Standalone component analysis

Model comparison

Fast and Full predictions are evaluated at the same condition. Difference is (Fast minus Full) divided by absolute Full, shown as a percentage; zero or missing Full values have no relative difference. Feasibility and optional ranking use the selected reference model, rather than averaging different fidelities. Equal objective scores share a rank. A satisfied constraint remains satisfied if an objective is undefined; that feasible result is unranked.

Freestream speed

Incoming air speed. The shared backend decomposes this speed and rotor-axis angle into the actual axial and edgewise velocities; the dashboard performs no separate aerodynamic calculations.

Angle to freestream

Rotor-axis angle relative to incoming air: zero is axial, 90 degrees is edgewise and 180 degrees reverses axial inflow. This differs from ground-relative tilt and local blade angle of attack. Select exactly one inflow representation per condition.

Pack length

Physical pack length, required by the component API. The standalone thermal model uses two-node cells and is not a resolved 3D pack mesh.

Pack width

Physical pack width in the account's length units.

Pack height

Physical pack height in the account's length units.

No-load test voltage

Voltage at which no-load current was measured, in volts. This reference is separate from supply voltage and maximum voltage rating.

No-load current

Measured no-load current in amperes at the stated test voltage. Together, these measurements define the motor loss reference.

Select Simulate component in a component catalog to analyze a propeller, motor or battery independently of the full powertrain.

Constraints determine feasibility in every selected condition. An optional objective ranks feasible results; constraints alone do not identify a winner. Search is bounded and does not promise a global optimum. Export actual evaluated results to keep them beyond the 24-hour job retention period; CSV values use canonical SI and JSON retains the request and provenance.

Operating inputs and readouts follow the account's units. Fast propellers use printed labels; Full needs blade geometry and airfoil shapes. Custom geometry can be authored, imported and varied on copies. Protected catalog geometry remains private while aerodynamic diagnostics are available.

RPM

Requested rotational speed. Propellers prescribe it; motors can prescribe it or solve speed from throttle and shaft load. A search axis replaces the fixed value.

Axial inflow

Signed incoming velocity along the rotor axis; negative values describe axial descent or reversed inflow.

Edgewise inflow

Magnitude of incoming air velocity in the rotor disk plane.

Flight speed

Horizontal ground-frame airspeed, combined with vertical speed and rotor tilt.

Vertical speed

Signed vertical flight velocity, following the same convention as the powertrain form.

Rotor tilt

Rotor-axis angle from horizontal: zero points forward and 90 degrees points upward. It is not blade pitch or blade angle of attack.

Air density

Fluid density used in the aerodynamic calculation. Choose density or altitude, not both.

Altitude

Standard-atmosphere altitude used to derive density. Ambient temperature remains explicit.

Ambient temperature

Surrounding air temperature used by the component's atmospheric or thermal model, distinct from an initial component temperature.

Kinematic viscosity

Optional independent fluid viscosity override. Blank uses the model's atmospheric default.

Speed of sound

Optional independent sound-speed override used for Mach effects. Blank uses air temperature.

Blade-angle offset

Collective change to blade pitch angle. This changes the blade, not the rotor's tilt relative to the incoming air.

Supply voltage

Fixed DC supply voltage for the standalone motor and ESC; no battery model is inserted.

Throttle

ESC command for a load-driven operating point. Speed is solved for the given shaft load and supply.

Shaft torque

Mechanical load torque imposed on the motor; an alternative to specifying shaft power.

Shaft power

Mechanical power required by the shaft load; an alternative to specifying torque.

Duration

Requested discharge horizon, subject to charge/voltage cutoff and convergence.

Cooling velocity

Explicit airflow cooling the motor, independent of a propeller slipstream.

Thermal resistance

Optional winding-to-ambient thermal resistance; blank uses the component model.

ESC resistance

ESC conduction resistance, separate from winding resistance.

PWM frequency

Switching frequency used in the ESC and motor loss calculation.

Load current

Constant pack current demand. Power, resistance and time-profile loads are alternatives.

Load power

Constant terminal power demand; current changes as pack voltage changes.

Load resistance

External resistance connected across the pack; not the battery's internal resistance.

Time step

Maximum integration/sample interval. Trajectories are bounded to 2,000 steps per evaluation.

Initial charge

State of charge at the start of the standalone battery analysis.

Initial temperature

Initial battery temperature, distinct from its surrounding air temperature.

Thermal resistance

Optional pack thermal resistance override; blank uses the component/cooling model.

Charge cutoff

Stop the trajectory when charge reaches this reserve threshold.

Cell-voltage cutoff

Optional minimum loaded cell voltage for terminating discharge; blank uses chemistry defaults.

Diameter scale

Scale custom blade radius and diameter together, without modifying the saved source.

Chord scale

Scale a custom blade's chord distribution while retaining its radial locations.

Twist offset

Shift a custom blade's twist distribution by an additive angle.

Thickness scale

Scale the custom blade's section thickness, using its section geometry.

Tip Mach

Tip-speed Mach number from the active propeller model, useful as an operating constraint.

In-plane force

Rotor in-plane aerodynamic force at oblique inflow.

Hover figure of merit

Ideal hover induced power divided by actual shaft power; available only at valid static hover conditions.

Thrust

Axial force predicted by the selected propeller model.

Torque

Shaft torque required to turn the propeller.

Shaft power

Mechanical shaft power, distinct from motor electrical input power.

Efficiency

Propulsive efficiency at the specified flight condition; undefined measures are reported as unavailable.

Thrust coefficient

Conventional n-based thrust coefficient CT = T/(ρ n² D⁴).

Power coefficient

Conventional n-based shaft-power coefficient CP = P/(ρ n³ D⁵).

Advance ratio

Axial advance ratio J = Vaxial/(n D).

Thrust per power

Thrust divided by mechanical shaft power; useful for static comparison.

Exit velocity

The model's predicted wake-exit velocity.

RPM

Actual evaluated propeller rotational speed.

RPM

Motor shaft speed, prescribed or solved for the shaft load.

Shaft torque

Delivered mechanical torque, separate from electromagnetic torque and losses.

Shaft power

Mechanical output power delivered at the shaft.

Electrical power

DC electrical input power billed to the supply.

Supply current

DC current drawn from the external supply.

Phase current

Motor phase-current readout using the production model's convention.

Efficiency

Mechanical output divided by electrical input for the modeled boundary.

Motor losses

Electrical and mechanical loss power in the motor.

ESC losses

Loss power in the selected ESC model.

Winding temperature

Predicted winding temperature after the specified exposure.

Magnet temperature

Predicted magnet/rotor temperature after the specified exposure.

Current margin

Remaining margin relative to the available component current rating.

Power margin

Remaining margin relative to the available component power rating.

Torque residual

Residual of the shaft-load balance; convergence is checked before ranking.

Terminal voltage

Loaded terminal voltage from the pack model.

Load current

Actual current at the evaluation or final trajectory sample.

Load power

Actual terminal power supplied to the external load.

Remaining charge

State of charge at the end of the evaluation/trajectory.

Remaining capacity

Estimated remaining capacity from final charge and pack capacity.

Core temperature

Predicted battery core temperature.

Case temperature

Predicted battery case temperature.

Heat

Pack heat generation from the modeled loss and thermal equations.

Delivered energy

Integral of terminal power over the simulated discharge interval.

Elapsed time

Actual simulated duration; it can stop before the requested horizon at cutoff.

Internal resistance

Pack internal resistance using the model's active state and convention.

Component source

Analyze one catalog or private component, compare selected candidates, or create an inline custom component. Source visibility follows your account.

Propeller model

Fast uses a printed-size label and planform assumptions. Full requires blade geometry and airfoils and uses the production aerodynamic kernel. Models are never silently substituted.

Analysis mode

Point evaluates fixed inputs. Sweep maps selected axes; Target finds an input matching a desired output; Optimize searches a bounded set; Sensitivity varies one axis at a time; model comparison evaluates both propeller models.

Inflow mode

Enter freestream speed and its angle to the rotor axis, axial and edgewise velocities directly, or horizontal speed, vertical speed and rotor tilt in the ground frame. The API rejects conflicting representations.

Atmosphere source

Specify air density directly or derive it from standard-atmosphere altitude. Air temperature and advanced fluid-property overrides remain explicit.

Motor control

Choose prescribed RPM or a load-driven throttle solve. A motor analysis uses an external supply and shaft load, with no inserted propeller or battery.

Shaft load

Specify required mechanical torque or shaft power. The active motor/ESC model checks the operating point's feasibility.

Battery load

Choose constant current, constant power, an external resistance or a time profile. Only one load representation is active.

Custom component

Inline custom specifications are copied into the analysis. Existing saved components are not changed by a search or geometry transformation.

Blade geometry

Author radius, chord, twist and thickness station data and select section airfoils. The geometry service materializes the blade for Full analysis.

Section airfoils

Select section shapes from the library or your own imported airfoils. Lift and drag are computed by the solver; they are not entered as coefficients.

Import specification

Load an exported JSON custom specification. Operating inputs are still edited in the form and the API validates the imported shape.

Variables

Choose operating inputs to vary, or custom propeller geometry transformations. Other inputs remain fixed; conditions override only operating values.

Parameter

Select a supported numeric operating input or custom geometry parameter. Each axis is distinct.

Minimum

Lower bound for the selected search or tolerance-study variable, displayed in your active units.

Maximum

Upper bound for the selected variable. It must exceed the minimum and satisfy the input's physical bounds.

Samples

Number of samples along an axis. A sweep's total work is the product of axis counts, candidates and conditions.

Remove

Remove this editable row or selection from the current request; it does not delete any saved component.

Constraints

Every selected condition must satisfy all constraints. Without an objective, feasible results have no ranking and no implied best result.

Metric

Choose the supported output used by a constraint, objective, target or plot. Undefined values do not satisfy a constraint or rank as successful results.

Comparison

Use at least, at most or equality within an explicit absolute tolerance.

Value

Constraint or target value in the selected metric's units. Changing the metric requires reconsidering this value.

Tolerance

Absolute permitted error in the selected metric's units. Equality constraints and target solves use this tolerance.

Objective

An optional objective ranks only feasible results. Leaving it disabled returns feasible samples without a winner.

Direction

Minimize or maximize the selected output, or minimize its absolute difference from a target value.

Aggregation

Weighted mean normalizes condition weights. Worst condition scores the conservative result. Feasibility is required in every condition.

Target

Find values of one bounded operating input that meet the selected output within tolerance. The search can discover more than one solution.

Conditions

Evaluate the same component or custom geometry at several labeled flight or load conditions. Each row can override operating inputs.

Condition name

Unique label identifying this flight or load condition in the returned results.

Weight

Nonnegative relative importance for weighted-mean objectives. At least one condition must have positive weight.

Condition inputs

Operating values overriding the base form in this condition. Switching representations replaces conflicting base fields.

Evaluation budget

Maximum actual component evaluations, including candidates, conditions and target-search refinement. The server caps it at 1,024.

Search seed

Reproducible seed for bounded sampled optimization. Deterministic grids retain their source/sample order without an objective.

Thermal model

Enable the component's supported thermal behavior. Motor results use the production finite-horizon equilibrium target; battery trajectories integrate core and case temperatures.

ESC type

Select the supported field-oriented or six-step drive model used by the motor's equations.

ESC timing

Select the timing policy used by the active ESC/motor modulation model.

Synchronous rectification

Enable synchronous rectification in the ESC loss model.

Cooling regime

Battery cooling setting, independent of any simulated propeller. Explicit thermal resistance can override the component's default.

Load profile

Time-ordered battery load rows beginning at zero. Each row selects current, power or resistance; row values apply until the next time.

Run analysis

Submit this request to the public API. Longer calculations run as an owner-scoped job, independent of the powertrain queue.

Cancel analysis

Request cooperative cancellation between evaluations. Cancelling a completed analysis does not erase its results.

Export

Download the actual result table as CSV or the request/result/provenance as JSON. Jobs expire 24 hours after submission.

Evaluated results

Inspect feasible and infeasible samples, per-condition outputs, constraints, warnings and numerical failures. A winner is identified only when an objective is supplied.

Inspect result

Select a evaluated candidate and condition to inspect its summary and diagnostics. This selection does not change the analysis or its ranking.

Operating plot

Plot actual evaluated outputs against selected operating/search axes. Two-axis sweeps can be displayed as operating maps; failed or undefined points are omitted.

Radial diagnostics

Aerodynamic section loading, angle of attack, Reynolds and Mach along r/R where provided by the selected model. The badge identifies Fast or Full; protected catalog geometry is not disclosed.

Discharge trajectory

Plot actual battery voltage, current, charge and temperature samples, including early termination at cutoff.

Sensitivity results

Changes in selected output metrics when each variable is perturbed across its bounds with other inputs held fixed.

Job status

Queued, running, completed, failed or cancelled. Progress counts actual evaluated points; partial failures are reported in the result.

Simulate component

Open the standalone analysis workspace for this component type, separate from full powertrain simulation.

Back to catalog

Return to this component catalog without altering saved components.

Component name

Label for this inline component; it does not rename a saved source.

Diameter

Diameter in the selected length units. Fast uses the label; Full requires matching physical station geometry.

Printed pitch

Printed geometric pitch used by the Fast model, independent of freestream angle.

Reference pitch

Nominal pitch metadata used during geometry creation. Explicit Full-model station twist defines the actual blade angles.

Blade count

Blade count: Fast supports 2–8 and Full supports 1–16 blades.

Camber

Section camber as a percentage of chord for Fast analysis.

Planform family

Fast-model family determines chord ratio at 75% radius. Custom exposes this ratio explicitly.

Chord / diameter at 75% radius

Fast custom-family chord at 75% radius divided by diameter, dimensionless.

Maximum RPM

Mechanical RPM rating of the custom propeller. A rating exceedance is infeasible; the requested operating RPM is separate.

KV

Motor speed constant in rpm per volt.

Pole count

Even magnetic pole count; this is the total poles, not pole pairs.

Winding resistance

Measured phase-to-phase winding resistance in ohms. The production builder handles the per-phase convention.

Phase inductance

Per-phase motor inductance in henries; it must be positive.

Motor diameter

Housing diameter in the account's length units.

Motor length

Housing length in the account's length units.

Motor mass

Mass in the account's mass units, used by thermal/inertia estimates.

Current rating

Available manufacturer current rating in amperes; it supplies a feasibility margin.

Power rating

Available manufacturer electrical-input power rating in watts.

Series cells

Cells in series set the pack voltage. The standalone pack has an explicit S/P composition.

Parallel cells

Number of parallel cells in each series position. Capacity and resistance follow the production pack builder.

Pack capacity

Total capacity in mAh, including parallel cells.

Pack resistance

Total internal pack resistance in milliohms, distinct from the external load.

Pack mass

Total pack mass used by thermal estimates.

Chemistry

Choose the actual chemistry. NMC, NCA and LFP are distinct; unknown chemistry does not silently become LiPo.

Source voltage

Constant voltage of an ideal source, in volts; this source does not simulate finite battery capacity.

r/R

Normalized station radius from the rotor center, strictly increasing within (0,1].

c/R

Section chord divided by tip radius. Geometry generation converts the authored ratio to physical metres.

Twist

Local geometric blade pitch angle in degrees, not local aerodynamic angle of attack.

t/c

Section thickness divided by local chord; the selected airfoil shape is materialized by the geometry service.

Entropic heat

Enable the supported reversible entropic heating term in battery thermal integration. This does not add aging or dynamic hysteresis.