Aircraft design: a conceptual approach |
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Contents
Sizing from a Conceptual Sketch | 11 |
Airfoil and Geometry Selection | 33 |
ThrusttoWeight Ratio and Wing Loading | 77 |
Copyright | |
17 other sections not shown
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Common terms and phrases
actual aerodynamic center aileron aircraft weight airflow airfoil altitude analysis angle of attack approximately aspect ratio axis boundary layer calculated camber canard capture area Chapter chord climb component compression conceptual design cost cross section cruise curve defined deflection determined diameter dihedral distance downwash dynamic pressure effect engine equal equations estimated fighter Figure flap flight flow force fuel fuselage geometry horizontal tail increase induced drag initial landing gear layout leading edge leading-edge length lift coefficient lift force load factor longitudinal Mach number maximum lift methods mission nacelle nozzle parasite drag pilot pitching podded engine produce propulsion radar radius reduced roll rudder shear shock shown in Fig span stability static stress structural strut subsonic supersonic surface sweep T-tail thrust tion tire transonic turboprop turn rate typical usually velocity vertical tail wave drag wetted area wheel wing loading zero
Bibliographic information
| Title | Aircraft design: a conceptual approach Educ Series AIAA Textbook Series AIAA education series American Institute of Aeronautics and Astronautics education series |
| Author | Daniel P. Raymer |
| Editor | American Institute of Aeronautics and Astronautics |
| Edition | 2 |
| Publisher | American Institute of Aeronautics and Astronautics, 1989 |
| ISBN | 0930403517, 9780930403515 |
| Length | 729 pages |
| Subjects | › Aeronautics Airplanes Technology & Engineering / Aeronautics & Astronautics |
| Export Citation | BiBTeX EndNote RefMan |