Path: Airships/Analysis
% Evaluate the maximum velocity and thrust for the airship throughout its altitude range. The maximum velocity and thrust are computed based upon the assumption that thrust = drag at the maximum velocity, with a constant power limit applied throughout. -------------------------------------------------------------------------- Form: [llh,ra,rEF,t] = DASim( x0, d, hMin ); -------------------------------------------------------------------------- ------ Inputs ------ Cd0 (1,1) Zero angle drag coefficient Vol23 (1,1) Reference area, volume^(2/3) (m^2) Pmax (1,1) Maximum available power (W) h (1,N) Altitude vector (m) ------- Outputs ------- Vmax (1,N) Maximum velocity at each altitude Tmax (1,N) Maximum required thrust at each altitude q (1,N) Max dynamic pressure at each altitude --------------------------------------------------------------------------
AerospaceUtils: AeroData/AtmData Common: Graphics/NewFig
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