Calculadora de Velocidad del Aire Gratis
Convierte entre velocidad indicada, calibrada, equivalente y verdadera del aire. Para pilotos e ingenieros.
True Airspeed (TAS)
280.6 knots
True Airspeed (TAS) vs Indicated Airspeed (IAS)
Fórmula
## Indicated vs True Airspeed Indicated airspeed (IAS) is what the pitot-static system reads, calibrated for sea-level standard density. As altitude increases and air density decreases, the true airspeed (TAS) becomes higher than the indicated reading. ### Simplified Relationship **TAS = IAS / sqrt(sigma)** where sigma is the density ratio (local density divided by sea-level standard density). This approximation is valid for low subsonic speeds where compressibility effects are negligible.
Ejemplo Resuelto
An aircraft reads 250 KIAS at 10,000 ft pressure altitude with OAT of -5°C.
- 01ISA temperature at 10,000 ft = 15 - 1.981 × 10 = -4.81°C
- 02Temperature ratio component = 288.15 / 268.15 = 1.0746
- 03Pressure ratio component = (1 - 0.000006875 × 10000)^4.2561 = 0.6877
- 04Density ratio sigma = 1.0746 × 0.6877 = 0.7392
- 05TAS = 250 / sqrt(0.7392) = 250 / 0.8598 = 290.8 knots
Preguntas Frecuentes
Why is TAS higher than IAS at altitude?
At higher altitudes, the air is less dense. The pitot tube senses lower ram pressure for the same true speed, so IAS under-reads. TAS corrects for this density difference.
When does compressibility matter?
Above about Mach 0.3 (roughly 200 knots TAS at sea level), compressibility effects become significant and the simple IAS/sqrt(sigma) formula loses accuracy. Calibrated airspeed (CAS) corrections are needed.
What is equivalent airspeed (EAS)?
EAS is IAS corrected for compressibility but not for density. TAS = EAS / sqrt(sigma). For low speeds, EAS ≈ IAS, making TAS ≈ IAS / sqrt(sigma).
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