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Engineering casebook

Case 10 / Aerodynamic modelling

DATCOM aerodynamic modelling workflow

Read an aerodynamic input deck, connect geometry and flight conditions to coefficient outputs, and explore a credited reference dataset.

Geometry inputs · coefficient analysis · reference-data explorer
Aerodynamics & CFDFlight dynamicsMATLAB/Simulink
My work

DATCOM input development and aerodynamic data interpretation

The engineering question

Can you trace an aerodynamic curve back to the geometry, condition, units and source that produced it?

I adapted DATCOM input decks and interpreted aerodynamic outputs as part of the aircraft-design workflow. This case connects reference geometry and flight conditions to lift, drag and pitching-moment coefficients. The interactive explorer uses a credited Citation reference dataset to demonstrate coefficient interpretation.

Inside the method

Method and workflow

  1. 01

    Identify the source

    Separate supplied examples from a modified deck and retain the original template attribution.

  2. 02

    Read the definition

    Inspect reference quantities, geometry, flight conditions and the units requested by the deck.

  3. 03

    Read the outputs

    Keep static coefficients and derivative units distinct. View lift, drag and moment over the sampled incidence range.

  4. 04

    Check the connection

    Require a documented geometry mapping before treating a CAD model and a coefficient table as the same aircraft.

Citation reference model

Read the coefficient curves.

Download this reference ↗

Reference dataset: DATCOM+ Citation example. Input template: Bill Galbraith, Holy Cows, Inc.

Incidence2°
Lift coefficient0.2411CL
Drag coefficient0.0093CD
Pitch moment-0.0556Cm
Lift coefficientCL
-0.34-0.00840.330.661.00Citation CL: 2.00, 0.24-6.003.0012.00Incidence (°)
Citation CL
Pitching-moment coefficientCm
-0.37-0.22-0.08260.05900.20Citation Cm: 2.00, -0.0556-6.003.0012.00Incidence (°)
Citation Cm

These curves belong to the supplied Citation reference example. A negative pitching-moment slope describes a local restoring tendency at the reference condition; complete aircraft stability requires further analysis.

Project figures / 2 selected figures

Project figures

01 / 02
Design-study aerodynamic output
Design-study aerodynamic output
Design-study aerodynamic output

Aerodynamic analysis output from the joint design report. The interactive Citation reference curves are a separate dataset.

Open full-size image ↗
Technical notes

Model assumptions and scope

  • The interactive curves use the Citation reference dataset credited below; they are separate from the FireBolt configuration.
  • Geometry, reference quantities and units must be consistent when transferring coefficients into a flight-dynamics model.
  • DATCOM estimates are presented without wind-tunnel or flight-test correlation.
Potential extensions

Document the geometry mapping and unit conventions of the adapted model before comparing its outputs with other analysis tools.

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