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If the densities of the propellants are very different from one another, the pump head raise is ___________ for the lower-density propellant compared to higher-density propellant.

If the densities of the propellants are very different from one another, the pump head raise is ___________ for the lower-density propellant compared to higher-density propellant. Correct Answer higher

Pump head refers to the difference between discharge and suction head of the pump. It is measured in meters or feet. It is much higher for the lower density propellant if the propellant combination used in an engine has a noticeable difference in their densities.

Related Questions

Two centrifugal pumps P and R are available for use in a pipe flow system and their head-discharge characteristics are as follows. Pump P Pump R Discharge (cumecs) Head (m) Discharge (cumecs) Head (m) 0 40 0 45 0.12 35 0.14 40 0.2 28 0.24 35 0.3 18 0.3 28   The following statements (S1, S2, and S3) pertain to the head and discharge values during actual operation. Neglect losses in the system. Which of the following statements are correct? S1: When the two pumps P and R are connected in parallel, the discharge is 0.36 cumecs corresponding to a head of 35 m. S2: When the two pumps P and R are connected in parallel, the discharge is 0.36 cumecs corresponding to a head of 70 m. S3: When the two pumps P and R are connected in series, the discharge is 0.3 cumecs corresponding to a head of 46 m.
For effective propellant utilization, the rate at which tank can expulse the propellants should be ____________ and the amount of residual propellants should be ____________
একটি পানিপূর্ণ কুয়ার গভীরতা 20m ও ব্যাস 2 m. কুয়াটিকে পানি শূণ্য করার জন্য 5 HP এর একটি পাম্প লাগানো হল। অর্ধেক পানি তোলার পর পাম্পটি নষ্ট হয়ে গেল। বাকি পানি তোলার জন্য একই ক্ষমতা সম্পন্ন আর একটি পাম্প লাগানো হল। প্রথম পাম্প দ্বারা সম্পাদিত কাজের পরিমান নির্ণয় কর।(The depth and diameter of a water filled well are 20 m and 2 m respectively. An engine of 5 HP is attached to pump out the water. The pump was ruined after emptying half of the water. Then another pump of same capacity was attached to pump out rest of the water. Determine the work done by first pump.) 
If the motor axial specific impulse of a given nozzle is 340s for propellant ‘A’ and its characteristic velocity is 1400 m/s, determine the specific impulse for the same nozzle using a propellant ‘B’ with a characteristic velocity of 980 m/s. Assume both propellants ‘A’ and ‘B’ have the same specific heat ratio.
What is the major disadvantage associated with solid propellants compared to liquid propellants?
A, B and C are three small pumps fitted to a tank. D is a large pump fitted to the tank. Pump B is 25% more efficient than A. Pump C is 20% more efficient than B. Pump D is 4/3rd efficient of pump C. All of the pumps are used to fill the tank. What is the ratio of the time taken by pumps A and B to fill the tank together to the time taken by the pumps B and D to fill the tank together?
Which one of the following four addresses is NOT EXACTLY the same as the one given below? Robert S Ingram 1998 Revocable 8 Shaftsbury Ln Hilton Head Island, SC 29926 (843) 342­7094 (i) Robert S Ingram 1998 Revocable 8 Shaftsbury Ln Hilton Head Island, SC 29926 (843) 342­7094 (ii) Robert S Ingram 1998 Revocable 8 Shaftsbury Ln Hilton Head Island, SC 29926 (843) 342­7094 (iii) Robert S Ingram 1998 Revocable 8 Shaftsbary Ln Hilton Head Island, SC 29926 (843) 342­7094 (iv) Robert S Ingram 1998 Revocable 8 Shaftsbury Ln Hilton Head Island, SC 29926 (843) 342­7094
A rocket engine moving at 500 m/s produces a total thrust of 9563 N, consuming propellants at the rate of 4.55 kg/s. The energy content of the propellants is 5.35 MJ/kg. Find the effective exhaust velocity.
Propellants that are thick or viscous under static conditions, but flow through valves, injectors, pipes or pumps when adequate shear stress is applied are called __________ propellants.
For pressurizing cryogenic propellant tanks, the amount of gas required is _________ compared to an equivalent tank containing a non-cryogenic propellant.