Axial Compressor Stage Calculator
An axial stage at 300 m/s blade speed adding 100 m/s of whirl does 30 kJ/kg of work, raising the temperature 29.9 K for a stage pressure ratio of 1.35711.
Air 1.4; hot combustion gases about 1.3; helium 1.667.
1.35710638590312
Full answer, then cut to fewer decimals (not rounded):
- 1.35710638590312
- 1.3571063859031
- 1.357106385903
- 1.35710638590
- 1.3571063859
- 1.357106385
- 1.35710638
- 1.3571063
- 1.357106
- 1.35710
- 1.3571
- 1.357
- 1.35
- 1.3
- Specific work w = U(C_θ2 − C_θ1)
- 30 kJ/kg
- Stagnation temperature rise ΔT₀ = w/c_p
- 29.85074627 K
- Degree of reaction R = 1 − (C_θ1 + C_θ2)/2U
- 0.5
- Work coefficient ψ = ΔC_θ/U
- 0.3333333333
Step-by-step solution
- w = U ΔC_θ = 300 × (200 − 100) = 30000 J/kg (Euler turbomachine equation)
- ΔT₀ = w ÷ c_p = 29.85074627 K
- π = (1 + η ΔT₀/T₀₁)^(γ/(γ−1)) = 1.357106386
Axial Compressor Stage Formula
w = U(C_θ2 − C_θ1), ΔT₀ = w/c_p
π = (1 + ηΔT₀/T₀₁)^(γ/(γ−1)); R = 1 − (C_θ1 + C_θ2)/(2U)
Worked Example
A stage with U = 300 m/s turning the whirl from 100 to 200 m/s at 288 K inlet and 88 % efficiency:
- w = U ΔC_θ = 300 × (200 − 100) = 30000 J/kg (Euler turbomachine equation)
- ΔT₀ = w ÷ c_p = 29.85074627 K
- π = (1 + η ΔT₀/T₀₁)^(γ/(γ−1)) = 1.357106386
Stagnation temperature rise ΔT₀ = w/c_p: 29.85074627 K · Degree of reaction R = 1 − (C_θ1 + C_θ2)/2U: 0.5 · Work coefficient ψ = ΔC_θ/U: 0.3333333333
GATE tip
With velocity triangles: ΔC_θ = C_a(tan β₁ − tan β₂) using relative flow angles. For n identical stages the overall ratio is roughly the product of the stage ratios.
More Propulsion Calculators
-
Jet Engine Thrust Calculator
F = ṁₐ[(1 + f)vₑ − V₀] + Bṁₐ(v_f − V₀)
TSFC = ṁ_f/F; η_p = FV₀/ΔKE; η_th = ΔKE/(ṁ_f Q_R)
Example: A turbojet with 50 kg/s of air, f = 0.02, flying at 250 m/s with a 600 m/s jet: Thrust F = 18.1 kN.
-
Rocket Equation Calculator
Δv = I_sp g₀ ln(m₀ / m_f)
m₀ initial (wet) mass, m_f final (dry) mass, g₀ = 9.80665 m/s², vₑ = I_sp g₀
Example: A stage with I_sp = 350 s burning from 100 t to 10 t: Delta-v Δv = 7903.23 m/s.
-
Rocket Thrust Calculator
F = ṁvₑ + (pₑ − pₐ)Aₑ
I_sp = F/(ṁg₀); effective exhaust velocity c = F/ṁ
Example: 250 kg/s at 3000 m/s, exit pressure 70 kPa, 0.8 m² exit at sea level: Thrust F = 724.94 kN.
Frequently asked questions
What is the degree of reaction?
The share of the stage’s static enthalpy rise that happens in the rotor. 50 % reaction gives symmetric velocity triangles and is common in compressors.
Why are compressor stages limited to low pressure ratios?
Flow decelerates in the blade passages against a rising pressure; too much diffusion separates the boundary layer and stalls the blades, so stages give only about 1.2–1.4 each.
Sources
- The International System of Units (SI), 9th edition (SI Brochure), Bureau International des Poids et Mesures .
Last reviewed: . Factors are stored exactly and computed with 50-digit decimal arithmetic. See how we verify conversion factors.
Cite this page
APA
Scientific Converters. (2026, October 15). Axial Compressor Stage Calculator. Retrieved October 25, 2026, from https://scientificconverters.com/calculators/axial-compressor-calculator/
IEEE
Scientific Converters, "Axial Compressor Stage Calculator," scientificconverters.com. Accessed: Oct. 25, 2026. [Online]. Available: https://scientificconverters.com/calculators/axial-compressor-calculator/