Aircraft Comparison Notes and Details Page

This is the “Notes” and “Details” page for my blogs involving comparisons between aircraft where I get to explain a little bit more some of the terms and formulas used in those blogs.

For the “Maneuverability” and “Payload and Range” sections, the following considerations were made:
– Weights with 100% internal fuel was used to try to simulate the aircraft going into combat with full internal fuel after dropping their External Fuel Tanks.
– The weights of the armaments were not included as the RATIOS and DIFFERENCES BETWEEN BOTH AIRCRAFT will remain the same if they will be armed with the same type and same number of armaments.

‘Manueverability’
For both aircraft’s maneuvering capability, I am looking at their WING LOADING and POWER TO WEIGHT RATIO.

WING LOADING is the amount of weight the wing supports during flight, and is expressed in weight per area, or in the metric system, kg/m^2. This is computed by: Wing Area divided by a given Weight (Wikipedia Article – Wing Loading)

POWER TO WEIGHT RATIO on the other hand means how much power the aircraft has compared to its weight, and is expressed by a simple number. This is computed by: The Maximum Power of the aircraft’s Engine divided by a given Weight (Wikipedia Article – Thrust to Weight Ratio)

I would’ve wanted to take a look at more aspects like Stall Speed, Maximum Alpha, etc., but those data are hard to come by, hence these should suffice for now. Remember that a lower Wing Loading means the aircraft can turn tighter and vice-versa, and that a higher Thrust-to-Weight Ratio means the aircraft can go faster going straight up or straight down, and vice-versa.

‘Payload and Range’
For Range, I am using INTERNAL FUEL FRACTION (INTFF) as a rough indicator how far each aircraft can go based on the internal fuel available to them.

INTERNAL FUEL FRACTION is the weight of the internal fuel the aircraft compared to its maximum take-off weight, and is expressed by a simple number (meaning with no units of measurement). Formula used is: Maximum internal fuel capacity divided by maximum takeoff weight (Wikipedia Article – Fuel Fraction)

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