de Havilland DH 2 by Peter Cooksley, Richard Hudson, Glen Phillips, Don Greer

By Peter Cooksley, Richard Hudson, Glen Phillips, Don Greer

Booklet by way of Peter Cooksley

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The reason for this is the fact that aerodynamic forces and moments are all proportional to the dynamic pressure: q = V~ . 54)! 8 qualify as steady state flight conditions. 9 shows that the flight path angles for which the steady state assumption applies are riot very steep! Definition 2: Perl:ufbed State Fli&ht A perturbed state ffight condition is dermed as one for which ALL motion variables are defined relative to a known steady state ffight condition. ) ----------I. SteAdY Rectiljnrar Flight '''------------ -~/ 2.

This notation will be consistently used unless no confusion can result from Chapter 1 24 Equations of Motion and Axis Systems , dropping the subscript. 57) take on special foffilS. These special forms will now be derived. application of these forms to the problems of steady state controllability is presented in Chapter 4. 8 is characterized by the following condition: iii = 0 which in turn implies that: P 1 = 0 1 = Rl =0. 59) form the basis for studying airplane controllability problems in the following flight conditions: * Cruise * Shallow climbs, dives and glides * Engine(s) inoperative flight * Steady state flight with ce~ failed systems Applications are discussed in Chapter 4.

Flight conditions The remainder of this text is primarily concerned with the smdy and applications of the ' general' airplane equations of motion to these two sets of flight conditions. • Definition 1: Steady State Flight • A steady state ffight condition is dermed as one for which ALL motion variables remain constant with time relative to the body-rlXed axis systeill XYZ. 54) Vp and ware constant with time relative to axis system XYZ. 8 illustrates three typical steady state flight conditions, ',," It should be observed that (strictly speaking) the defmition fQr steady state flight applies only in an atmosphere of constant density.

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