Aircraft Propulsion·compressor-hub-tip-radius-geometry

Compressor Hub Tip Radius Geometry

For an annular compressor blade row with a known hub-to-tip radius ratio and tip radius (or tip speed and rotational speed), determine the hub radius and annular area. This is used to define the meridional geometry and blade stacking.

✓ All 2 test cases pass.

Inputs

Tip radius

Radius at blade tip (m)

Hub-to-tip radius ratio

Ratio of hub radius to tip radius (dimensionless)

Test cases

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#	Inputs	Expected	Got	Status
1	{"tip_radius":0.5,"hub_tip_ratio":0.488}	0.244	0.244	✓
2	{"tip_radius":1,"hub_tip_ratio":0.6}	0.6	0.6	✓

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Endpoint

POST/api/calculators/aircraft-propulsion/compressor-hub-tip-radius-geometry/compute

Inputs (2)

tip_radiusnumberdefault 0.5
hub_tip_rationumberdefault 0.488

Example

curl -sX POST http://localhost:3001/api/calculators/aircraft-propulsion/compressor-hub-tip-radius-geometry/compute \
  -H "Content-Type: application/json" \
  -d '{"inputs":{"tip_radius":0.5,"hub_tip_ratio":0.488}}'

Try it live

Edit the body below, then click Call API.

Request body

Response

(click Call API to see the response)

full API docs →

Source: Pattern from: 19870008266.pdf. Reproduces a standard compressor-hub-tip-radius-geometry computation; problem text paraphrased.

AI disclosure: Calculator code generated by anthropic/claude-haiku-4-5-20251001; verified by 2 test cases.