Analysis of the Influence of Aircraft Design Parameters on Air-to-Air Combat Capability.

A computer study was made to analyze the influence on close-in air-to-air combat success rates of wing loading, thrust loading and limit load factor utilizing twelve different combinations of these aircraft design parameters. A single set of engine performance data was used for all aircraft. Wing loadings of 50 psf, 60 psf and 80 psf were combined with limit load factors of 6.5 g, 7.5 g, 8.5 g and 9.5 g with appropriate thrust loading increases to account for the weight growth due to structural changes. These parameter variations were analyzed in sixty six one-on-one air combat engagements. Results of the study showed a decided advantage for the aircraft with the lowest wing loading. At a low wing loading, the advantage then increased with limit load factor growth but peaked at 8.5 gs. Data analysis indicated a limit load factor of approximately 9 to be optimum for the given engine performance at the 50 psf wing loading. Large increases in thrust-to-weight ratios for a high wing loaded aircraft were necessary to offset the advantage of a low wing loading. In addition, an increase in thrust-to-weight ratio did not significantly improve the success rate when lift or limit load factor was the primary maneuvering constraint.