AT2814 static-thrust figures can help compare specific motor-and-propeller setups and screen their electrical demands, but they cannot tell you how much thrust the setup produces in cruise. Cruise performance requires a propeller thrust and power map at the relevant airspeeds and RPM, plus an aircraft drag estimate. Until those are available, treat cruise thrust, torque, and efficiency as unknown—not as scaled versions of a static result.
What the AT2814 static test does—and does not—tell you
T-Motor’s AT2814 long-shaft listing covers KV900, KV1050, and KV1200 windings. Its propeller-table rows report bench results for named motor and propeller configurations under static conditions. They can support component-level comparisons, but they do not report thrust at a specified forward airspeed.
For example, the manufacturer lists the KV900 with an APC 10×5.5 at 40% command as producing 687 g of static thrust at 6,433 RPM, 15.19 V, and 6.54 A. At 85% command, that pairing is listed at 1,702 g and 9,791 RPM, with 14.90 V and 23.55 A. Those readings belong to those exact table rows; neither is a cruise result.
Propeller behavior changes with advance ratio, J = V/(nD), where V is forward airspeed, n is propeller revolutions per second, and D is diameter. In a static test V is zero, so J is zero. In flight it is not. Without a thrust and power coefficient map over advance ratio—or validated dynamic measurements—a static table leaves in-flight thrust, torque, and propulsive efficiency undetermined. As UNITED UAV puts it, “It is not enough to predict cruise without an airspeed-dependent propeller map.”
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Keep each winding’s electrical limits separate
The manufacturer specifies a 3–4S LiPo range for the long-shaft variants and gives different peak-current and maximum-power figures by KV. The maximum power figures are explicitly limited to 180 seconds; they are not continuous ratings. These are manufacturer product claims, not independent validation of a complete installed powertrain. They do not establish safe limits for the ESC, battery, wiring, connectors, or airframe installation.
| AT2814 winding | Manufacturer peak current | Maximum power and stated duration |
|---|---|---|
| KV900 | 45 A | 650 W for 180 seconds |
| KV1050 | 50 A | 700 W for 180 seconds |
| KV1200 | 55 A | 800 W for 180 seconds |
Do not treat one winding’s limit as applying to another or infer a continuous operating allowance from the 180-second specification. For the KV1200, the listing also gives 108 g including cable, 26 mΩ internal resistance, 1.8 A idle current at 10 V, and 5 mm input and output shaft diameters. These are listing specifications, not substitutes for checking installed-system compatibility.
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A separate KV1200 example published by UNITED UAV illustrates why a static row must also be checked against its duration-qualified electrical boundary. Its 4S APC 9×6 full-command row reports 14.46 V, 49.57 A, 716.86 W, 12,788 RPM, and 2,152 g static thrust. The 4S APC 10×5.5 full-command row reports 14.37 V, 54.64 A, 785.36 W, 12,029 RPM, and 2,616 g. The latter is close to the manufacturer’s KV1200 55 A and 800 W limits specified for 180 seconds; that proximity is a boundary comparison, not evidence of a safe margin or continuous capability.
Estimate the aircraft’s thrust requirement from drag
In steady, level flight, thrust balances drag. Aircraft weight is not the cruise-thrust requirement. Estimate drag at each airspeed using an explicit aerodynamic model and aircraft inputs, then compare that requirement with a propulsion system’s validated in-flight capability.
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A preliminary model uses the drag polar CD = CD0 + k·CL². With dynamic pressure q = 0.5·ρ·V², wing reference area S, and lift approximately equal to weight W in level flight, the corresponding drag estimate is:
D = q·S·CD0 + k·W²/(q·S)
Here, ρ is air density, V is true airspeed, CD0 is the zero-lift drag coefficient, and k represents the induced-drag factor. Required thrust in steady, level flight is approximately D, and useful propulsive power is D·V. The result is only as credible as the input values and the applicability of the drag model.
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Make the inputs traceable
For every candidate flight condition, record aircraft mass, wing reference area, air density, true airspeed, and the source or basis for the drag-polar coefficients. Keep each value tied to its operating condition and provenance. Replace illustrative coefficients with wind-tunnel or flight-identification data when available; example values are not measured aircraft properties.
Account for climb and real-system losses
For a climb, useful power must also supply the rate of gain in potential energy: add W·climb_rate to the drag-power term. Then account for propeller efficiency, motor and ESC losses, installation effects, and operating margin. These factors cannot be recovered from static thrust alone.
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Build a preliminary propulsion envelope without inventing cruise data
- Define flight points. Choose the airspeeds and climb conditions that matter for the mission, and record the airframe inputs needed to estimate drag.
- Calculate required thrust and power. Use the declared aerodynamic model to estimate drag and, for level flight, the useful propulsive power D·V at each point.
- Choose an exact motor-propeller configuration. Keep winding, propeller diameter and pitch, voltage, and test condition attached to every static-table result. Do not combine rows from different KV variants as if they described one configuration.
- Obtain airspeed-dependent propeller data. For each relevant operating point, use thrust and power coefficient maps across advance ratio, or validated dynamic measurements from a suitable wind-tunnel, dynamometer, or flight-derived method. If these are unavailable, mark cruise thrust, torque, and propulsive efficiency as unknown.
- Check the complete electrical and physical installation. Compare loaded voltage, current, and electrical power with the duration-qualified limits for the exact winding. Also assess motor temperature under a stated test duration and cooling condition, along with mass, installation, and clearance constraints.
- Validate before relying on the estimate. Compare predicted and measured behavior under documented conditions, and update the envelope when better aircraft or propulsion data become available.
Do not manufacture a cruise estimate by scaling static thrust with voltage, RPM squared, or throttle percentage. A published Tyto Robotics AT2814 static test record, dated 2023-04-29, explicitly omits dynamic performance and airspeed and recommends internal testing before relying on the data for a design.
Compare configurations on like-for-like terms
Hold the airframe and mission condition constant when assessing candidate propulsion setups. A useful comparison keeps the following dimensions visible rather than ranking motors by their largest static-thrust number:
- Required aircraft drag and thrust across the airspeed range.
- Propeller diameter and pitch, together with its advance-ratio performance map.
- Loaded voltage, current, and electrical power against the exact winding’s duration-qualified limits.
- Motor temperature under a documented test duration, starting temperature, ambient condition, sensor placement, and airflow.
- Motor and propeller mass, installation effects, and airframe clearance.
The manufacturer page includes an operating-temperature field, but without test details it should not be turned into a general thermal model. Temperature readings depend on factors including sensor placement, airflow, starting temperature, and ambient conditions.
Read derived power and efficiency values carefully
Tyto Robotics’ test database focuses on static results and distinguishes several derived quantities. Preserve its definitions and units when repeating them: electrical power is voltage multiplied by current; mechanical power is torque multiplied by rotational speed; motor efficiency is mechanical power divided by electrical power; propeller efficiency is thrust divided by mechanical power; and powertrain efficiency is thrust divided by electrical power. These definitions do not make a static result an in-flight efficiency measurement.
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