Equivalent 2 x V2527-A5 CeRAS rated deck UAV with conventional horizontal tail · 13608.0 kg payload · 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.
Post-hoc, truth-conditioned CeRAS CSR-01 reconstruction from public geometry, propulsion, payload, and mission inputs. The 42,092 kg operating-empty mass and 18,402 kg fuel load are algebraically derived from the same published mission rows used by the verification case; they are frozen inputs, not independent predictions. The equivalent trapezoid preserves published wing span, area, and MAC. The sparse two-engine deck contains only the two CeRAS rated conditions plus declared part-throttle engineering interpolants. The NACA 2412 sections, equivalent-tail details, 14 m operating-empty CG, payload/fuel-box locations, CLmax/stall screen, structural gauges, and nacelle frontal-CD allowance are declared conceptual assumptions. The small-aircraft OAS wingbox method explicitly refuses structural closure at this transport scale.
| Requirement | Target | Predicted | Verdict |
|---|---|---|---|
| Engine | Equivalent 2 x V2527-A5 CeRAS rated deck | Equivalent 2 x V2527-A5 CeRAS rated deck | MET |
| Payload | 13608.0 kg | 13608.0 kg | MET |
| Endurance | 6.33 h | 7.78 h | MET |
| Dash | maximize; M ≤ 0.78 | 833 km/h · M 0.78 | MET |
| Configuration | sketch envelope | 34.07 m span · 25.0° 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=28
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 60.252 m³; engine/payload clear
optimized/geometry.json · Upstream response: Move/resize bays, increase body or tank volume, or reduce required fuel.Same-run VSPAERO wing/body/nacelle evidence feeds the declared tail model; the resulting static margin is a component-model screen, not an independent measurement.
component-model SM full 0.283; reserve 0.276 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 -2.112° vs spec -2.112°; 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 73.380 m/s ≤ 75.0 m/s at CLmax 1.80
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.
cant-corrected fin volume Vv 0.1175 ≥ 0.02 (source-locked reproduction)
optimized/aero.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.
unsupported domain: the current OAS wingbox method is qualified only for span <= 10 m and MTOW <= 1000 kg; use a transport load-path model before claiming structural closure
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.
7.78 h; 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 0.91; root/L 0.16; sweep 25.0°; 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 12/12; VSPAERO/OAS CLα ratio 0.914; NP method spread 0.095 MAC (diagnostic); report Mach 0.780 vs recomputed 0.780; MTOW report/aero/MDO 74102.000/74102.000/74102.000 kg; L/D report/aero/MDO 17.103/17.103/17.103
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 | 34.070 m | 34.070 m | unchanged |
| Wing area | 122.410 m² | 122.410 m² | unchanged |
| Aspect ratio | 9.48 | 9.48 | unchanged |
| Taper | 0.176 | 0.176 | unchanged |
| LE sweep | 25.0 deg | 25.0 deg | unchanged |
| Airfoil | NACA 2412 | NACA 2412 | unchanged |
| Thickness t/c | 0.120 | 0.120 | unchanged |
| Tip twist | -2.00 deg | -2.00 deg | unchanged |
| MTOW | 74102.00 kg | 74102.00 kg | unchanged |
| Fuel | 18402.00 kg | 18402.00 kg | unchanged |
| Dash speed | 833 km/h | 833 km/h | unchanged |
| Endurance | 7.78 h | 7.78 h | unchanged |
| Cruise L/D | 17.10 | 17.10 | unchanged |
| Stall speed | 73.4 m/s | 73.4 m/s | unchanged |
| Static margin (full) | 0.283 MAC | 0.283 MAC | unchanged |
| Trim tail incidence | -2.11 deg | -2.11 deg | -0.01 deg |
Mission, topology, and proportions become a validated, version-controlled concept specification.
Fuel and MTOW close at 7.78 h; 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 833 km/h delivered configuration.
| Start | Dash | Endurance | MTOW | Feasible |
|---|---|---|---|---|
| deterministic_reference_closure | 833 km/h | 7.78 h | 74102.0 kg | yes |
| Attempt | Internal band | Evaluated full / reserve | Verdict |
|---|---|---|---|
| same-run component analysis | declared solver evidence | {"ok":true,"method":"VSPAERO hybrid: thick fuselage/nacelles + thin main wing","points":[{"ok":tr… | 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 | 0.117 | >= 0.02 or passing same-run directional derivatives (source-locked reproduction) | PASS |
| fin te within body | core gate | 0.546 | <= 0.7498 m | PASS |
| hybrid component provenance | core gate | {"wing_body_np_mac":0.23350876358829661,"wing_body_cl_alpha_per_deg":0.10708004205475} | serialized constants trace to converged same-run VSPAERO | PASS |
| vspaero vs oas CL | core gate | 0.914 | 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 5,602.2 kg; SU2 cruise converged=no, rmsρ=-1.770.
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 | 37.49 × 3.95 × 4.14 m |
| Wing | 34.07 m span · 122.41 m² · AR 9.48 |
| Planform | root 6.11 m · taper 0.176 · LE sweep 25.0° |
| Airfoil / thickness | NACA 2412 · t/c 0.120 |
| Twist | root +2.00° · tip -2.00° |
| Single fin | 6.86 m span · 0.0° cant |
| Propulsion | Equivalent 2 x V2527-A5 CeRAS rated deck · 235800.0 N SL |
| Fuel | 18402.00 kg delivered spec |
| Structure | wingbox · skin 25.00 mm · spar 40.00 mm |
| Material | Al7050-T7451 · yield 470 MPa |
| Item | Mass | x station |
|---|---|---|
| operating_empty | 42092.00 kg | 14.000 m |
| payload | 13608.00 kg | 15.500 m |
| fuel_wing | 11857.90 kg | 14.382 m |
| fuel_fuselage | 6544.10 kg | 14.000 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: ceras-csr01
notes: Post-hoc, truth-conditioned CeRAS CSR-01 reconstruction from public geometry,
propulsion, payload, and mission inputs. The 42,092 kg operating-empty mass and
18,402 kg fuel load are algebraically derived from the same published mission rows
used by the verification case; they are frozen inputs, not independent predictions.
The equivalent trapezoid preserves published wing span, area, and MAC. The sparse
two-engine deck contains only the two CeRAS rated conditions plus declared part-throttle
engineering interpolants. The NACA 2412 sections, equivalent-tail details, 14 m
operating-empty CG, payload/fuel-box locations, CLmax/stall screen, structural gauges,
and nacelle frontal-CD allowance are declared conceptual assumptions. The small-aircraft
OAS wingbox method explicitly refuses structural closure at this transport scale.
sketch:
treatment: reproduction
hard_scale: 3.0
fidelity_weight: 1.0
span_over_length: 0.9087756735
span_over_length_tol: 0.01
root_over_length: 0.1629367501
root_over_length_tol: 0.01
le_sweep_deg: 25.0
le_sweep_tol_deg: 2.0
taper: 0.176361983
taper_tol: 0.02
x_le_root_over_length: 0.2667377967
x_le_root_over_length_tol: 0.02
payload_bay_x_lo_m: null
payload_bay_x_hi_m: null
fuel_tank_x_lo_m: null
fuel_tank_x_hi_m: null
twist_tip_lo_deg: null
twist_tip_hi_deg: null
fin_span_m: 6.86
fin_span_tol_m: 0.2
fin_root_chord_m: 5.6
fin_root_chord_tol_m: 0.3
fin_le_sweep_deg: 40.0
fin_le_sweep_tol_deg: 5.0
fin_cant_deg: null
fin_cant_tol_deg: null
fin_x_le_m: 30.6
fin_x_le_tol_m: 0.4
engine:
name: Equivalent 2 x V2527-A5 CeRAS rated deck
energy_source: liquid_fuel
diameter_m: 1.61
length_m: 3.2
dry_mass_kg: 7362.0
installation: external
installation_count: 2
x_m: 11.41
lateral_offset_m: 5.2
z_m: -1.85
max_thrust_sl_n: 235800.0
fuel_flow_max_kg_s: 2.348568
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: 0.2
fuel_density_kg_m3: 800.0
nacelle_frontal_cd: 0.01
deck:
name: CSR-01 equivalent pair, CeRAS bucket points
points:
- altitude_m: 0.0
mach: 0.0
throttle: 0.2
thrust_n: 47160.0
fuel_flow_kg_s: 0.54017064
- altitude_m: 0.0
mach: 0.0
throttle: 0.6
thrust_n: 141480.0
fuel_flow_kg_s: 1.47959784
- altitude_m: 0.0
mach: 0.0
throttle: 1.0
thrust_n: 235800.0
fuel_flow_kg_s: 2.348568
- altitude_m: 10668.0
mach: 0.78
throttle: 0.2
thrust_n: 8680.0
fuel_flow_kg_s: 0.16699886
- altitude_m: 10668.0
mach: 0.78
throttle: 0.6
thrust_n: 26040.0
fuel_flow_kg_s: 0.45743166
- altitude_m: 10668.0
mach: 0.78
throttle: 1.0
thrust_n: 43400.0
fuel_flow_kg_s: 0.726082
interpolation: condition-idw
extrapolation: clamp
altitude_scale_m: 10668.0
mach_scale: 0.78
wing:
span_m: 34.07
root_chord_m: 6.108488762310252
taper: 0.17636198300988576
le_sweep_deg: 25.0
dihedral_deg: 5.0
twist_root_deg: 2.0
twist_tip_deg: -2.0
t_over_c: 0.12
airfoil: '2412'
x_le_root_m: 10.0
z_root_m: -0.75
sections: null
tip_chord_m: 1.0773051913146388
area_m2: 122.41000000000001
aspect_ratio: 9.482598643901643
mac_m: 4.180000000000001
y_mac_m: 6.529637728852366
x_le_mac_m: 13.04482007794167
x_ac_m: 14.08982007794167
fuselage:
length_m: 37.49
max_width_m: 3.95
max_height_m: 4.14
nose_fine_ratio: 0.2
tail_fine_ratio: 0.3
payload_bay_length_m: 19.0
payload_bay_width_m: 3.5
payload_bay_height_m: 2.2
payload_bay_x_m: 6.0
fuel_tank_x_m: 14.0
stations:
- x_over_length: 0.0
width_m: 0.0
height_m: 0.0
z_offset_m: 0.0
side_power: 2.0
top_power: 2.0
bottom_power: 2.0
max_width_loc: 0.0
- x_over_length: 0.08
width_m: 2.7
height_m: 3.1
z_offset_m: 0.0
side_power: 2.0
top_power: 2.0
bottom_power: 2.0
max_width_loc: 0.0
- x_over_length: 0.2
width_m: 3.95
height_m: 4.14
z_offset_m: 0.0
side_power: 2.0
top_power: 2.0
bottom_power: 2.0
max_width_loc: 0.0
- x_over_length: 0.68
width_m: 3.9
height_m: 4.05
z_offset_m: 0.0
side_power: 2.0
top_power: 2.0
bottom_power: 2.0
max_width_loc: 0.0
- x_over_length: 0.9
width_m: 2.2
height_m: 2.8
z_offset_m: 0.35
side_power: 2.0
top_power: 2.0
bottom_power: 2.0
max_width_loc: 0.0
- x_over_length: 1.0
width_m: 0.0
height_m: 0.0
z_offset_m: 0.55
side_power: 2.0
top_power: 2.0
bottom_power: 2.0
max_width_loc: 0.0
fairings: null
vtail:
count: 1
root_attachment: derived
span_m: 6.86
root_chord_m: 5.6
taper: 0.3
le_sweep_deg: 40.0
cant_deg: 0.0
t_over_c: 0.1
x_le_m: 30.6
y_root_m: 0.0
z_root_m: 1.75
area_m2: 24.970399999999998
htail:
span_m: 12.46
root_chord_m: 4.15
taper: 0.32
le_sweep_deg: 30.0
t_over_c: 0.1
x_le_m: 31.3
z_m: 1.45
incidence_deg: -2.1118
area_m2: 34.12794000000001
mission:
endurance_s: 22800.0
endurance_required: true
payload_kg: 13608.0
cruise_altitude_m: 10668.0
dash_altitude_m: 10668.0
cruise_mach: 0.78
cruise_cl: 0.5846538405906798
dash_mach_cap: 0.78
limit_positive_g: 2.5
limit_negative_g: -1.0
safety_factor: 1.5
static_margin_min: 0.15
static_margin_max: 0.45
reserve_fuel_fraction: 0.05
cl_max: 1.8
cl_max_basis: aircraft
stall_speed_max_mps: 75.0
pitch_trim_control: auto
structures:
fem_model_type: wingbox
spar_thickness_m: 0.04
skin_thickness_m: 0.025
tube_radius_m: 0.4
tube_thickness_m: 0.025
wing_weight_ratio: 1.35
n_spanwise: 9
n_chordwise: 3
material:
name: Al7050-T7451
E_pa: 71700000000.0
nu: 0.33
yield_pa: 470000000.0
density_kg_m3: 2830.0
G_pa: 26954887218.045113
spanwise: null
modal_calibration: []
sensor_stations: []
drag:
interference_fraction: 0.08
protuberance_cd0: 0.0005
mass:
fuel_mass_kg: 18402.0
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: 42092.0
operating_empty_cg_x_m: 14.0
systems_kg: 0.0
landing_gear_fraction: 0.0
avionics_kg: 0.0
contingency_fraction: 0.0
flight_dynamics:
enabled: false
reference_airspeed_mps: 18.0
reference_altitude_m: 0.0
inertia: null
control_surfaces: []
aeroelastic:
enabled: false
strip_count: 48
modes_per_family: 1
frequency_min_hz: 0.5
frequency_max_hz: 30.0
frequency_points: 160
maximum_reduced_frequency: 0.3
elastic_axis_fraction_chord: 0.4
lift_curve_slope_per_rad: null
calibration_id: none
allow_diagonal_inertia_approximation: false
calibration_id: none
solver:
oas_with_viscous: true
oas_with_wave: true
optimize_maxiter: 20
optimize_tol: 1.0e-05
fd_step: 0.001
vspaero_wake_iters: 12
vspaero_convergence_factor: 0.01
su2_maxiter: 200
gmsh_lc_m: 1.0
stability_method: hybrid_component
np_shift_mac: 0.1
wing_body_np_mac: 0.23350876358829661
wing_body_cl_alpha_per_deg: 0.10708004205475
cm_washout_per_deg: 0.0042
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: 3.75