DATASET-2026-01 // COMPUTATIONAL BENCHMARKLicense: CC BY 4.0Aeroway Computational QA:
ICAO Standard Atmosphere & Density Altitude Benchmark Matrix
A computational benchmark of 6,885 discrete atmospheric calculation points spanning −1,000 ft to +20,000 ft geopotential altitude and −30°C to +50°C temperature. Features analytical density-altitude inversions and quantitative error divergence for the 120 ft/°C flight-training heuristic.
Format: CSV (458 KB, 6,885 data rows, 11 columns)
1. Grid Specifications & Envelope
Altitude Range (H)
−1,000 to +20,000 ft
250-ft increments (85 discrete levels)
Temperature Envelope
−30°C to +50°C
1°C increments (81 discrete levels)
Discrete Calculation Points
6,885 Points
85 × 81 parameter combinations
2. Representative Data Samples
Sample extract from 6,885 calculation records| Scenario | Geopotential Alt | OAT | ISA Dev | Pressure | Density | Analytical DA | Heuristic DA | DA Error | TAS Factor |
|---|---|---|---|---|---|---|---|---|---|
| Sea Level Standard Point | 0 ft | 15.0°C | 0.00°C | 101,325.00 Pa | 1.2250 kg/m³ | 0 ft | 0 ft | 0 ft | 1.0000 |
| 5,000 ft near-standard | 5,000 ft | 5.0°C | −0.09°C | 84,307.25 Pa | 1.0558 kg/m³ | 4,988 ft | 4,989 ft | +1 ft | 0.9998 |
| 10,000 ft near-standard | 10,000 ft | −5.0°C | −0.19°C | 69,681.64 Pa | 0.9052 kg/m³ | 9,978 ft | 9,977 ft | −1 ft | 0.9996 |
| High & Hot Condition | 10,000 ft | +25.0°C | +29.81°C | 69,681.64 Pa | 0.8142 kg/m³ | 13,312 ft | 13,577 ft | +265 ft | 1.0540 |
| 15,000 ft near-standard | 15,000 ft | −15.0°C | −0.28°C | 57,181.99 Pa | 0.7716 kg/m³ | 14,967 ft | 14,966 ft | −1 ft | 0.9995 |
| 20,000 ft near-standard | 20,000 ft | −25.0°C | −0.38°C | 46,563.24 Pa | 0.6534 kg/m³ | 19,955 ft | 19,954 ft | −1 ft | 0.9992 |
| Cold-Weather Inversion | 5,000 ft | −20.0°C | −25.09°C | 84,307.25 Pa | 1.1601 kg/m³ | 1,846 ft | 1,989 ft | +143 ft | 0.9538 |
3. Complete Data Dictionary (11 Fields)
| Column | Type | Units | Mathematical Formulation & Description |
|---|---|---|---|
| Elevation_ft | Integer | ft | Input geopotential altitude coordinate (H) within the troposphere (−1,000 to +20,000 ft in 250-ft steps). |
| Temperature_C | Integer | °C | Independently varied ambient outside air temperature (OAT) from −30°C to +50°C in 1°C steps. |
| ISA_Temperature_C | Float | °C | Standard ISA temperature corresponding to altitude coordinate: TISA = 15.0 − 0.0019812 · H. |
| ISA_Deviation_C | Float | °C | Temperature departure: ΔTISA = Temperature_C − ISA_Temperature_C. |
| Pressure_Pa | Float | Pa | Standard-atmosphere static pressure corresponding to altitude coordinate H. Actual temperature is varied independently to compute density. |
| Density_kg_m3 | Float | kg/m³ | Calculated air density from ideal gas equation: ρ = P / (R · TK), with dry air constant R = 287.05287 J/(kg·K). |
| Density_Ratio_sigma | Float | — | Local density ratio relative to standard density at the same altitude: σlocal = ρ / ρISA(H) = TISA,K / TK. |
| Exact_Density_Altitude_ft | Integer | ft | Analytical density-altitude inversion based on standard-atmosphere formulation: 145366.45 · (1 − (ρ/ρ₀)0.234969). |
| Heuristic_Density_Altitude_ft | Integer | ft | Flight-training 120 ft/°C rule-of-thumb estimate: Elevation_ft + (120 · ISA_Deviation_C). |
| DA_Error_ft | Integer | ft | Heuristic divergence error delta: Heuristic_Density_Altitude_ft − Exact_Density_Altitude_ft. |
| TAS_Multiplier | Float | — | Theoretical true airspeed factor for equivalent aerodynamic dynamic pressure: 1 / √(σlocal). |
4. Mathematical Methodology & Analytical Inversion
Based on the adopted ICAO Standard Atmosphere / U.S. Standard Atmosphere 1976 formulation
Static Ambient Pressure P(H)
Hydrostatic equilibrium integrated across the standard tropospheric lapse rate (L = 0.0019812 K/ft):
P(H) = P₀ · [1 − (L·H / T₀)](g₀ / RL)
Where P₀ = 101,325 Pa, T₀ = 288.15 K, R = 287.05287 J/(kg·K), and exponent κ = 5.25588.
Aeroway Analytical DA Inversion
Solving analytically for altitude hDA where standard density equals ambient density ρ:
hDA = (T₀ / L) · [1 − (ρ / ρ₀)0.234969]
With coefficient (T₀ / L) = 145,366.45 ft, standard sea-level density ρ₀ = 1.22500 kg/m³, and constant-lapse troposphere limitation.
5. Attribution & Citation
Creative Commons Attribution 4.0 International (CC BY 4.0)APA (7th Edition)
Aeroway Flight Engineering. (2026). ICAO Standard Atmosphere & Density Altitude Computational Benchmark Matrix (Version 1.0) [Data set]. Figshare. https://doi.org/10.6084/m9.figshare.34059369
BibTeX
@dataset{aeroway_density_altitude_benchmark_2026,
author = {{Aeroway Flight Engineering Team}},
title = {{ICAO Standard Atmosphere & Density Altitude Computational Benchmark Matrix}},
month = oct,
year = 2026,
publisher = {Figshare},
version = {1.0.0},
doi = {10.6084/m9.figshare.34059369},
url = {https://doi.org/10.6084/m9.figshare.34059369},
note = {Computational benchmark grid based on standard atmosphere formulations (-1,000 ft to +20,000 ft, -30°C to +50°C)}
}Explore Interactive Calculations
Test scenarios dynamically in the Aeroway density altitude laboratory and checkride training tools.