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The MN4010 title alone cannot produce a finished motor operating point. A point needs an aircraft mass, a rotor count, a mission profile and a propeller, and none of these are given here. What you can do is follow a fixed sequence: define the mission, find the conditions that demand the most from each motor, match those conditions to a specific MN4010 variant and propeller test row, and then check the electrical, thermal and control margins that a bench table does not show.
What counts as an operating point
An operating point is a set of measured conditions, not a throttle setting. For a motor, it means the motor, the propeller, the battery voltage and the load, together with the results they produce: thrust, current, input power, RPM and temperature. A statement such as “75% throttle” is meaningless for design work unless the variant, propeller and voltage are attached to it. Any value you carry forward should keep those three items with it.
Step 1: Define the vehicle and mission
Start by writing down the inputs that the sizing depends on. Missing any one of them makes the rest of the calculation unreliable.
| Input | What to record | Why it matters |
|---|---|---|
| Takeoff mass | Airframe, payload and battery, as a single figure | Sets the total thrust the rotors must produce in hover |
| Lifting rotors | Number of active rotors and their positions | Determines how thrust is split between motors |
| Mission segments | Each segment with its duration and, where relevant, distance | Different segments impose different thrust and power levels |
| Environment | Altitude and ambient temperature | Air density changes the thrust a given propeller produces |
| Forward speed | Speed in each segment where it applies | Affects transition and cruise loads |
| Reserve | Energy or time reserve the mission must keep | Limits how much of the battery is available for the mission itself |
| Degraded or control cases | Conditions such as a lost rotor or a required maneuver, if they apply | Can set the highest demand on individual motors |
NASA’s NDARC documentation (Input – Vol 3, dated 2022 in NASA’s NTRS record) frames the problem this way: “The sizing task determines the dimensions, power, and weight of a rotorcraft that can perform a specified set of design conditions and missions.” In that framework a mission is a sequence of segments, and each segment is evaluated for time, distance and energy or fuel use. The motor selection follows from that analysis rather than from a single headline maximum thrust.
#1 Best Overall
- Fit For MN4010 KV370 Drone
- Stable Power Output Provides smooth and reliable flight performance
- Lightweight Design Helps improve flight efficiency and control
- Easy To Install Supports quick replacement and setup
- Wide Compatibility Suitable for FPV drones and quadcopters Hexacopter or Octocopter
Step 2: Find the demanding conditions
For a multirotor, the first calculation is the total thrust needed at each condition. Divide that total by the number of rotors active in that condition to get the average thrust per motor, then add margin for control and maneuvering. Hover balance alone does not prove that the aircraft can climb or respond to control inputs, so each condition needs its own check.
Conditions to evaluate
- Hover at the highest takeoff mass and the highest altitude and temperature the mission allows.
- Climb at the required rate, which often needs more thrust than hover.
- Transition between hover and forward flight, where thrust and attitude demands change together.
- Cruise at the planned speed and altitude.
- Reserve segments, including any return or loiter the mission requires.
- Degraded or control cases, where the remaining rotors must still meet the control requirement.
Which control axis drives the motor
A 2021 NASA-cited motor-sizing study found that, for the reference vehicles it examined, heave was the most demanding axis when actuator use was translated into current, torque and power margin. Yaw came next, followed by roll and then pitch. That ranking belongs to those vehicles. Your aircraft’s rotor layout and control law can change it, so calculate the demand on each axis for your own design rather than assuming the same order.
Rank #2
- Fit For MN4010 KV370 Drone
- Stable Power Output Provides smooth and reliable flight performance
- Lightweight Design Helps improve flight efficiency and control
- Easy To Install Supports quick replacement and setup
- Wide Compatibility Suitable for FPV drones and quadcopters Hexacopter or Octocopter
Step 3: Choose a variant and a propeller candidate
The T-MOTOR MN4010 product page lists three KV variants with different continuous limits. These limits are part of the operating point, so the variant must be fixed before any test row is read.
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| MN4010 variant | Continuous current | Continuous power | Limit label on the page |
|---|---|---|---|
| KV370 | 20 A | 450 W | 180S |
| KV475 | 30 A | 540 W | 180S |
| KV580 | 31 A | 575 W | 180S |
The page recommends a T-MOTOR 15×5 propeller for this series, and its test tables also include other propeller sizes. Choose the propeller that matches your thrust target and then confirm that the same propeller appears in the test row you use.
Rank #3
- Compatibility: Links with multiple power sources and fits standard transmission setups found on diverse multicopter models.
- Installation: Uses a common screw-spacing layout, allowing quick mounting to frame brackets with basic tools.
- Durability: Encased in a sturdy shell with sealed bearing units that ward off sand, dampness, and ordinary flight bumps.
- Performance: Generates uniform force and speed transitions, keeping craft steady as loads vary.
- Suitable For: Serves platforms, freight movers, surveying gear, and leisure aircraft requiring reliable spin action.
Physical data from the same page: dimensions Φ44.7 × 30.5 mm; stator diameter 40 mm and height 10 mm; 4 mm shaft; mass 137 g with cables and 112 g without; listed battery compatibility 4–8S LiPo. The page also gives a maximum thrust of 2.2 kg with the recommended propeller. That figure is the manufacturer’s claim for its test setup, not an aircraft-level sizing result.
Step 4: Read a complete test row
The page’s example row for the KV370 shows what a usable test point looks like:
Rank #4
- Compatibility: Links with multiple power sources and fits standard transmission setups found on diverse multicopter models.
- Installation: Uses a common screw-spacing layout, allowing quick mounting to frame brackets with basic tools.
- Durability: Encased in a sturdy shell with sealed bearing units that ward off sand, dampness, and ordinary flight bumps.
- Performance: Generates uniform force and speed transitions, keeping craft steady as loads vary.
- Suitable For: Serves platforms, freight movers, surveying gear, and leisure aircraft requiring reliable spin action.
| Field | Value in the row |
|---|---|
| Motor | MN4010 KV370 |
| Battery voltage | 14.8 V |
| Propeller | T-MOTOR 15×5 CF |
| Throttle | 75% |
| Current | 5.1 A |
| Input power | 75.48 W |
| Thrust | 820 g |
| RPM | 3,800 |
| Efficiency | 10.86 g/W |
Check the row before you use it. Input power equals voltage times current: 14.8 V × 5.1 A = 75.48 W. Efficiency is thrust divided by input power: 820 g ÷ 75.48 W = 10.86 g/W. This is grams of thrust per watt, a practical measure for comparing propellers. It is not a dimensionless propulsion efficiency, so do not compare it with efficiency figures from other sources.
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Three limits apply to this row:
- Voltage. 14.8 V is the nominal voltage of a 4S pack. A fully charged 4S pack is about 16.8 V and sags under load, so the row describes one pack state only. A 6S or 8S setup at a different voltage needs its own test row; do not scale current or RPM from this one.
- Temperature. The page gives a temperature test condition of motor surface temperature at 100% throttle after 10 minutes. Not every row carries a temperature value, and this condition does not represent cooling in flight.
- Throttle. A 75% throttle point is a bench condition. Convert it to a thrust requirement from your own mission numbers, not from the throttle percentage.
Step 5: Check limits and margins
A candidate that meets thrust can still fail. Check each of the following against the values for the variant you chose:
Best Value
- Compatibility: Links with multiple power sources and fits standard transmission setups found on diverse multicopter models.
- Installation: Uses a common screw-spacing layout, allowing quick mounting to frame brackets with basic tools.
- Durability: Encased in a sturdy shell with sealed bearing units that ward off sand, dampness, and ordinary flight bumps.
- Performance: Generates uniform force and speed transitions, keeping craft steady as loads vary.
- Suitable For: Serves platforms, freight movers, surveying gear, and leisure aircraft requiring reliable spin action.
- Continuous current and power. Compare the current and power at each mission condition with the variant’s limits. In the KV370 example, 5.1 A is about 26% of the 20 A continuous current rating. That condition is only one point, so check every segment.
- The 180S label. The page labels the continuous figures as 180S, which marks them as time-limited ratings rather than unlimited operation. Read the duration from current manufacturer documentation before relying on these figures for sustained hover or climb.
- Battery under load. Confirm capacity and discharge rating for the chosen voltage, including the voltage drop at peak current.
- ESC rating. The controller must handle the peak and continuous current with headroom.
- Wires and connectors. Check gauge and length for the current at the highest-demand condition.
- Cooling. Confirm that the installed motor stays within temperature limits through the longest high-load segment.
- Propeller clearance. Confirm clearance to the frame and to other rotors, including at maximum deflection.
- Reserve. Confirm that the remaining energy and thrust margin meet the reserve requirement.
Step 6: Validate the installed combination
Bench values describe the motor on a test stand. They do not validate the installed aircraft. Validate the combination in this order:
- Bench-test the selected motor, propeller, ESC and battery with instrumentation that records voltage, current, RPM and motor temperature at each condition in your mission.
- Compare the measured values with the test row you used. Note any difference in voltage, propeller or throttle before accepting it.
- Run staged aircraft tests that start with low-risk conditions and increase demand gradually, watching current, temperature and voltage at each step.
- Confirm the aircraft-level requirement, including climb, transition and control response, only after the staged tests pass.
Step 7: Iterate when a candidate fails
If a candidate meets peak thrust but draws too much current, runs hot or shortens endurance, the fix is usually to change one lever and retest. NASA’s NDARC approach uses off-design mission and point-condition analysis for this kind of iteration.
| Symptom | Likely lever | What to check next |
|---|---|---|
| Thrust target met, current above continuous limit | Propeller, motor variant, or voltage | Current and power at each segment against the variant’s limits |
| Motor runs hot at a required condition | Propeller load, duty cycle, or variant | Temperature over the longest high-load segment |
| Endurance falls short | Propeller efficiency (g/W), voltage, or mission assumptions | Energy per segment and reserve |
| Control response thin in yaw, roll or pitch | Rotor sizing or per-motor margin | Thrust demand per axis for degraded cases |
| Voltage drops below the test point under load | Battery capacity or discharge rating | Voltage at peak current on the bench |
Each change needs a new test row or a new bench measurement. A value taken from a different variant, voltage or propeller does not carry over.
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Quick Recap
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