What is a Radial Flux Electric Motor? Flux Path, Topologies, Stator Core Parameters, and the Procurement Audit

A radial flux electric motor powers the overwhelming majority of drones flying today, and most purchase orders for one describe only its envelope. The datasheet names the stator diameter, the stack height, the KV rating, and the weight. It almost never names the four parameters that decide whether the motor holds its thrust curve through a full flight or sags as the winding heats: core loss at the operating electrical frequency, B50 flux density, stacking factor, and concentricity. Two motors labelled 2207 1750KV can therefore differ by 15–25°C in winding temperature, because one used a ≤9.5 W/kg finished-stack core with ≥97% stacking factor and the other used a 10–14 W/kg generic grade on a loose stack. The label is identical. The motor is not.

This guide answers What is a radial flux electric motor? at the level a propulsion engineer or procurement lead needs: the flux-path definition and the three structural properties that make the topology dominant, the rotor and slot classifications that define drone motors, the published stator core parameters that determine whether the motor meets its thrust table, the mission profiles where radial flux is the correct choice, and a five-step selection and audit workflow. Every published value in this article is expressed as a number plus a test standard plus a measurement location, so it can be verified on the finished part rather than read from a mill certificate.

What Is a Radial Flux Electric Motor? The Flux-Path Definition and the Three Structural Properties

A radial flux electric motor is a machine in which the magnetic flux between the stator and the rotor crosses the air gap perpendicular to the rotation axis — radially outward or inward — through a cylindrical gap between two coaxial cylinders. The stator is a slotted cylinder carrying the windings; the rotor is a coaxial cylinder carrying the permanent magnets, sitting either outside the stator (outrunner) or inside it (inrunner). Published definitions describe radial flux as the construction in which magnetic field lines cross the air gap radially, producing the conventional cylindrical layout used in the majority of drone propulsion motors.

That geometry has three structural consequences that explain the topology’s dominance.

First, the magnetic attraction self-cancels. Because the air gap is a full cylinder, the magnetic pull on the rotor is balanced around the entire circumference. The rotor does not need a second air gap, a second rotor, or a stiff balancing structure to stay centred. Published engineering analysis of axial flux explicitly contrasts this: axial flux needs two rotors or two stators to cancel the attraction, which introduces a second air gap and roughly doubles the magnetic reluctance of the circuit.

Second, torque scales with a single parameter. The torque a radial flux motor produces is proportional to the cylindrical air-gap area, which grows with diameter × stack length. To double torque, you double the stack length — essentially a single-parameter change in design and tooling. Published scalability analysis uses exactly this comparison: doubling torque in radial flux is straightforward, while in axial flux it requires increasing diameter, which demands a more complete tooling change.

Third, the supply chain is mature and multi-sourced. Radial flux stator cores are produced by high-speed progressive stamping of non-oriented electrical steel — a process with a deep, competitive supplier base. Published comparisons note that radial flux motors remain dominant because of scalability and lower production costs, while axial flux serves compact, specialized applications at a cost premium.

Radial Flux Motor Classification: Outrunner vs Inrunner, Slotted vs Slotless, SPM vs IPM, 12N14P and Slot-Pole Families

Rotor topology: outrunner versus inrunner

Source: Published radial flux topology comparison (outrunner external rotor, inrunner internal rotor; torque-radius and inertia differences).

The outrunner dominates drone propulsion because a multirotor propeller needs relatively high torque at moderate RPM, and the outrunner’s larger torque radius delivers it without a gearbox. The inrunner’s lower inertia and higher speed ceiling suit ducted-fan and gimbal applications where rapid response matters more than raw torque. The distinction is structural: it changes the bearing arrangement, the air-gap location, and the thermal path, and it cannot be inferred from the KV rating.

Slot geometry: slotted versus slotless

Source: Published BLDC slot geometry classification (slotted vs slotless; slotless produces high-speed motors with low inductance, more expensive due to more coil turns).

Magnet placement: surface-mount versus interior

Slot-pole families: 12N14P and the alternatives

The slot-pole combination defines the winding factor and the cogging profile, and it is fixed at the stator core design stage. 12N14P is the drone workhorse: 12 slots and 14 poles give slots per pole per phase of q = 12 ÷ (14 × 3) ≈ 0.286, a fractional-slot concentrated winding with a fundamental winding factor of approximately 0.933 and very low cogging torque. The slight asymmetry between slot and pole count means the magnets never align with all teeth simultaneously, which is why cogging is suppressed.

Source: Published BLDC winding calculator (12N14P winding factor 0.933; 9N12P lower pole count reduces iron losses at the expense of slightly higher torque ripple); Reenives slot-pole configuration record.

Published Stator Core Parameters: Core Loss, B50, Stacking Factor, Concentricity, Tolerance, Burr, Coating, Slot-Pole

A radial flux motor’s performance is bounded by its stator core. The topology determines the structure; the core determines whether the structure delivers its rated thrust or quietly derates. The published parameter set below is expressed as value, standard, and measurement location, so it can be audited on the finished part.

Sources: Reenives radial flux drone stator core specification (core loss, lamination thickness, B50, stacking factor, concentricity, tolerance, burr, coating, dielectric strength, temperature range, slot-pole); IEC 60404-2 Epstein-frame method; ASTM D149 dielectric strength standard.

Core loss: the thermal ceiling

Core loss has two components: hysteresis loss, proportional to frequency and the material’s coercivity, and eddy-current loss, proportional to the square of both lamination thickness and frequency. At drone electrical frequencies — hundreds of hertz to over 1 kHz — the eddy-current term dominates, and it scales with the square of thickness. Published comparison data places a 0.35 mm grade at roughly 28–35 W/kg at 1.0 T / 400 Hz, a generic 0.20 mm grade at roughly 10–14 W/kg, and the Reenives 0.20 mm grade at ≤9.5 W/kg measured per IEC 60404-2. The 0.35 → 0.20 mm switch reduces eddy-current loss by approximately 67% at the same flux density, which becomes lower winding temperature and longer continuous torque headroom.

B50 and stacking factor: the flux-density pair

B50 is the flux density measured at a magnetizing field of 5,000 A/m, and it defines the torque-per-amp ceiling at the material level. A core at the low end of the 1.65–1.72 T band saturates earlier, so the motor draws more current for the same torque and runs hotter. Stacking factor is the ratio of actual magnetic steel volume to the total stack envelope, measured by the weight/dimension method. Moving from a 96% to a 98% stacking factor raises effective flux density by roughly 6% without any change to the mill certificate — which is why a loose stack wastes the grade the buyer paid for.

Concentricity, tolerance, and burr: the manufacturing controls

Concentricity ≤0.02 mm is the deviation of the stator bore centre from the outer diameter centre. It defines half the air gap: a 0.02 mm error on each side is a meaningful fraction of a 0.10–0.12 mm FPV air gap. Critical tolerance ±0.05 mm governs how consistently the stator seats in the winding fixture and how closely the bore matches the nominal design. Burr height <0.03 mm is the raised edge left by stamping; a burr can pierce the interlamination coating of the adjacent sheet during stacking and create a local short that becomes a hot spot. All three must be measured on the finished core, not inferred from the mill certificate.

Coating: the survival barrier

C5 epoxy powder coating at >1400 V per ASTM D149, across −40°C to 180°C with a 200°C short-term peak, is the interlamination electrical barrier. It is not a finish. During winding, tension and tool contact can abrade or pierce it; during operation, thermal cycling and vibration stress it further. A uniform, pinhole-free layer survives both; a thin or voided layer can pass the initial electrical test and break down after hours of flight. C6 is available where harsher chemical or thermal duty applies.

Application Profiles: Which Radial Flux Configuration Binds Which Drone Mission

The pattern is that the binding parameter tracks the mission’s dominant failure mechanism. FPV racing binds on core loss because high electrical frequency converts iron loss into heat that sags the thrust curve. Cinematic and inspection platforms bind on concentricity and cogging because vibration reaches the payload before it reaches the pilot. Agricultural platforms bind on coating and temperature range because the duty cycle is long, wet, and thermal. Heavy-lift binds on stacking factor and B50 because continuous torque depends on the flux density the finished stack actually delivers. Inrunner applications bind on inertia and speed ceiling because the mission is response, not raw torque.

A 5-Step Radial Flux Motor Selection and Audit Workflow

1. Fix the application class and the propeller before the motor. State the all-up weight, propeller diameter, voltage platform, and continuous duty cycle. The propeller determines the torque and RPM the motor must deliver; the motor exists to serve it. A 5-inch FPV on 6S and a 30-inch heavy-lift on 14S sit in different application classes, and the KV band follows from the class: high KV (2000–4000+) for small propellers, mid KV (1000–2000) for 5-inch freestyle, low KV (90–1000) for large propellers and heavy-lift.
2. Choose the rotor topology and slot geometry from the structural requirement. For multirotor propulsion, the outrunner with a slotted stator is the default because the larger torque radius delivers the required torque without a gearbox. For EDF, ducted fan, or gimbal applications, the inrunner’s lower inertia and higher speed ceiling are the reason to select it. Slotless geometry is reserved for high-speed, low-cogging applications where the reduced torque density is acceptable.
3. Confirm the slot-pole combination before tooling is ordered. Specify 12N14P for the drone workhorse — q ≈ 0.286, winding factor ≈ 0.933, very low cogging — or 9N12P for lightweight high-speed builds, 18N24P or 24N28P for larger high-torque platforms. Because the slot-pole pair is fixed at the core design stage, an error here requires a new die set rather than a process adjustment.
4. Specify the stator core with value, standard, and location for every parameter. Write 0.20 mm non-oriented silicon steel, core loss ≤9.5 W/kg at 1.0 T / 400 Hz per IEC 60404-2 on the finished stack, B50 1.65–1.72 T, stacking factor ≥97%, concentricity ≤0.02 mm by vision, critical tolerance ±0.05 mm, burr height <0.03 mm by optical comparator, and C5 epoxy coating at >1400 V per ASTM D149 across −40°C to 180°C. A quote that omits the standard and the location leaves the interpretation to the supplier.
5. Run a trial sample and audit the evidence before volume commitment. Send the motor design intent to the core supplier and request a finished-stack core-loss report, a stacking-factor measurement, a concentricity record, a burr measurement, and a rejected unit from their inspection process. Confirm that the electrical frequency at the intended operating RPM (RPM × pole pairs ÷ 60) falls where the specified grade delivers its published loss — for a 14-pole motor at 15,000 RPM that is 1,750 Hz, well into the range where the 0.20 mm grade is the baseline rather than an upgrade.

FAQ: Definition, Self-Cancelling Pull, 12N14P, Core Loss, B50, Stacking Factor, Concentricity, and Coating

Summary: Radial Flux Is the Default for a Structural Reason

A radial flux electric motor routes magnetic flux perpendicular to the shaft across a cylindrical air gap. That geometry delivers three properties that explain why it powers the vast majority of drones: the magnetic attraction self-cancels around the full circumference, so the rotor stays centred without extra structure; torque scales by lengthening the stator stack, a single-parameter tooling change; and the progressive-stamped lamination supply chain is mature and multi-sourced. Axial flux can beat radial flux on torque density and axial length, but it pays with dual air gaps, near-ton assembly attraction, and tighter gap uniformity — which is why radial flux remains the lower-risk, lower-cost topology for volume drone production.

The published stator core parameter set for a radial flux drone motor is concrete: 0.20 mm non-oriented silicon steel, core loss ≤9.5 W/kg at 1.0 T / 400 Hz per IEC 60404-2 on the finished stack, B50 1.65–1.72 T, stacking factor ≥97%, concentricity ≤0.02 mm, critical tolerance ±0.05 mm, burr height <0.03 mm, and C5 epoxy coating at >1400 V per ASTM D149 across −40°C to 180°C, in 12N14P (winding factor ≈0.933, very low cogging) with 9N12P, 18N24P, and 24N28P alternatives. Each value is expressed as number plus standard plus location, so it can be audited on the finished part.

The procurement takeaway is that the topology label is the beginning of the specification, not the end. A supplier who quotes “radial flux, 2207, 1750KV” has named the geometry and the envelope; a supplier who can also restate the core-loss figure with its standard, the B50 and stacking factor with their methods, the concentricity and burr limits with their instruments, and the coating dielectric strength with its test standard is describing the part that decides whether the motor holds its thrust curve. That is the difference between a topology quote and a motor specification.