Area · total pressure · temperature · Mach

Compressible mass flow

Inputs

Declared flow areaAUser-entered flow area; nozzle, throat, and duct geometry are not derived.

Declared total pressureptUser-entered absolute total pressure; pressure losses and state conversion are not derived.

Declared total temperatureTtUser-entered absolute total temperature; heat transfer and temperature state are not derived.

Declared Mach numberM—User-entered Mach number; this workspace does not determine flow regime or choking.

Declared specific-heat ratioγ—User-entered ideal-gas specific-heat ratio; gas properties are not derived.

Declared specific gas constantRJ/(kg·K)User-entered specific gas constant; gas composition and properties are not derived.

Literal ideal compressible mass flow

3.4833

kg/s

Declared Mach number

0.5

—

Declared flow areaA

0.01

Declared total pressure

200,000

ṁ = (A·pt/√Tt)·√(γ/R)·M·[1 + ((γ − 1)/2)·M²]^(−(γ + 1)/(2(γ − 1)))

A first-pass number, not a code check, certification, or approval. Read the method and its limits below. What this is and is not.

Calculation snapshot

Formula version 1.0.0

Declared flow area	0.01
Declared total pressure	200000
Declared total temperature	300
Declared Mach number	0.5
Declared specific-heat ratio	1.4
Declared specific gas constant	287

Literal ideal compressible mass flow	3.4833 kg/s
Declared Mach number	0.5 —
Declared flow area	0.01 m²
Declared total pressure	200,000 Pa

ṁ = (A·pt/√Tt)·√(γ/R)·M·[1 + ((γ − 1)/2)·M²]^(−(γ + 1)/(2(γ − 1)))

NASA Glenn mass-flow equations: https://www1.grc.nasa.gov/beginners-guide-to-aeronautics/mass-flow-rate-equations/

This printout is a record of displayed inputs and deterministic formula output. It is not an approval, certification, or engineering conclusion.

Method

Apply NASA’s ideal isentropic mass-flow relation to gas-state and flow inputs without determining Mach number, choking, or nozzle geometry.

ṁ = (A·pt/√Tt)·√(γ/R)·M·[1 + ((γ − 1)/2)·M²]^(−(γ + 1)/(2(γ − 1)))

When

Don’t

This applies NASA’s stated ideal isentropic mass-flow relation only to user-declared area, total state, Mach number, specific-heat ratio, and gas constant. It does not determine Mach number, gas properties, choking, nozzle or duct geometry, pressure losses, heat transfer, flow regime, capacity, safety, suitability, or approval.