TAS, density alt, Mach API

Computes true airspeed from calibrated airspeed plus pressure altitude and OAT, returning density altitude, density ratio, speed of sound and Mach. Answers 'What is my TAS at 8000 ft and 0 C?', 'What density altitude and Mach correspond to this CAS?'.

Price$0.06per request

MethodPOST

Route/v1/nav/true-airspeed

StatusLive

MIME typeapplication/json

Rate limit120/minute

Cache0s public

aviationtrue-airspeedtascasdensity-altitudemachisaperformance

API URLhttps://x402.hexl.dev/v1/nav/true-airspeed

Integration docs

Example request

{
  "calibratedAirspeedKt": 120,
  "pressureAltitudeFt": 8000,
  "oatC": 0
}

Example response

{
  "trueAirspeedKt": 135.6,
  "densityAltitudeFt": 8101,
  "densityRatioSigma": 0.7836,
  "isaTempAtAltitudeC": -0.8,
  "speedOfSoundKt": 644,
  "machNumber": 0.21,
  "tasOverCasFactor": 1.1297,
  "interpretation": "TAS 136 kt (CAS 120), density altitude 8101 ft, Mach 0.21."
}

Input schema

{
  "type": "object",
  "required": [
    "calibratedAirspeedKt",
    "pressureAltitudeFt",
    "oatC"
  ],
  "properties": {
    "calibratedAirspeedKt": {
      "type": "number",
      "examples": [
        120
      ]
    },
    "pressureAltitudeFt": {
      "type": "number",
      "examples": [
        8000
      ]
    },
    "oatC": {
      "type": "number",
      "examples": [
        0
      ]
    }
  }
}

Output schema

{
  "type": "object",
  "additionalProperties": true
}