Increase speed
The same vertical gust produces a larger lift increment as speed increases in this simple model.
06 / BOUND · Flight mechanics
Manoeuvre & Gust Envelope
Flight envelopeBrowser calculation
Move a speed–gust operating point against stall and illustrative structural boundaries. Connect the picture to lift and wing loading.
THE SAME GUST. A DIFFERENT LOAD.LIVE B
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Solid boundary: minimum of the positive stall curve and selected structural limit; lower boundary uses CLmin = −0.8 and nmin = −1.5. The graph ends at 120 m/s; this is not a design-speed limit. The gust point is an unalleviated quasi-steady estimate, not a time history or certified envelope.
Increase wing loading
At fixed speed and gust, increased mass reduces Δn. It also moves the stall boundary to a higher speed.
Respect the stall boundary
The linear gust estimate is still displayed outside the envelope, but is explicitly marked beyond the modelled admissible state. It does not predict post-stall load.
CALCULATED FROM THE SAME MODEL
Read the parameter study
B · solid turquoise A · dashed amber
Dots mark the selected settings; curves sweep one variable
Compare the evidence
| Quantity | A · saved | B · live | Unit |
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A remains fixed until you save again. Export includes settings, selected outputs and curve data.
Equations, assumptions and topic connections
Physical model
Illustrative aircraft S = 16 m², ρ = 1.225 kg/m³, lift-curve slope 5.5 rad⁻¹. A small vertical gust changes incidence by approximately Ude/V and ΔL = ½ρVS a Ude. No gust-alleviation factor, dynamic penetration, elastic response, regulatory speeds, fatigue or certification assessment is included.
n_stall = ½ρV² S CLmax/(mg); Δn = ρ V a Ude/[2(mg/S)]; n_gust = 1 + Δn; VA = √[2nlimit(mg/S)/(ρCLmax)]. Stall/structural boundaries are references, not a command to achieve a manoeuvre.
Topic connections
S42 accelerated-performance/load-factor foundation. Gust response is an explicitly labelled extension; it is not asserted to be a certified-envelope treatment in the supplied deck.
FAA · Aerodynamics for Naval Aviators
Original schematic diagrams. No manufacturer performance, certification or maintenance-authorisation claim. Numerical verification checks the declared model; it is not experimental validation. Model version: course-foundations-v1.