Diana 2 nose electric folding-prop installation UAV with conventional horizontal tail · baseline-to-optimized evidence with an embedded model of the actual exported mesh.
Headline values come from the optimized aircraft’s own artifacts. Every gate below carries one-line evidence and a source path; the green state is not inferred from a stage’s top-level flag alone.
Source-locked reconstruction of the as-flown 1:3 Baudismodel Diana 2 from diana2-design-input-v1 only. Public geometry and measured mass properties are frozen in reproduction mode. The proprietary wing section is represented by NACA 0012, detailed body lofting and electric-installation dimensions are unscored geometry assumptions, and the visible L1 spanwise overlay carries aircraft-specific structural calibration without a first-principles claim. The declared quasi-isotropic CFRP equivalent is used only for internal OAS static-stress feasibility and is not an as-built laminate or certification claim. The broad conventional-tail static-margin band is a source-reproduction representability screen only; rigid-body handling quality is not claimed.
| Requirement | Target | Predicted | Verdict |
|---|---|---|---|
| Engine | Diana 2 nose electric folding-prop installation | Diana 2 nose electric folding-prop installation | MET |
| Payload | 0.0 kg | 0.0 kg | MET |
| Endurance | not claimed | n/a | N/A |
| Dash | maximize; M ≤ 0.11 | 134 km/h · M 0.11 | MET |
| Configuration | sketch envelope | 5.00 m span · 0.2° sweep | MET |
Source and delivered specifications deserialize; every source-locked field is unchanged except declared trim and same-run component-stability constants.
source=yes; optimized=yes; engine requirement=yes; payload requirement=yes; reproduction frozen=yes
design.yaml · Upstream response: Correct design.yaml values or schema violations; never patch generated JSON.The exported mesh—not only the intended parameters—matches the requested aircraft.
read-back=yes; bbox=yes; mesh checks=16
optimized/geometry.json · Upstream response: Fix OpenVSP construction, section placement, or source geometry, then rerun geometry.Engine, payload, and fuel occupy non-overlapping usable volume.
fuel-volume margin 0.026 m³; engine/payload clear
optimized/geometry.json · Upstream response: Move/resize bays, increase body or tank volume, or reduce required fuel.Measured static margin is inside the mission band at full and reserve fuel.
independently measured SM full 0.361; reserve 0.361 MAC
optimized/aero.json · Upstream response: Adjust wing, payload, fuel, or engine longitudinal stations; recalibrate NP only with OAS evidence.The aircraft closes lift and pitching moment at its selected wing twist or tail incidence.
tail incidence -2.469° vs spec -2.471°; CM residual 0.0000
optimized/aero.json · Upstream response: Adjust twist/tail incidence, airfoil moment, CG/wing station, or OAS-backed calibration.Wing loading remains compatible with the documented CLmax assumption.
Vstall 11.773 m/s ≤ 20.0 m/s at CLmax 1.20
optimized/aero.json · Upstream response: Increase wing area, reduce MTOW, or change CLmax only with aerodynamic evidence.Source-locked geometry clears either the minimum conceptual fin-volume screen or same-run restoring/damping derivative checks; no upper-band sizing claim or fin-sizing optimum is made.
source Vv 0.0203; same-run Cnβ 0.0457, Cnr -0.0309 (source-locked reproduction)
optimized/validation.json · Upstream response: Correct the source geometry or remove the reproduction claim; do not resize a source-locked fin to make the screen pass.The OAS wingbox survives the positive limit load with the encoded safety factor.
+4g failure index -0.085; CL 0.951/0.950; lift closed=yes; mass closed=yes; tip deflection 0.338 m
optimized/structures.json · Upstream response: Increase skin/spar gauge, section depth, or material capability; reduce load only by changing requirements.The closed fuel budget meets endurance and installed thrust covers modeled drag.
endurance not claimed for electric reproduction; cruise/dash thrust ≥ buildup drag
optimized/aero.json + baseline/mdo.json · Upstream response: Trade fuel, mass, drag, cruise condition, wing geometry, or propulsion assumptions upstream.Source coordinates remain frozen while a separate OAS solve checks trim and structures; stability retains its declared independent-derivative or component-model evidence label.
feasible=yes; driver=yes; post-delivery verify=yes; calibration=yes; frozen=yes; 1 starts
baseline/mdo.json · Upstream response: Fix source serialization, trim/structures verification, or stability provenance; do not optimize frozen reproduction coordinates.Delivered proportions stay inside the hard identity bound and every soft-prior departure is explained.
span/L 2.15; root/L 0.10; sweep 0.2°; 0 scored shape departures; 0 total audit records
optimized/design.yaml + baseline/mdo.json · Upstream response: Fix unjustified departures or the upstream physics; never widen the hard identity bound silently.Required analytical identities and declared-scope solver checks pass, method spread is disclosed, and headline values reproduce from same-phase artifacts.
core 14/14; VSPAERO/OAS CLα ratio 1.003; NP method spread 0.038 MAC (diagnostic); report Mach 0.110 vs recomputed 0.110; MTOW report/aero/MDO 10.700/10.700/10.700 kg; L/D report/aero/MDO 10.071/10.071/10.071
optimized/validation.json + optimized/report.json · Upstream response: Use the failed validation check name to fix its upstream model or calibration.The first figure and interactive hero are rendered from the exported STL itself. The remaining figures expose the numerical story: what changed, where drag and mass live, and how close the design sits to its constraints.
The baseline is the aircraft as drawn; the optimizer answers what it presented. Both columns below are read from their own phase artifacts — the two phases are different aircraft and are never mixed inside one number. The delivered configuration is checked by a separate OAS solve; stability evidence is labeled by method.
| Quantity | Baseline | Optimized | Change |
|---|---|---|---|
| Wing span | 5.000 m | 5.000 m | unchanged |
| Wing area | 1.030 m² | 1.030 m² | unchanged |
| Aspect ratio | 24.27 | 24.27 | unchanged |
| Taper | 0.845 | 0.845 | unchanged |
| LE sweep | 0.2 deg | 0.2 deg | unchanged |
| Airfoil | NACA 0012 | NACA 0012 | unchanged |
| Thickness t/c | 0.120 | 0.120 | unchanged |
| Tip twist | -1.00 deg | -1.00 deg | unchanged |
| MTOW | 10.70 kg | 10.70 kg | unchanged |
| Fuel | 0.00 kg | 0.00 kg | unchanged |
| Dash speed | 134 km/h | 134 km/h | unchanged |
| Cruise L/D | 10.07 | 10.07 | unchanged |
| Stall speed | 11.8 m/s | 11.8 m/s | unchanged |
| Static margin (full) | 0.361 MAC | 0.361 MAC | unchanged |
| Trim tail incidence | -2.47 deg | -2.47 deg | unchanged |
Mission, topology, and proportions become a validated, version-controlled concept specification.
Fuel and MTOW close without an endurance claim; artifact geometry and OAS models establish the reference.
Source coordinates remain frozen while same-run OAS closes model calibration and verifies trim, stability, and structures.
Separate OAS and mesh-truth checks produce the 134 km/h delivered configuration.
| Start | Dash | Endurance | MTOW | Feasible |
|---|---|---|---|---|
| deterministic_reference_closure | 134 km/h | n/a | 10.7 kg | yes |
| Attempt | Internal band | Evaluated full / reserve | Verdict |
|---|---|---|---|
| same-run OAS NP | model error ≤ 0.05 MAC | 0.108 / 0.006 MAC | PASS |
Analytical identities, OAS comparisons, VSPAERO, artifact-level geometry checks, and stretch solvers test different failure modes. TACS and SU2 are shown as calibration data—not promoted into certification evidence.
| Check | Class | Observed | Reference | Verdict |
|---|---|---|---|---|
| k450 tsfc kg per kgf hr | core gate | 1.467 | 1.467 | PASS |
| breguet round trip | core gate | 7,200.0 | 7,200.0 | PASS |
| isa T sl | core gate | 288.1 | 288.1 | PASS |
| isa rho sl | core gate | 1.225 | 1.225 | PASS |
| oas induced drag vs elliptic | core gate | 0.003 | 0.003 | PASS |
| cantilever deflection identity | core gate | 0.014 | 0.014 | PASS |
| thin airfoil cm ac | core gate | {"0012":0.0,"2412":-0.05311944998613994} | {"0012":0.0,"2412":-0.047} | PASS |
| fin volume coefficient | core gate | 0.020 | >= 0.02 or passing same-run directional derivatives (source-locked reproduction) | PASS |
| fin te within body | core gate | -0.030 | <= 0.0466 m | PASS |
| neutral point model vs oas | core gate | 0.814 | 0.813 | PASS |
| wing mass buildup vs oas | core gate | 2.380 | 0 < wing structural mass < 10.7 kg reference OE mass | PASS |
| modal consistency | core gate | [{"id":"first_symmetric_wing_bending","family":"bending","order":1,"predicted_frequency_hz":7.415… | all visible L1 frequency residuals <= 10% and exactly 21 declared strain channels | PASS |
| vspaero vs oas CL | core gate | 1.003 | n/a | PASS |
| elevon cm delta vspaero vs oas | core gate | n/a | pitch trim control is not elevon | PASS |
| tacs artifact schema | stretch calibration | tacs | stretch; schema presence only | PASS |
| su2 convergence reported separately | stretch calibration | [false,false] | stretch; 'ok' means ran+parsed, 'converged' is the residual verdict | PASS |
Component extents, fin verticality, whole-model envelope, and root attachment are measured on exported STL files.
VSPAERO versus OAS lift-curve slope across α=[3.0, 7.0]° on the same lifting surfaces. Absolute CL has different camber fidelity; CD is intentionally not compared.
Shell mass 1.030 kg; SU2 cruise converged=no, rmsρ=-2.436.
This section preserves the details needed to challenge or reproduce the design. Values are generated from the delivered optimized YAML and same-directory stage outputs.
| Parameter | Value |
|---|---|
| Fuselage | 2.33 × 0.18 × 0.22 m |
| Wing | 5.00 m span · 1.03 m² · AR 24.27 |
| Planform | root 0.22 m · taper 0.845 · LE sweep 0.2° |
| Airfoil / thickness | NACA 0012 · t/c 0.120 |
| Twist | root +0.00° · tip -1.00° |
| Single fin | 0.34 m span · 0.0° cant |
| Propulsion | Diana 2 nose electric folding-prop installation · 70.0 N SL |
| Fuel | 0.00 kg delivered spec |
| Structure | wingbox · skin 1.00 mm · spar 1.50 mm |
| Material | L1-calibrated quasi-isotropic CFRP equivalent · yield 250 MPa |
| Item | Mass | x station |
|---|---|---|
| operating_empty | 10.70 kg | 0.740 m |
| Python | 3.12.3 |
| OpenVSP | OpenVSP 3.51.3 |
| OpenMDAO | 3.45.0 |
| OpenAeroStruct | 2.12.0 |
| Pydantic | 2.13.4 |
| NumPy | 2.5.2 |
| Matplotlib | 3.11.1 |
name: diana2
notes: Source-locked reconstruction of the as-flown 1:3 Baudismodel Diana 2 from diana2-design-input-v1
only. Public geometry and measured mass properties are frozen in reproduction mode.
The proprietary wing section is represented by NACA 0012, detailed body lofting
and electric-installation dimensions are unscored geometry assumptions, and the
visible L1 spanwise overlay carries aircraft-specific structural calibration without
a first-principles claim. The declared quasi-isotropic CFRP equivalent is used only
for internal OAS static-stress feasibility and is not an as-built laminate or certification
claim. The broad conventional-tail static-margin band is a source-reproduction representability
screen only; rigid-body handling quality is not claimed.
sketch:
treatment: reproduction
hard_scale: 1.0
fidelity_weight: 1.0
span_over_length: 2.145922746781116
span_over_length_tol: 0.01
root_over_length: 0.09585121602288985
root_over_length_tol: 0.005
le_sweep_deg: 0.198595
le_sweep_tol_deg: 0.5
taper: 0.8447761194029852
taper_tol: 0.01
x_le_root_over_length: 0.2811158798283262
x_le_root_over_length_tol: 0.015021459227467813
payload_bay_x_lo_m: 0.45
payload_bay_x_hi_m: 0.55
fuel_tank_x_lo_m: 0.7
fuel_tank_x_hi_m: 0.78
twist_tip_lo_deg: -2.0
twist_tip_hi_deg: 0.0
fin_span_m: 0.34
fin_span_tol_m: 0.02
fin_root_chord_m: 0.32
fin_root_chord_tol_m: 0.02
fin_le_sweep_deg: 32.0
fin_le_sweep_tol_deg: 3.0
fin_cant_deg: 0.0
fin_cant_tol_deg: 1.0
fin_x_le_m: 1.96
fin_x_le_tol_m: 0.04
engine:
name: Diana 2 nose electric folding-prop installation
energy_source: electric
diameter_m: 0.1
length_m: 0.2
dry_mass_kg: 1.0
installation: internal
installation_count: 1
x_m: null
lateral_offset_m: 0.0
z_m: 0.0
max_thrust_sl_n: 70.0
fuel_flow_max_kg_s: 0.0
thrust_lapse_k_mach: 0.35
thrust_lapse_floor: 0.08
tsfc_part_a: 0.8
tsfc_part_b: 0.2
tsfc_mach_k: 0.15
min_throttle: 0.18
fuel_density_kg_m3: 800.0
nacelle_frontal_cd: 0.08
deck: null
wing:
span_m: 5.0
root_chord_m: 0.22333333333333333
taper: 0.8447761194029852
le_sweep_deg: 0.198595
dihedral_deg: 0.0
twist_root_deg: 0.0
twist_tip_deg: -1.0
t_over_c: 0.12
airfoil: '0012'
x_le_root_m: 0.655
z_root_m: 0.0
sections: null
tip_chord_m: 0.1886666666666667
area_m2: 1.03
aspect_ratio: 24.271844660194173
mac_m: 0.20648615605897158
y_mac_m: 1.214940668824164
x_le_mac_m: 0.6592111672175353
x_ac_m: 0.7108327062322781
fuselage:
length_m: 2.33
max_width_m: 0.18
max_height_m: 0.22
nose_fine_ratio: 0.22
tail_fine_ratio: 0.28
payload_bay_length_m: 0.25
payload_bay_width_m: 0.12
payload_bay_height_m: 0.12
payload_bay_x_m: 0.5
fuel_tank_x_m: 0.74
stations: null
fairings: null
vtail:
count: 1
root_attachment: derived
span_m: 0.34
root_chord_m: 0.32
taper: 0.4
le_sweep_deg: 32.0
cant_deg: 0.0
t_over_c: 0.1
x_le_m: 1.96
y_root_m: 0.0
z_root_m: 0.11
area_m2: 0.07616
htail:
span_m: 0.82
root_chord_m: 0.205
taper: 0.45
le_sweep_deg: 18.0
t_over_c: 0.1
x_le_m: 2.03
z_m: 0.37
incidence_deg: -2.4706
area_m2: 0.1218725
mission:
endurance_s: 7200.0
endurance_required: false
payload_kg: 0.0
cruise_altitude_m: 175.0
dash_altitude_m: 175.0
cruise_mach: 0.066
cruise_cl: 0.335
dash_mach_cap: 0.11
limit_positive_g: 4.0
limit_negative_g: -2.0
safety_factor: 1.5
static_margin_min: 0.05
static_margin_max: 0.4
reserve_fuel_fraction: 0.0
cl_max: 1.2
cl_max_basis: aircraft
stall_speed_max_mps: 20.0
pitch_trim_control: auto
structures:
fem_model_type: wingbox
spar_thickness_m: 0.0015
skin_thickness_m: 0.001
tube_radius_m: 0.018
tube_thickness_m: 0.0025
wing_weight_ratio: 1.35
n_spanwise: 13
n_chordwise: 3
material:
name: L1-calibrated quasi-isotropic CFRP equivalent
E_pa: 35000000000.0
nu: 0.3
yield_pa: 250000000.0
density_kg_m3: 1600.0
G_pa: 13461538461.538462
spanwise:
- eta: 0.0
ei_bend_n_m2: 4550.0
gj_n_m2: 500.0
mass_per_span_kg_m: 1.1
polar_mass_moment_per_span_kg_m: 0.004
section_modulus_m3: 4.5e-06
- eta: 0.2
ei_bend_n_m2: 3600.0
gj_n_m2: 410.0
mass_per_span_kg_m: 0.95
polar_mass_moment_per_span_kg_m: 0.0035
section_modulus_m3: 4.0e-06
- eta: 0.4
ei_bend_n_m2: 2650.0
gj_n_m2: 320.0
mass_per_span_kg_m: 0.82
polar_mass_moment_per_span_kg_m: 0.0029
section_modulus_m3: 3.4e-06
- eta: 0.6
ei_bend_n_m2: 1780.0
gj_n_m2: 220.0
mass_per_span_kg_m: 0.68
polar_mass_moment_per_span_kg_m: 0.0023
section_modulus_m3: 2.8e-06
- eta: 0.8
ei_bend_n_m2: 985.0
gj_n_m2: 120.0
mass_per_span_kg_m: 0.52
polar_mass_moment_per_span_kg_m: 0.0017
section_modulus_m3: 2.1e-06
- eta: 1.0
ei_bend_n_m2: 303.0
gj_n_m2: 35.0
mass_per_span_kg_m: 0.35
polar_mass_moment_per_span_kg_m: 0.001
section_modulus_m3: 1.2e-06
modal_calibration:
- id: first_symmetric_wing_bending
family: bending
order: 1
frequency_hz: 7.42
damping_fraction: 0.0288
source: diana2-design-input-v1 visible ground mode 1
sensor_stations:
- id: I
eta: 0.1638
source: Diana2_sensor_locations.xlsx
- id: M
eta: 0.3452
source: Diana2_sensor_locations.xlsx
- id: O
eta: 0.6612
source: Diana2_sensor_locations.xlsx
drag:
interference_fraction: 0.08
protuberance_cd0: 0.004
mass:
fuel_mass_kg: 0.0
fuel_mass_mode: fixed
fuel_capacity_kg: null
listed_mass_min_kg: null
listed_mass_max_kg: null
listed_mass_state: null
operating_empty_mass_kg: 10.7
operating_empty_cg_x_m: 0.74
systems_kg: 0.0
landing_gear_fraction: 0.0
avionics_kg: 0.0
contingency_fraction: 0.0
flight_dynamics:
enabled: true
reference_airspeed_mps: 22.5
reference_altitude_m: 175.0
inertia:
ixx_kg_m2: 4.445
iyy_kg_m2: 1.642
izz_kg_m2: 6.897
ixy_kg_m2: 0.0
ixz_kg_m2: 0.332
iyz_kg_m2: 0.0
source: diana2-design-input-v1 published pendulum and rotational testing
control_surfaces:
- id: outer_aileron
host: wing
span_start_fraction: 0.62
span_end_fraction: 0.97
chord_fraction: 0.22
max_up_deg: 20.0
max_down_deg: 12.0
neutral_deg: null
trim_deflection_deg: 0.0
source: diana2-design-input-v1 public control inventory and image abstraction
mixing:
- id: aileron
mode: differential
axis: roll
gain: 1.0
- id: middle_aileron
host: wing
span_start_fraction: 0.34
span_end_fraction: 0.62
chord_fraction: 0.22
max_up_deg: 14.0
max_down_deg: 10.0
neutral_deg: null
trim_deflection_deg: 0.0
source: diana2-design-input-v1 public control inventory and image abstraction
mixing:
- id: aileron
mode: differential
axis: roll
gain: 0.7
- id: flap
host: wing
span_start_fraction: 0.1
span_end_fraction: 0.34
chord_fraction: 0.22
max_up_deg: 8.0
max_down_deg: 20.0
neutral_deg: null
trim_deflection_deg: 0.0
source: diana2-design-input-v1 public control inventory and image abstraction
mixing:
- id: flap
mode: collective
axis: lift
gain: 1.0
- id: elevator
host: htail
span_start_fraction: 0.08
span_end_fraction: 0.96
chord_fraction: 0.3
max_up_deg: 20.0
max_down_deg: 20.0
neutral_deg: null
trim_deflection_deg: 0.0
source: diana2-design-input-v1 public control inventory and image abstraction
mixing:
- id: elevator
mode: collective
axis: pitch
gain: 1.0
- id: rudder
host: vtail
span_start_fraction: 0.12
span_end_fraction: 0.95
chord_fraction: 0.32
max_up_deg: 25.0
max_down_deg: 25.0
neutral_deg: null
trim_deflection_deg: 0.0
source: diana2-design-input-v1 public control inventory and image abstraction
mixing:
- id: rudder
mode: single
axis: yaw
gain: 1.0
aeroelastic:
enabled: true
strip_count: 64
modes_per_family: 1
frequency_min_hz: 0.5
frequency_max_hz: 30.0
frequency_points: 1000
maximum_reduced_frequency: 0.3
elastic_axis_fraction_chord: 0.4
lift_curve_slope_per_rad: null
calibration_id: diana2-training-aeroelastic-v2
allow_diagonal_inertia_approximation: true
calibration_id: none
solver:
oas_with_viscous: true
oas_with_wave: true
optimize_maxiter: 35
optimize_tol: 1.0e-05
fd_step: 0.001
vspaero_wake_iters: 5
vspaero_convergence_factor: 0.01
su2_maxiter: 200
gmsh_lc_m: 0.08
stability_method: lifting_surface
np_shift_mac: 0.10816484428353546
wing_body_np_mac: null
wing_body_cl_alpha_per_deg: null
cm_washout_per_deg: 0.00362
tail_incidence_offset_deg: 0.0
tail_lift_effectiveness_factor: 1.0
tail_lift_effectiveness_source: null
elevon_effectiveness_factor: 1.0
elevon_effectiveness_source: null
n_ult: 6.0