Geometric data and propulsions
Comparisons of weight, wing properties, shapes and layouts.
This is the one section of the website where real external sources are needed to provide reliable data about the airplane’s geometry and powerplants.
Lift, Drag and Aerodynamic efficiency.
A wealth of experimentally proven equations (sources available in bibliography) and complex mathematical methods (such or the Biot-Savart for calculating flow deviation) allow us to obtain accurate results for the lift and drag generation. Derived parameters such as aerodynamic effiency, theoretical maximum speeds and the flight envelope are then able to be acquired.
At the time at which WWII airplanes were being designed, neither advanced mathematical methods nor software existed to allow the designers to verify whether the aircraft would perform as planned. Field testing in various conditions often shed contradictory results.
The fluid dynamics, aerodynamics, flight mechanics,
AIAA Aerospace Engineers Guide (2003);
USAF DATCOM, by Hoak et al. (1978);
Fundamentals of Flight, by Shevell (1989),
Fluid-Dynamic Drag by Hoerner (1965);
AIAA article (Takahashi, German, Shajanian, et al.)
that allows estimating the Critical Mach Number (Journal of Aircraft, vol. 49, issue 1,
2012, ETSID library). In addition:
Fundamentals of Aircraft and Airship Design by L.Nicolai & G. Carichner (AIAA, 2010);
Aircraft Performance: An Engineering Approach by M. Sadraey (CRC, 2017); Theory and Practice of Aircraft Performance, by K. Kundu et al. (Wiley, 2018).