Performance Landing Calculator

Landing ground roll and total distance corrected for density altitude, weight, wind, and runway condition.

Field elevation (ft)

Outside air temp (°C)

Altimeter (inHg)

Landing weight (lb)

POH reference weight (lb)

POH ground roll (ft)

POH total distance (ft)

Headwind (kts, neg=tail)

Runway (0=dry,1=wet,2=grass)

Runway gradient (%)

Vref (KIAS)

Tab to move between fields

Ground roll (ft)

650

Total over 50 ft (ft)

1,596

Factored distance (ft)2,665

Density altitude (ft)7,400

Pressure altitude (ft)5,000

Adjusted Vref (KIAS)60.4

Weight factor0.86

Wind factor1

How to Use This Calculator

Enter field elevation (ft), outside air temperature (°C), and current altimeter setting (inHg).
Set actual landing weight (lb) and the POH reference weight and ground roll distance.
Review density altitude, pressure altitude, corrected ground roll (ft), and total landing distance over 50 ft.
Compare factored landing distance to available runway length — use a 1.67 factor for wet or contaminated runways.

How the result changes with Altimeter (inHg)

Field elevation (ft): Airport elevation above MSL.
Outside air temp (°C): Actual outside air temperature.
Altimeter (inHg): Current altimeter setting.
Landing weight (lb): Aircraft weight at landing.
POH reference weight (lb): Reference weight from POH landing charts.
POH ground roll (ft): Ground roll from POH at SL, std day, calm wind.
POH total distance (ft): Total distance over 50-ft obstacle from POH.
Headwind (kts, neg=tail): Headwind component. Negative for tailwind.
Runway (0=dry,1=wet,2=grass): 0 = dry paved, 1 = wet paved (+15%), 2 = grass (+45%).
Runway gradient (%): Positive = uphill (shorter landing); negative = downhill.
Vref (KIAS): Reference approach speed at max gross weight.

Ground roll (ft): Estimated landing ground roll.
Total over 50 ft (ft): Total distance from 50-ft obstacle to stop.
Factored distance (ft): Total distance × 1.67 safety factor per AC 91-79A.
Density altitude (ft): Effective altitude for performance.
Pressure altitude (ft): Field elevation corrected for non-standard pressure.
Adjusted Vref (KIAS): Approach speed adjusted for actual weight.
Weight factor: Weight correction multiplier.
Wind factor: Wind correction multiplier.

Identify Input Parameters
4 parameters
Field elevation (ft) = 5000, Outside air temp (°C) = 25, Altimeter (inHg) = 29.92, Landing weight (lb) = 2200 = 11 input(s) provided
Calculate Ground roll
Ground roll = refGroundRollFt * daFactor * weightFactor * windFactor * conditionFactor * gr...
650 = 650
Calculate Total over 50 ft
Total over 50 ft = refTotalDistFt * daFactor * weightFactor * windFactor * conditionFactor
1596 = 1596
Calculate Factored distance
Factored distance = totalDistance * 1.67
2665 = 2665
Calculate Density altitude
Density altitude = pressureAltitude + 120 * tempDeviation
7400 = 7400