Dynamic Pressure given Normal Pressure Calculator

✖Specific Heat of Air is the heat required to raise the temperature of air by one degree to that required to raise the temperature of an equal mass of water by one degree.ⓘ Specific Heat of Air [cp]			+10% -10%
✖Pressure is the force applied perpendicular to the surface of an object per unit area over which that force is distributed.ⓘ Pressure [p]			+10% -10%
✖Mach Number is a dimensionless quantity defined as ratio of speed of object to speed on sound.ⓘ Mach Number [M_r]			+10% -10%

✖Dynamic Pressure is simply a convenient name for the quantity which represents the decrease in the pressure due to the velocity of the fluid.ⓘ Dynamic Pressure given Normal Pressure [q]

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Formula

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Dynamic Pressure given Normal Pressure

Formula

q = \frac{1}{2} \cdot cp \cdot p \cdot {M r}^{2}

Example

70.59468 Pa = \frac{1}{2} \cdot 0.003 J/(kg*K) \cdot 800 Pa \cdot {7.67}^{2}

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Dynamic Pressure given Normal Pressure Solution

STEP 0: Pre-Calculation Summary

Formula Used

Dynamic Pressure = 1/2*Specific Heat of Air*Pressure*Mach Number^2
q = 1/2*cp*p*M_r^2
This formula uses 4 Variables

Variables Used

Dynamic Pressure - (Measured in Pascal) - Dynamic Pressure is simply a convenient name for the quantity which represents the decrease in the pressure due to the velocity of the fluid.
Specific Heat of Air - (Measured in Joule per Kilogram per K) - Specific Heat of Air is the heat required to raise the temperature of air by one degree to that required to raise the temperature of an equal mass of water by one degree.
Pressure - (Measured in Pascal) - Pressure is the force applied perpendicular to the surface of an object per unit area over which that force is distributed.
Mach Number - Mach Number is a dimensionless quantity defined as ratio of speed of object to speed on sound.

STEP 1: Convert Input(s) to Base Unit

Specific Heat of Air: 0.003 Joule per Kilogram per K --> 0.003 Joule per Kilogram per K No Conversion Required
Pressure: 800 Pascal --> 800 Pascal No Conversion Required
Mach Number: 7.67 --> No Conversion Required

STEP 2: Evaluate Formula

Substituting Input Values in Formula

q = 1/2*cp*p*M_r^2 --> 1/2*0.003*800*7.67^2

Evaluating ... ...

q = 70.59468

STEP 3: Convert Result to Output's Unit

70.59468 Pascal --> No Conversion Required

FINAL ANSWER

70.59468 Pascal <-- Dynamic Pressure

(Calculation completed in 00.004 seconds)

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Created by Himanshu Sharma

National Institute of Technology, Hamirpur (NITH), Himachal Pradesh

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< Preliminary Aerodynamics Calculators

Power required at sea-level conditions

Go Power Required at Sea-level = sqrt((2*Weight of Body^3*Drag Coefficient^2)/([Std-Air-Density-Sea]*Reference Area*Lift Coefficient^3))

Power required at Altitude

Go Power Required at Altitude = sqrt((2*Weight of Body^3*Drag Coefficient^2)/(Density*Reference Area*Lift Coefficient^3))

Velocity at Sea-Level given Lift Coefficient

Go Velocity at Sea-Level = sqrt((2*Weight of Body)/([Std-Air-Density-Sea]*Reference Area*Lift Coefficient))

Velocity at Altitude

Go Velocity at an Altitude = sqrt(2*Weight of Body/(Density*Reference Area*Lift Coefficient))

Dynamic Pressure given Normal Pressure Formula

Dynamic Pressure = 1/2*Specific Heat of Air*Pressure*Mach Number^2
q = 1/2*cp*p*M_r^2

What is dynamic pressure?

the pressure on a surface at which a flowing fluid is brought to rest in excess of the pressure on it when the fluid is not flowing is dynamic pressure.

How to Calculate Dynamic Pressure given Normal Pressure?

Dynamic Pressure given Normal Pressure calculator uses Dynamic Pressure = 1/2*Specific Heat of Air*Pressure*Mach Number^2 to calculate the Dynamic Pressure, Dynamic Pressure given Normal Pressure is a measure of the pressure exerted by a fluid or gas in motion, calculated as one half the product of the specific heat of air, the pressure, and the square of the Mach number. Dynamic Pressure is denoted by q symbol.

How to calculate Dynamic Pressure given Normal Pressure using this online calculator? To use this online calculator for Dynamic Pressure given Normal Pressure, enter Specific Heat of Air (cp), Pressure (p) & Mach Number (M_r) and hit the calculate button. Here is how the Dynamic Pressure given Normal Pressure calculation can be explained with given input values -> 70.96332 = 1/2*0.003*800*7.67^2.

FAQ

What is Dynamic Pressure given Normal Pressure?

Dynamic Pressure given Normal Pressure is a measure of the pressure exerted by a fluid or gas in motion, calculated as one half the product of the specific heat of air, the pressure, and the square of the Mach number and is represented as q = 1/2*cp*p*M_r^2 or Dynamic Pressure = 1/2*Specific Heat of Air*Pressure*Mach Number^2. Specific Heat of Air is the heat required to raise the temperature of air by one degree to that required to raise the temperature of an equal mass of water by one degree, Pressure is the force applied perpendicular to the surface of an object per unit area over which that force is distributed & Mach Number is a dimensionless quantity defined as ratio of speed of object to speed on sound.

How to calculate Dynamic Pressure given Normal Pressure?

Dynamic Pressure given Normal Pressure is a measure of the pressure exerted by a fluid or gas in motion, calculated as one half the product of the specific heat of air, the pressure, and the square of the Mach number is calculated using Dynamic Pressure = 1/2*Specific Heat of Air*Pressure*Mach Number^2. To calculate Dynamic Pressure given Normal Pressure, you need Specific Heat of Air (cp), Pressure (p) & Mach Number (M_r). With our tool, you need to enter the respective value for Specific Heat of Air, Pressure & Mach Number and hit the calculate button. You can also select the units (if any) for Input(s) and the Output as well.

How many ways are there to calculate Dynamic Pressure?

In this formula, Dynamic Pressure uses Specific Heat of Air, Pressure & Mach Number. We can use 3 other way(s) to calculate the same, which is/are as follows -

Dynamic Pressure = Lift Force/Lift Coefficient
Dynamic Pressure = Drag Force/Drag Coefficient
Dynamic Pressure = 1/2*Ambient Air Density*Flight Speed^2

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