dyhaa.blogg.se - Angle of attack 737 torrent

Statistical relations between empty weight and take-off weight of existing similar aircraft.

These parameters are estimated on the basis of the following input:

Sensitivity of take-off weight to aerodynamic, propulsion and mission parameters.

The purpose of the Weight Sizing module is to rapidly estimate the following weight components and/or sensitivity coefficients: The accuracy of Class II methods is therefore greater than Class I methods. Class II uses more sophisticated methods than Class I and requires more detailed information of the airplane to be known. Class II design accounts for power plant installation, landing gear disposition and component locations on the airplane. Class II design incorporates detailed weight & balance, aerodynamics, stability & control calculations including trim analysis and flying qualities used in conjunction with the preliminary design sequence. Most other modules do not have a speed dependency and can be used in any speed regime.ĪAA is used for preliminary and Class II design and stability and control analysis of new and existing aircraft. It does not calculate the derivatives for transonic and supersonic flow. The stability and control derivatives modules only deal with subsonic flow (up to about Mach=0.7) for most derivatives. The detailed drag module allows designers to go all the way to supersonic flow. The AAA program allows students and preliminary design engineers to take an aircraft configuration from early weight sizing through open loop and closed loop dynamic stability and sensitivity analysis, while working within regulatory and cost constraints.ĪAA can be used to design fighter style aircraft and high speed aircraft.

AAA provides a powerful framework to support the iterative and non-unique process of aircraft preliminary design.