Hacker A40-12 S V2 / Jeti SPIN Pro 66 / Aeronaut CAM 14x8 tailless UAV · 0.0 kg payload · baseline-to-optimized evidence with an embedded model of the actual exported mesh.
This 2026-08-22 report is retained as sealed historical evidence. Its original generator claimed concept-source and optimized-spec paths that were never committed and cannot be regenerated under the current schema. Read the embedded results in that historical context; this notice does not reopen or alter the holdout evidence.
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-MAPPED CONFIGURATION NTNU Skywalker X8, May 2023 system-identification configuration: a tailless swept flying wing with two blended tip fins, one rear electric pusher, and mirrored elevons mixed collectively for pitch and differentially for roll. The equivalent trapezoid is source-bounded and reproduces the public b=2.10 m, Sref=0.75 m^2, and MAC=0.36 m exactly. Its 25 deg leading-edge sweep carries the input pack's +/-5 deg allowance. The NACA 0012 section and +2/-2 deg twist are explicitly disclosed geometric surrogates because the molded production airfoil and twist are not known. The test-configuration 2.10 m span is used rather than the separately noted 2.12 m catalog span.
SOURCE DATA RETAINED HERE BECAUSE VEHICLESPEC HAS NO DEDICATED FIELDS Fuselage source note: 0.790 m is the manufacturer length; the 0.180 m width, 0.170 m height, and loft are bounded installation-drawing estimates. Tip-fin dimensions are source-bounded equivalents fitted to the visible blended fins. The measured campaign trim alpha was 8.0 deg; horizontal wind was 9.0 m/s and inferred vertical wind was 2.8 m/s. Those values document the operating condition and are not aerodynamic coefficients.
Electric hardware: Hacker A40-12 S V2 14-pole KV610 motor, Jeti SPIN Pro 66 controller, Aeronaut CAM folding 14x8 propeller, 16.0 V nominal supply, back-EMF constant 0.0157 V/(rad/s), motor resistance 0.017 ohm, propeller diameter 0.3556 m, and propeller inertia 0.000346 kg m^2. Published nondimensional propeller polynomials are CT(J) = 0.1400 - 0.0300 J - 0.2370 J^2 + 0.0847 J^3 and CQ(J) = 0.0082 + 0.0112 J - 0.0211 J^2. The seven schema deck points retain every supplied thrust value; airspeed was converted to Mach with ISA sea-level a=340.293988026089 m/s because the supplied deck derivation uses rho=1.225 kg/m^3. Electric fuel flow is zero.
The measured 3.364 kg flight mass includes battery and installed propulsion. With no separately declared payload or liquid fuel, it is represented as a measured operating-empty mass at the public xCG=0.435 m nose station. That nominal station is the midpoint of the source-noted 0.430-0.440 m CG range. The full measured inertia tensor, including Ixz=0.029 kg m^2, is retained in flight_dynamics. Elodin's diagonal-only boundary is explicitly allowed, but the source tensor itself is not diagonalized here.
DECLARED CALIBRATION flight_dynamics.calibration_id is ntnu-x8-low-re-elevon-v1, selected only by the identifier supplied in the design-time pack. No implementation or fitted factor is copied into this design. The pack declares that identifier frozen from 13 publisher-designated training maneuvers for four scalar low-Re collective/differential elevon-effectiveness and pitch/roll-damping corrections; four publisher-designated validation maneuvers remain untouched.
ENGINEERING ASSUMPTIONS (NOT SOURCE CLAIMS) Zero wing dihedral and the reference z stations define the schema coordinate system. Parametric fuselage fineness, payload-bay dimensions, inactive tank station, pusher packaging envelope/mass/location, and tip-fin attachment coordinates are conservative conceptual placeholders. The assumed fin root has its trailing edge at the 0.790 m body station and lies near the local swept-wing leading edge. The measured all-up mass override prevents assumed component bookkeeping from changing flight mass.
No battery capacity or electric endurance was supplied, so endurance is explicitly not claimed; endurance_s=1 is only the schema-required positive placeholder. Level-flight cruise CL is derived from measured mass, Sref, 18 m/s, and ISA density at 175 m. Stall, load-factor, static-margin, drag, structural-material, and solver values are conservative generic conceptual assumptions, not NTNU measurements or validation outcomes.
INPUT-PACK SOURCES Løw-Hansen et al. (2025), doi:10.1007/s13272-025-00816-3; NTNU Dataverse dataset doi:10.18710/U4TLYV; Gryte et al. (2018), doi:10.1109/ICUAS.2018.8453370; Reinhardt et al. (2022), doi:10.1109/ICUAS54217.2022.9836104; Skywalker manufacturer installation material.
One or more preliminary-design gates failed. Review the red evidence cards and fix the upstream model before presenting the concept as viable.
| Requirement | Target | Predicted | Verdict |
|---|---|---|---|
| Engine | Hacker A40-12 S V2 / Jeti SPIN Pro 66 / Aeronaut CAM 14x8 | Hacker A40-12 S V2 / Jeti SPIN Pro 66 / Aeronaut CAM 14x8 | MET |
| Payload | 0.0 kg | 0.0 kg | MET |
| Endurance | not claimed | n/a | N/A |
| Dash | maximize; M ≤ 0.30 | 228 km/h · M 0.19 | MET |
| Configuration | sketch envelope | 2.10 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=24
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 0.011 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 0.080; reserve 0.080 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.
washout 4.000° vs spec 4.000°; CM residual -0.0010
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 8.474 m/s ≤ 18.0 m/s at CLmax 1.00
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 0.0107; same-run Cnβ 0.0113, Cnr -0.0069 (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.
+4g failure index -0.958; CL 0.792/0.792; lift closed=yes; mass closed=yes; tip deflection 0.001 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 2.66; root/L 0.52; 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 0.998; NP method spread 0.018 MAC (diagnostic); report Mach 0.187 vs recomputed 0.187; MTOW report/aero/MDO 3.364/3.364/3.364 kg; L/D report/aero/MDO 9.539/9.539/9.539
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 delivered configuration is checked by a separate OAS solve. Stability evidence is labeled by method: an independent lifting-surface derivative or a same-run VSPAERO component model combined with the declared tail model.
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 228 km/h delivered configuration.
| Start | Dash | Endurance | MTOW | Feasible |
|---|---|---|---|---|
| deterministic_reference_closure | 228 km/h | n/a | 3.4 kg | yes |
| Attempt | Internal band | Evaluated full / reserve | Verdict |
|---|---|---|---|
| same-run OAS NP | model error ≤ 0.05 MAC | 0.059 / 0.000 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 | 0.011 | >= 0.02 or passing same-run directional derivatives (source-locked reproduction) | PASS |
| fin te within body | core gate | -0.040 | <= 0.0158 m | PASS |
| neutral point model vs oas | core gate | 0.464 | 0.464 | PASS |
| wing mass buildup vs oas | core gate | 1.587 | 0 < wing structural mass < 3.364 kg reference OE mass | PASS |
| vspaero vs oas CL | core gate | 0.998 | n/a | 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 0.782 kg; SU2 cruise converged=no, rmsρ=-2.294.
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 | 0.79 × 0.18 × 0.17 m |
| Wing | 2.10 m span · 0.75 m² · AR 5.88 |
| Planform | root 0.41 m · taper 0.732 · LE sweep 25.0° |
| Airfoil / thickness | NACA 0012 · t/c 0.120 |
| Twist | root +2.00° · tip -2.00° |
| Twin fins | 0.22 m span each · 12.0° cant |
| Propulsion | Hacker A40-12 S V2 / Jeti SPIN Pro 66 / Aeronaut CAM 14x8 · 60.4 N SL |
| Fuel | 0.00 kg delivered spec |
| Structure | wingbox · skin 1.00 mm · spar 1.50 mm |
| Material | Assumed quasi-isotropic CFRP equivalent · yield 250 MPa |
| Item | Mass | x station |
|---|---|---|
| operating_empty | 3.36 kg | 0.435 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: ntnu-x8-capstone-blind
notes: "SOURCE-MAPPED CONFIGURATION\nNTNU Skywalker X8, May 2023 system-identification\
\ configuration: a tailless\nswept flying wing with two blended tip fins, one rear\
\ electric pusher, and\nmirrored elevons mixed collectively for pitch and differentially\
\ for roll.\nThe equivalent trapezoid is source-bounded and reproduces the public\n\
b=2.10 m, Sref=0.75 m^2, and MAC=0.36 m exactly. Its 25 deg leading-edge\nsweep\
\ carries the input pack's +/-5 deg allowance. The NACA 0012 section and\n+2/-2\
\ deg twist are explicitly disclosed geometric surrogates because the\nmolded production\
\ airfoil and twist are not known. The test-configuration\n2.10 m span is used rather\
\ than the separately noted 2.12 m catalog span.\n\nSOURCE DATA RETAINED HERE BECAUSE\
\ VEHICLESPEC HAS NO DEDICATED FIELDS\nFuselage source note: 0.790 m is the manufacturer\
\ length; the 0.180 m width,\n0.170 m height, and loft are bounded installation-drawing\
\ estimates.\nTip-fin dimensions are source-bounded equivalents fitted to the visible\n\
blended fins. The measured campaign trim alpha was 8.0 deg; horizontal wind\nwas\
\ 9.0 m/s and inferred vertical wind was 2.8 m/s. Those values document\nthe operating\
\ condition and are not aerodynamic coefficients.\n\nElectric hardware: Hacker A40-12\
\ S V2 14-pole KV610 motor, Jeti SPIN Pro 66\ncontroller, Aeronaut CAM folding 14x8\
\ propeller, 16.0 V nominal supply,\nback-EMF constant 0.0157 V/(rad/s), motor resistance\
\ 0.017 ohm, propeller\ndiameter 0.3556 m, and propeller inertia 0.000346 kg m^2.\
\ Published\nnondimensional propeller polynomials are CT(J) = 0.1400 - 0.0300 J\
\ -\n0.2370 J^2 + 0.0847 J^3 and CQ(J) = 0.0082 + 0.0112 J - 0.0211 J^2.\nThe seven\
\ schema deck points retain every supplied thrust value; airspeed\nwas converted\
\ to Mach with ISA sea-level a=340.293988026089 m/s because the\nsupplied deck derivation\
\ uses rho=1.225 kg/m^3. Electric fuel flow is zero.\n\nThe measured 3.364 kg flight\
\ mass includes battery and installed propulsion.\nWith no separately declared payload\
\ or liquid fuel, it is represented as a\nmeasured operating-empty mass at the public\
\ xCG=0.435 m nose station. That\nnominal station is the midpoint of the source-noted\
\ 0.430-0.440 m CG range.\nThe full measured inertia tensor, including Ixz=0.029\
\ kg m^2, is retained in\nflight_dynamics. Elodin's diagonal-only boundary is explicitly\
\ allowed, but\nthe source tensor itself is not diagonalized here.\n\nDECLARED CALIBRATION\n\
flight_dynamics.calibration_id is ntnu-x8-low-re-elevon-v1, selected only by\nthe\
\ identifier supplied in the design-time pack. No implementation or fitted\nfactor\
\ is copied into this design. The pack declares that identifier frozen\nfrom 13\
\ publisher-designated training maneuvers for four scalar low-Re\ncollective/differential\
\ elevon-effectiveness and pitch/roll-damping\ncorrections; four publisher-designated\
\ validation maneuvers remain untouched.\n\nENGINEERING ASSUMPTIONS (NOT SOURCE\
\ CLAIMS)\nZero wing dihedral and the reference z stations define the schema coordinate\n\
system. Parametric fuselage fineness, payload-bay dimensions, inactive tank\nstation,\
\ pusher packaging envelope/mass/location, and tip-fin attachment\ncoordinates are\
\ conservative conceptual placeholders. The assumed fin root\nhas its trailing edge\
\ at the 0.790 m body station and lies near the local\nswept-wing leading edge.\
\ The measured all-up mass override prevents assumed\ncomponent bookkeeping from\
\ changing flight mass.\n\nNo battery capacity or electric endurance was supplied,\
\ so endurance is\nexplicitly not claimed; endurance_s=1 is only the schema-required\
\ positive\nplaceholder. Level-flight cruise CL is derived from measured mass, Sref,\n\
18 m/s, and ISA density at 175 m. Stall, load-factor, static-margin, drag,\nstructural-material,\
\ and solver values are conservative generic conceptual\nassumptions, not NTNU measurements\
\ or validation outcomes.\n\nINPUT-PACK SOURCES\nL\xF8w-Hansen et al. (2025), doi:10.1007/s13272-025-00816-3;\
\ NTNU Dataverse\ndataset doi:10.18710/U4TLYV; Gryte et al. (2018),\ndoi:10.1109/ICUAS.2018.8453370;\
\ Reinhardt et al. (2022),\ndoi:10.1109/ICUAS54217.2022.9836104; Skywalker manufacturer\
\ installation\nmaterial."
sketch:
treatment: reproduction
hard_scale: 1.0
fidelity_weight: 1.0
span_over_length: 2.6582278481012658
span_over_length_tol: 0.03
root_over_length: 0.5221154312153242
root_over_length_tol: 0.03
le_sweep_deg: 25.0
le_sweep_tol_deg: 5.0
taper: 0.7317226765403747
taper_tol: 0.05
x_le_root_over_length: 0.1864556962025316
x_le_root_over_length_tol: 0.04430379746835443
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: -3.0
twist_tip_hi_deg: -1.0
fin_span_m: 0.22
fin_span_tol_m: 0.03
fin_root_chord_m: 0.3
fin_root_chord_tol_m: 0.04
fin_le_sweep_deg: 35.0
fin_le_sweep_tol_deg: 5.0
fin_cant_deg: 12.0
fin_cant_tol_deg: 5.0
fin_x_le_m: 0.49
fin_x_le_tol_m: 0.035
engine:
name: Hacker A40-12 S V2 / Jeti SPIN Pro 66 / Aeronaut CAM 14x8
energy_source: electric
diameter_m: 0.06
length_m: 0.12
dry_mass_kg: 0.5
installation: external
installation_count: 1
x_m: 0.74
lateral_offset_m: 0.0
z_m: 0.02
max_thrust_sl_n: 60.3845350822
fuel_flow_max_kg_s: 0.0
thrust_lapse_k_mach: 0.0
thrust_lapse_floor: 1.0
tsfc_part_a: 1.0
tsfc_part_b: 0.0
tsfc_mach_k: 0.0
min_throttle: 0.3
fuel_density_kg_m3: 800.0
nacelle_frontal_cd: 0.08
deck:
name: Published X8 electric thrust deck at rho=1.225 kg/m^3
points:
- altitude_m: 0.0
mach: 0.0
throttle: 0.3
thrust_n: 6.1245397711
fuel_flow_kg_s: 0.0
- altitude_m: 0.0
mach: 0.0
throttle: 0.6
thrust_n: 23.215699427
fuel_flow_kg_s: 0.0
- altitude_m: 0.0
mach: 0.0
throttle: 1.0
thrust_n: 60.3845350822
fuel_flow_kg_s: 0.0
- altitude_m: 0.0
mach: 0.05289543933588392
throttle: 0.6
thrust_n: 10.979210524
fuel_flow_kg_s: 0.0
- altitude_m: 0.0
mach: 0.05289543933588392
throttle: 1.0
thrust_n: 44.0867415841
fuel_flow_kg_s: 0.0
- altitude_m: 0.0
mach: 0.07346588796650545
throttle: 0.6
thrust_n: 3.5675422739
fuel_flow_kg_s: 0.0
- altitude_m: 0.0
mach: 0.07346588796650545
throttle: 1.0
thrust_n: 34.6208306371
fuel_flow_kg_s: 0.0
interpolation: condition-idw
extrapolation: clamp
altitude_scale_m: 10000.0
mach_scale: 1.0
wing:
span_m: 2.1
root_chord_m: 0.4124711906601062
taper: 0.7317226765403747
le_sweep_deg: 25.0
dihedral_deg: 0.0
twist_root_deg: 2.0
twist_tip_deg: -2.0
t_over_c: 0.12
airfoil: '0012'
x_le_root_m: 0.1473
z_root_m: 0.0
tip_chord_m: 0.3018145236256081
area_m2: 0.75
aspect_ratio: 5.88
mac_m: 0.36
y_mac_m: 0.49788911657654805
x_le_mac_m: 0.3794695079716712
x_ac_m: 0.4694695079716712
fuselage:
length_m: 0.79
max_width_m: 0.18
max_height_m: 0.17
nose_fine_ratio: 0.22
tail_fine_ratio: 0.28
payload_bay_length_m: 0.3
payload_bay_width_m: 0.12
payload_bay_height_m: 0.1
payload_bay_x_m: 0.2
fuel_tank_x_m: 0.435
stations: null
vtail:
count: 2
span_m: 0.22
root_chord_m: 0.3
taper: 0.45
le_sweep_deg: 35.0
cant_deg: 12.0
t_over_c: 0.1
x_le_m: 0.49
y_root_m: 0.75
z_root_m: 0.02
area_m2: 0.04785
htail:
span_m: 0.0
root_chord_m: 0.1
taper: 0.5
le_sweep_deg: 0.0
t_over_c: 0.1
x_le_m: 0.49
z_m: 0.02
incidence_deg: 0.0
area_m2: 0.0
mission:
endurance_s: 1.0
endurance_required: false
payload_kg: 0.0
cruise_altitude_m: 175.0
dash_altitude_m: 175.0
cruise_mach: 0.053000154399591666
cruise_cl: 0.2254109964699504
dash_mach_cap: 0.3
limit_positive_g: 4.0
limit_negative_g: -2.0
safety_factor: 1.5
static_margin_min: 0.03
static_margin_max: 0.1
reserve_fuel_fraction: 0.0
cl_max: 1.0
cl_max_basis: aircraft
stall_speed_max_mps: 18.0
structures:
fem_model_type: wingbox
spar_thickness_m: 0.0015
skin_thickness_m: 0.001
tube_radius_m: 0.012
tube_thickness_m: 0.001
wing_weight_ratio: 1.2
n_spanwise: 9
n_chordwise: 3
material:
name: Assumed quasi-isotropic CFRP equivalent
E_pa: 35000000000.0
nu: 0.3
yield_pa: 250000000.0
density_kg_m3: 1600.0
G_pa: 13461538461.538462
drag:
interference_fraction: 0.08
protuberance_cd0: 0.004
mass:
fuel_mass_kg: 0.0
fuel_mass_mode: fixed
operating_empty_mass_kg: 3.364
operating_empty_cg_x_m: 0.435
systems_kg: 0.0
landing_gear_fraction: 0.0
avionics_kg: 0.0
contingency_fraction: 0.0
flight_dynamics:
enabled: true
reference_airspeed_mps: 18.0
reference_altitude_m: 175.0
inertia:
ixx_kg_m2: 0.325
iyy_kg_m2: 0.14
izz_kg_m2: 0.4
ixy_kg_m2: 0.0
ixz_kg_m2: 0.029
iyz_kg_m2: 0.0
source: "L\xF8w-Hansen et al. May 2023 configuration; bifilar provenance in Reinhardt\
\ et al."
elevon:
span_start_fraction: 0.48
span_end_fraction: 0.94
chord_fraction: 0.2
max_up_deg: 20.0
max_down_deg: 20.0
source: Visible X8 elevons and Gryte et al. +/-20 deg control sweeps
allow_diagonal_inertia_approximation: true
calibration_id: ntnu-x8-low-re-elevon-v1
solver:
oas_with_viscous: true
oas_with_wave: false
optimize_maxiter: 35
optimize_tol: 1.0e-05
fd_step: 0.001
vspaero_wake_iters: 5
su2_maxiter: 200
gmsh_lc_m: 0.08
stability_method: lifting_surface
np_shift_mac: -0.015612415298241498
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
n_ult: 6.0