Flight Vehicle Performance and Aerodynamic ControlAmerican Institute of Aeronautics and Astronautics, 2001 - Počet stran: 359 "Flight Vehicle Performance and Aerodynamic Control" is designed to serve as a text for either an 11-week or a 16-week course at the sophomore level. It explains typical methods used to estimate aircraft performance, the theoretical basis of these methods, and how various parameters derived from the aircraft geometry can be used to estimate the requirements of control surfaces and the aerodynamic forces required to actuate these surfaces. This book includes time-tested computer programs that perform the analyses in a manner that reduces student error and improves result accuracy. Because the source code is given, users with a FORTRAN compiler can modify the program to suit particular needs. The major advantage of the software is that more realistic problems may be treated and the effects of parametric programs are more accurate than calculators. The programs are available as executables for Windows machines as well as in ASCII source code versions that can be readily compiled and then executed on Unix, Linux, and Macintosh machines, and on mainframes. |
Vyhledávání v knize
Výsledky 1-3 z 31
Strana 105
... axes are absolute velocities , because at any instant , the Eulerian axes are considered to be fixed in space . Also , moments and products of inertia in the Eulerian axis system are independent of time , because these axes are fixed in ...
... axes are absolute velocities , because at any instant , the Eulerian axes are considered to be fixed in space . Also , moments and products of inertia in the Eulerian axis system are independent of time , because these axes are fixed in ...
Strana 114
... axes are referred to as stability axes . When the airframe is disturbed from the steady flight condition , the Eulerian axes rotate with the airframe and do not change direction with respect to the airplane . Consequently , the disturbed X ...
... axes are referred to as stability axes . When the airframe is disturbed from the steady flight condition , the Eulerian axes rotate with the airframe and do not change direction with respect to the airplane . Consequently , the disturbed X ...
Strana 253
... axis relative to the X axis . 12 ) Iyy is the moment of inertia about the aircraft the Y axis . 13 ) m is the aircraft mass . 14 ) g is the acceleration caused by gravity . 15 ) Mu is the change in pitching moment caused by a change in ...
... axis relative to the X axis . 12 ) Iyy is the moment of inertia about the aircraft the Y axis . 13 ) m is the aircraft mass . 14 ) g is the acceleration caused by gravity . 15 ) Mu is the change in pitching moment caused by a change in ...
Obsah
Classification of Flight Vehicles | 5 |
xi | 32 |
The Atmosphere | 39 |
Autorská práva | |
Další části 9 nejsou zobrazeny.
Další vydání - Zobrazit všechny
Běžně se vyskytující výrazy a sousloví
aerodynamic aileron aircraft airfoil airframe airplane airstream altitude angle of attack aspect ratio Assume atmosphere axial-flow compressor axis blade angle Boeing c.g. location characteristics chord compressor configuration constant control surface cruise density determine distance drag coefficient dynamic effects efficiency enter equations factor fighter flaps flow flying ft/s ft² fuselage given gross weight horizontal tail increase induced drag input ISBN jet engines lift coefficient longitudinal Mach number miles motion NACA operating output parameters passenger PATHPE performance pilot piston engines pitching pitching moment power required pressure problem propeller radial rate of climb result Reynolds number rudder sea level specific fuel consumption speed of sound stability derivative STADER97 static thrust stick force takeoff weight temperature tests true airspeed turbine U.S. Air Force usually velocity wind tunnel wing area wing loading wing span zero