Advanced Aircraft Analysis (AAA) is the industry standard aircraft design, stability, and control analysis software. AAA is installed in over 55 countries and is used by major aeronautical engineering universities, aircraft manufacturers, and military organizations worldwide.

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

Advanced Aircraft Analysis Version 3.4 contains various enhancements and revisions to version 3.3 as well as bug fixes. Major enhancements include new modules and calculations. Listing of differences between AAA 3.4 and AAA 3.3:

• The effect of fuselage slenderness on the apparent mass factor is shown as an output.

• Control surface drag parameters obtained in wind tunnel tests are used to calculate full-scale control surface drag parameters. (NEW)

• The X-axis scales are different for the Empty C.G. plot and the Forward-Aft C.G. plot.

• Aerodynamic center calculations for Nacelles, Stores, Tailbooms and Floats are calculated similar to fuselage methods. (NEW)

• More variables have alternate units.

• The Help system is expanded and updated.

• Flaps, Ailerons, Elevators and Rudders are added to the Wind Tunnel Drag Module.

• An option to export aerodynamic data to the Aircraft Performance Program (APP) is added. (NEW)

• The Component C.G. module is now separated into its respective components. (NEW)

• Propeller C.G. is accounted for.

• Float C.G. is now included in the Component C.G. Module.

• A constant to estimate the dry weight of piston engines is now shown in the Class II Weight Module.

• In Class II Weight Vought methods are added to all weight calculations, Courtesy Daniel Raymer. (NEW)

• The Cost Escalation Factor is updated.

• Ventral fins are now plotted in the airplane three-view.

• Steady State coefficients are no longer linked to the calculation of the stability and control derivatives and can be included or excluded from the Recalculate module.

• There is now an option to calculate drag coefficient from the drag trend line in the Recalculate module.

• The hinge moment derivatives are no longer linked to the stability and control derivatives and can be included or excluded from the Recalculate module.