User manual MATLAB AEROSPACE TOOLBOX 2

[. . . ] Aerospace Toolbox 2 User's Guide How to Contact The MathWorks Web Newsgroup www. mathworks. com/contact_TS. html Technical Support www. mathworks. com comp. soft-sys. matlab suggest@mathworks. com bugs@mathworks. com doc@mathworks. com service@mathworks. com info@mathworks. com Product enhancement suggestions Bug reports Documentation error reports Order status, license renewals, passcodes Sales, pricing, and general information 508-647-7000 (Phone) 508-647-7001 (Fax) The MathWorks, Inc. 3 Apple Hill Drive Natick, MA 01760-2098 For contact information about worldwide offices, see the MathWorks Web site. Aerospace Toolbox User's Guide © COPYRIGHT 2006­2010 by The MathWorks, Inc. The software described in this document is furnished under a license agreement. The software may be used or copied only under the terms of the license agreement. [. . . ] Vertical locations of the center of gravity. Body base area. Stored with Indices of. . . mach, alt, number of runs mach, alt, number of runs (normally 1, 2 for hypers = true) mach, alt, number of runs (normally 1, 2 for hypers = true) mach, alt, number of runs (normally 1, 2 for hypers = true) mach, alt, number of runs (normally 1, 2 for hypers = true) mach, alt, number of runs (normally 1, 2 for hypers = true) mach, alt, number of runs (normally 1, 2 for hypers = true) mach, alt, number of runs (normally 1, 2 for hypers = true) mach, alt mach, alt alpha, mach, alt alpha, mach, alt alpha, mach, alt zcg_b basearea_b cd0_b Body zero lift drags. basedrag_b Body base drags. fricdrag_b Body friction drags. presdrag_b Body pressure drags. lemac sidewash hiv_b_w hiv_w_h hiv_b_h Leading edge mean aerodynamic chords. sidewash iv-b(w) iv-w(h) iv-b(h) 4-118 datcomimport Auxiliary and Partial Fields Available for the 1976 Version (Continued) Field gamma gamma2pialpvr clpgammacl0 clpgammaclp cnptheta cypgamma cypcl clbgamma cmothetaw cmothetah espeff despdalpeff dragdiv cd0mach cd0 clbclmfb_**** Matrix of. . . gamma*2*pi*alpha*v*r gamma*(2*pi*alpha*v*r)t clp(gamma=cl=0) clp(gamma)/cl (gamma=0) cnp/theta cyp/gamma cyp/cl (cl=0) clb/gamma (cmo/theta)w (cmo/theta)h (epsoln)eff d(epsoln)/d(alpha) eff drag divergence mach number Stored with Indices of. . . alpha, mach, alt alpha, mach, alt mach, alt mach, alt mach, alt mach, alt mach, alt mach, alt mach, alt mach, alt alpha, mach, and alt alpha, mach, alt mach, alt index, mach, alt index, mach, alt mach, alt. Four Mach numbers for the zero lift drag. Four zero lift drags. (clb/cl)mfb, where **** is either wb (wing-body) or bht (body-horizontal tail). cnam14_**** (cna)m=1. 4, where **** is either wb (wing-body) or bht mach, alt (body-horizontal tail). 4-119 datcomimport Auxiliary and Partial Fields Available for the 1976 Version (Continued) Field area_*_** Matrix of. . . Areas, where * is either w (wing), ht (horizontal tail), vt (vertical tail), or vf (ventral fin) and ** is either tt (total theoretical), ti (theoretical inboard), te (total exposed), ei (exposed inboard), or o (outboard). Taper ratios, where * is either w (wing), ht (horizontal tail), vt (vertical tail), or vf (ventral fin) and ** is either tt (total theoretical), ti (theoretical inboard), te (total exposed), ei (exposed inboard), or o (outboard). Aspect ratios, where * is either w (wing), ht (horizontal tail), vt (vertical tail), or vf (ventral fin) and ** is either tt (total theoretical), ti (theoretical inboard), te (total exposed), ei (exposed inboard), or o (outboard). Quarter chord sweeps, where * is either w (wing), ht (horizontal tail), vt (vertical tail), or vf (ventral fin) and ** is either tt (total theoretical), ti (theoretical inboard), te (total exposed), ei (exposed inboard), or o (outboard). Stored with Indices of. . . mach, alt, number of runs (normally 1, 2 for hypers = true) taperratio_*_** mach, alt, number of runs (normally 1, 2 for hypers = true) aspectratio_*_** mach, alt, number of runs (normally 1, 2 for hypers = true) qcsweep_*_** mach, alt, number of runs (normally 1, 2 for hypers = true) 4-120 datcomimport Auxiliary and Partial Fields Available for the 1976 Version (Continued) Field mac_*_** Matrix of. . . Mean aerodynamic chords, where * is either w (wing), ht (horizontal tail), vt (vertical tail), or vf (ventral fin) and ** is either tt (total theoretical), ti (theoretical inboard), te (total exposed), ei (exposed inboard), or o (outboard). Quarter chord x(mac), where * is either w (wing), ht (horizontal tail), vt (vertical tail), or vf (ventral fin) and ** is either tt (total theoretical), ti (theoretical inboard), te (total exposed), ei (exposed inboard), or o (outboard). y(mac), where * is either w (wing), ht (horizontal tail), vt (vertical tail), or vf (ventral fin) and ** is either tt (total theoretical), ti (theoretical inboard), te (total exposed), ei (exposed inboard), or o (outboard). Stored with Indices of. . . mach, alt, number of runs (normally 1, 2 for hypers = true) qcmac_*_** mach, alt, number of runs (normally 1, 2 for hypers = true) ymac_*_** mach, alt, number of runs (normally 1, 2 for hypers = true) cd0_*_** Zero lift drags, where * is either w (wing), ht (horizontal tail), vt (vertical tail), or vf (ventral fin) and ** is either tt (total theoretical), ti (theoretical inboard), te (total exposed), ei (exposed inboard), or o (outboard). mach, alt, number of runs (normally 1, 2 for hypers = true) 4-121 datcomimport Auxiliary and Partial Fields Available for the 1976 Version (Continued) Field friccoeff_*_** Matrix of. . . Friction coefficients, where * is either w (wing), ht (horizontal tail), vt (vertical tail), or vf (ventral fin) and ** is either tt (total theoretical), ti (theoretical inboard), te (total exposed), ei (exposed inboard), or o (outboard). cla-b(***), where *** is either w (wing) or ht (stabilizer). cla-***(b), where *** is either w (wing) or ht (stabilizer). k-b(***), where *** is either w (wing) or ht (stabilizer). k-***(b), where *** is either w (wing) or ht (stabilizer). xac/c-b(***), where *** is either w (wing) or ht (stabilizer). cdl/cl^2, where *** is either w (wing) or ht (stabilizer). clb/cl, where *** is either w (wing) or ht (stabilizer). Stored with Indices of. . . mach, alt, number of runs (normally 1, 2 for hypers = true) cla_b_*** mach, alt, number of runs (normally 1, 2 for hypers = true) mach, alt, number of runs (normally 1, 2 for hypers = true) mach, alt, number of runs (normally 1, 2 for hypers = true) mach, alt, number of runs (normally 1, 2 for hypers = true) mach, alt, number of runs (normally 1, 2 for hypers = true) mach, alt mach, alt cla_***_b k_b_*** k_***_b xacc_b_*** cdlcl2_*** clbcl_*** 4-122 datcomimport Auxiliary and Partial Fields Available for the 1976 Version (Continued) Field fmach0_*** Matrix of. . . Force break Mach numbers with zero sweep, where *** is either w (wing) or ht (stabilizer). Force break Mach numbers with sweep, where *** is either w (wing) or ht (stabilizer). mach(a), where *** is either w (wing) or ht (stabilizer). mach(b), where *** is either w (wing) or ht (stabilizer). cla(a), where *** is either w (wing) or ht (stabilizer). cla(b), where *** is either w (wing) or ht (stabilizer). (clb/cl)m=0. 6, where *** is either w (wing) or ht (stabilizer). [. . . ] 10 2, 2, 2, 1, 1, 1; ]; b. TimeSeriesSource = tsdata; b. update(5); See Also load 4-291 update (Aero. Camera) Purpose Syntax Description Update camera position based on time and position of other Aero. Body objects update(h, newtime, bodies) h. update(newtime, bodies) update(h, newtime, bodies) and h. update(newtime, bodies) update the camera object, h, position and aim point data based on the new time, newtime, and position of other Aero. Body objects, bodies. This function updates the camera object PrevTime property to newtime. Aero. Animation. play See Also 4-292 update (Aero. FlightGearAnimation) Purpose Syntax Description Update position data to FlightGear animation object update(h, time) h. update(time) update(h, time) and h. update(time) update the position data to the FlightGear animation object via UDP. It sets the new position and attitude of body h. [. . . ]