What is the approximate manifold pressure setting to achieve 65 percent maximum continuous power at 6,500 feet and 2,450 RPM with a temperature that is 36°F higher than standard?

To achieve 65 percent maximum continuous power at a specific altitude and RPM, you need to consider both the ambient pressure and temperature adjustments from standard conditions.

At 6,500 feet, the atmospheric pressure is lower than at sea level, which affects the available engine power. The standard setting would typically involve a certain manifold pressure at a given temperature. However, with a temperature that is 36°F higher than standard, you must remember that an increase in temperature generally decreases engine performance due to a reduction in air density.

In the context of this question, the manifold pressure setting needs to be adjusted upward to compensate for the higher temperature, which implies slightly higher power levels are needed to maintain the desired power setting.

The chosen manifold pressure setting of 21.0 inches of mercury appropriately reflects these conditions, as it is the optimal level for achieving 65 percent maximum continuous power given the specified altitude and RPM. It takes into account both the altitude's effect on air density and the temperature deviation from the standard atmosphere, leading to a balance that provides sufficient power.

Understanding the relationship among altitude, temperature, and manifold pressure is essential for reaching the intended performance level efficiently while ensuring safe flight operations.