See Our team

Wondering how we keep quality?

Got unsolved questions?

Ask Questions

Engineering
GATE
CBSE
NCERT
Psychology
English
Computer
Constitution
Astrology
Yoga
Economics
Physics
Biology
Electronics
Microprocessor
Career
Interview
Anatomy
Botany

### New updates

Updated ProfileDate:2018-10-19 04:16:49Done by:fredUpdated ProfileDate:2018-10-19 04:03:02Done by:Sarares

Updated ProfileDate:2018-10-19 03:51:03Done by:Helmickse1

### Similar Questions

**A rocket motor has combustion chamber temperature of 2600 K and the products have molecular weight of 25 g/mol and ratio of specific heats 1.2. GATE-Aerospace Engineering-Question-2012**

1 Answer

**The stagnation temperatures at the inlet and exit of a combustion chamber are 600 K and 1200 K, respectively GATE-Aerospace Engineering-Question-2012**

1 Answer

**A diesel engine has a compression ratio of 17 and cut-off take place at 10% of the stroke. Assuming ratio of specific heats ( γ ) as 1.4, the air-standard efficiency (in percent) is______. (Gate mechanical engineering 2014)**

1 Answer

**A rocket is to be launched from the bottom of a very deep crater on Mars for earth return. The specific impulse of the rocket, measured in seconds, is to be normalized by the acceleration due to gravity at GATE-Aerospace Engineering-Question-2012**

1 Answer

**Consider a simple gas turbine (Brayton) cycle and a gas turbine cycle with perfect regeneration. In both the cycles, the pressure ratio is 6 and the ratio of the specific heats of the working medium is 1.4. The ratio of minimum to maximum temperature**

1 Answer

**An airfoil generates a lift of 80 N when operating in a freestream flow of 60 m/s . GATE-Aerospace Engineering-Question-2012**

1 Answer

**Thrust of liquid oxygen - liquid hydrogen rocket engine is 300 kN. The O/F ratio used is 5. If the fuel mass flow rate is 12.5 kg/s, the specific impulse of the rocket motor in Ns/kg is ? GATE- Aerospace**

2 Answer

**Moist air is treated as an ideal gas mixture of water vapor and dry air (molecular weight of air = 28.84 and molecular weight of water = 18). At a location, the total pressure is 100 kPa, the temperature is 30°C and the relative humidity is 55%. Given that the saturation pressure of water at 30°C is 4246 Pa, the mass of water vapor per kg of dry air is _____________ grams.**

1 Answer

**Moist air is treated as an ideal gas mixture of water vapor and dry air (molecular weight of air = 28.84 and molecular weight of water = 18). At a location, the total pressure is 100 kPa, the temperature is 30°C and the relative humidity is 55%. Given that the saturation pressure of water at 30°C is 4246 Pa, the mass of water vapor per kg of dry air is _____________ grams**

1 Answer

**Moist air is treated as an ideal gas mixture of water vapor and dry air (molecular weight of air = 28.84 and molecular weight of water = 18). At a location, the total pressure is 100 kPa, the temperature is 30°C and the relative humidity is 55%. Given that the saturation pressure of water at 30°C is 4246 Pa, the mass of water vapor per kg of dry air is _____________ grams.**

1 Answer

**Moist air is treated as an ideal gas mixture of water vapor and dry air (molecular weight of air = 28.84 and molecular weight of water = 18). At a location, the total pressure is 100 kPa, the temperature is 30°C and the relative humidity is 55%. Given that the saturation pressure of water at 30°C is 4246 Pa, the mass of water vapor per kg of dry air is _____________ grams.**

1 Answer

**Moist air is treated as an ideal gas mixture of water vapor and dry air (molecular weight of air = 28.84 and molecular weight of water = 18). At a location, the total pressure is 100 kPa, the temperature is 30°C and the relative humidity is 55%. Given that the saturation pressure of water at 30°C is 4246 Pa, the mass of water vapor per kg of dry air is _____________ grams**

1 Answer

1 Answer

**The ideal static pressure coefficient of a diffuser with an area ratio of 2.0 is GATE-Aerospace Engineering-Question-2012**

1 Answer

**The Poisson’s ratio,ν of most aircraft grade metallic alloys has values in the range: GATE-Aerospace Engineering-Question-2012**

1 Answer

**The ratio of flight speed to the exhaust velocity for maximum propulsion efficiency is GATE-Aerospace Engineering-Question-2012**

1 Answer

**A 588 cm3 volume of moist sand weighs 1010 gm. Its dry weight is 918 gm and specific gravity of solids, G is 2.67. - gate civil 2017**

1 Answer

**A rocket motor has a chamber pressure of 100 bar and chamber temperature of 3000 K. The ambient pressure is 1 bar. Assume that the specifi c heat at constant pressure is 1 kJ/kg-K. Also assume that the flow in the**

1 Answer

**The concentration of Sulfur Dioxide (SO2) in ambient atmosphere was measured as 30 g/m3 . Under the same conditions, the above SO2 concentration expressed in ppm is _______________. - gate civil 2017**

1 Answer

**Enzyme-linked immunosorbent assay (ELISA) is used for GATE-Biotechnology-2017**

1 Answer

### Notes

**GATE-Aerospace Engineering-Question paper-2012**

**combustion**

**Nano cards into the robotics**

**GATE- Aerospace Engineering- 2013**

**GATE Mechanical Engineering Question Paper 2012 download**

**GATE Electrical Engineering Question Paper 2012 download**

**GATE Electronics and Communication Engineering Question Paper 2012 download**

**GATE Civil Engineering Question Paper 2012 download**

**GATE Computer Science Engineering / Information Technology Question Paper 2012 download**

**CE - Civil Engineering**

## A rocket motor has combustion chamber temperature of 2600 K and the products have molecular weight of 25 g/mol and ratio of specific heats 1.2. GATE-Aerospace Engineering-Question-2012

By:Amogh

Taged users:

Likes:

Be first to like this question

Dislikes:

Be first to dislike this question

Talk about thisDelete|Like|Dislike|

## Answers

Answer : - 1430 - 1440 m/s.A rocket engine is a type of jet engine that uses only stored rocket propellant mass for forming its high speed propulsive jet. Rocket engines are reaction engines, obtaining thrust in accordance with Newton's third law. Most rocket engines are internal combustion engines, although non-combusting forms (such as cold gas thrusters) also exist. Vehicles propelled by rocket engines are commonly called rockets. Since they need no external material to form their jet, rocket engines can perform in a vacuum and thus can be used to propel spacecraft and ballistic missiles

milan-ransingh

Likes:

Be first to like this answer

Dislikes:

Be first to dislike this answer

Talk about this|Once you have earned teacher badge you can edit this questionDelete|Like|Dislike|

------------------------------------

## Can you help us to add better answer here? Please see this