Final answer:
The question requires the calculation of lift slope for a finite wing given certain conditions, which cannot be solved with the provided reference information as it refers to different physics scenarios. Specific formulas involving aspect ratio and efficiency factors are necessary to approximate the lift slope for a finite wing.
Step-by-step explanation:
The student's question deals with a flying wing with a NACA 2415 airfoil sustaining level flight at high altitude with specified conditions. However, the provided pieces of reference information do not directly address this scenario, as they relate to different situations in physics. For example, they provide information about aircraft lift at takeoff, airflow speeds required for lift at different altitudes, and other unrelated scenarios including water pressure in pipes and heart ventricle power output.
Regarding the main question of calculating the lift slope for a finite wing, specific formulas and the effects of aspect ratio and efficiency factors need to be considered, which depend on the wing's characteristics and operating conditions. These details are not provided in the reference materials. However, the lift slope for a finite wing can be approximated using the formula:
a = a0 / (1 + (57.3*a0) / (π*AR*e))
where a0 is the lift curve slope for an infinite wing, AR is the aspect ratio, and e is the Oswald efficiency number. The lift curve slope for an infinite wing with a NACA 2415 airfoil is typically around 0.11 degrees-1 at low angles of attack. The Oswald efficiency number e is typically between 0.8 and 0.9 for most wings.