gamma =
INPUT:
Mach number
To/To* (sub)
To/To* (sup)
T/T* (below Tmax)
T/T* (above Tmax)
P/P*
Po/Po* (sub)
Po/Po* (sup)
U/U*
(s*-s)/R (sub)
(s*-s)/R (sup)
=
M=
T
o
/T
o
*=
T/T*=
P/P*=
P
o
/P
o
*=
U/U*=
(s*-s)/R=