See the result, learn how it was calculated, and practice explaining it like you would on a checkride.
Enter your aircraft, airport conditions and weight, and SkeyeMentor will compute takeoff and landing distances using verified POH data — then walk you through every step of the calculation.
Lycoming IO-360-L2A (180 HP)
Max TO Weight: 2,550 lb
Values digitized from the Cessna 172S POH for training and educational purposes. Always verify performance using the cur…
Only procedures supported by the selected aircraft's digitized data are available.
Planning margin is displayed separately from the POH-derived result.
Takeoff performance depends on the interaction of pressure altitude, temperature, aircraft weight, wind, runway surface and aircraft configuration. The Pilot’s Operating Handbook (POH) provides performance charts or tables that give ground roll and total distance to clear a 50-foot obstacle under specific conditions. When actual conditions fall between the charted values, interpolation is used to determine the applicable distance.
Landing performance charts work similarly to takeoff charts. They show ground roll (from touchdown to a complete stop) and the total distance from a 50-foot obstacle to a complete stop. Higher density altitude, greater weight and tailwind components all increase landing distances, while headwind reduces them.
Ground roll is the distance the aircraft travels along the runway surface during the takeoff or landing roll. The 50-foot obstacle distance includes the ground roll plus the additional distance required to climb to (or descend from) 50 feet above the runway. The obstacle distance is always larger and is the value most relevant to obstacle clearance.
Pressure altitude is the altitude indicated when the altimeter is set to 29.92 inHg. A common training approximation is: PA = Field Elevation + (29.92 − Current Altimeter Setting) × 1,000. When the altimeter setting is below standard (29.92), pressure altitude is higher than field elevation; when above standard, it is lower.
Density altitude is pressure altitude corrected for non-standard temperature. It represents the altitude in the standard atmosphere that has the same air density as the actual conditions. Higher density altitude means thinner air, which reduces engine power output and decreases the lift produced by the wings at a given airspeed, resulting in longer takeoff and landing distances.
Heavier aircraft require more lift to become airborne, which means a longer takeoff roll to reach the required liftoff speed. The relationship is not linear — a 10% increase in weight can increase takeoff distance by more than 10% because both the required speed and the acceleration are affected.
Headwind effectively provides “free” airspeed, reducing the ground roll needed to achieve liftoff speed. Tailwind has the opposite effect — even a small tailwind component can materially increase takeoff and landing distances. POH wind corrections are typically more aggressive for tailwind than headwind.
POH performance data is developed under controlled test conditions with a new or well-maintained aircraft, optimal pilot technique and favorable conditions. Real-world performance may differ because of aircraft condition, engine wear, propeller condition, pilot technique, runway surface irregularities, actual wind variability and other factors.
Training & Planning Aid: SkeyeMentor Performance Calculations helps pilots learn and apply aircraft performance concepts. Calculations depend on the aircraft profile, source data, assumptions, and user-entered conditions. Always verify performance using the current approved POH/AFM and records for the specific aircraft. Actual performance can vary because of aircraft condition, pilot technique, runway condition, weather, and other factors. This tool does not determine whether a flight is safe, legal, or approved.