A practical takeoff distance calculator and landing distance calculator for GA pilots — a complete takeoff performance calculator with Koch-chart corrections for density altitude, weight, wind, grass and slope, ground roll + 50-ft obstacle splits, a runway required-vs-available verdict, and an accelerate-stop estimator — with Cessna 172, Cessna 152, Piper Warrior and Cirrus SR22 presets.
Ground roll and total distance over a 50-ft obstacle, corrected for weight, density altitude, wind, runway surface, slope and technique (Koch-style rule-of-thumb stack).
| Correction factor | Multiplier | Running total |
|---|
Ground roll and total over a 50-ft obstacle, corrected for weight, density altitude (verified within ~2% against the Cessna 152 POH landing chart), wind, surface and slope.
| Correction factor | Multiplier | Running total |
|---|
The classic FAA Koch chart as an interactive plot: pressure altitude and temperature drive density altitude; weight follows the square law; wind and grass add their POH correction notes. Move the sliders and watch the correction factor move along the chart.
Compare what the airplane needs (with your chosen safety margin) against the runway you actually have. Pull the latest takeoff/landing estimate or type a number from your POH.
Distance to accelerate to rotation speed (from your takeoff-tab ground roll), recognize the problem (2 s at Vr), then brake to a stop. Uses typical GA braking coefficients — a planning estimate.
| Segment | Distance |
|---|
Baselines are sea-level, standard-day, max-gross, short-field-technique figures. [POH] = verified against the published POH; [MFR] = manufacturer spec sheet; [REP] = representative published figure — confirm with your POH.
Enter your own POH sea-level/standard-day numbers — the estimators will use them exactly like a preset.
This takeoff landing distance calculator shows how to calculate takeoff distance the way pilots are taught: start from a POH baseline, then apply the classic correction stack. The take off distance formula used here is: baseline × (weight ratio)² × (1 + 10% per 1,000 ft of density altitude) × wind factor × surface factor × slope factor. Landing uses the same stack with the air-density (1/σ) rule instead of the Koch altitude line. All distances are ground roll plus the segment to clear a 50 foot obstacle.
| Factor | Takeoff | Landing | Source |
|---|---|---|---|
| Weight | × (W ÷ Wref)² — a 10% weight increase adds 21% distance | Koch chart (FAA AC 90-14) | |
| Density altitude | × (1 + 10% per 1,000 ft DA) | × 1/σ (air-density ratio) — matches the C152 POH landing chart within ~2% | Koch chart; FAA PHAK |
| Wind | −10% per 9 kt headwind; +10% per 2 kt tailwind (capped +50%) | Cessna 172S POH §5 notes | |
| Surface (takeoff) | dry grass +15%, wet grass +30%, soft +25% of ground roll | — | C172S POH §5 (dry grass); FAA Koch material (wet) |
| Surface (landing) | — | dry grass +45%, wet grass +60% of ground roll | C172S POH §5 (dry grass) |
| Slope | +5% per 1% upslope | −5% per 1% upslope | Typical light-aircraft AFM correction |
Pressure altitude comes from field elevation and altimeter setting (PA = elev + 1,000 × (29.92 − QNH)); density altitude adds the temperature effect (DA = PA + 120 × (OAT − ISA temp)). ISA temperature is 15°C at sea level, falling 1.98°C per 1,000 ft. These are the standard FAA PHAK formulas.
| Aircraft | Takeoff roll / 50 ft | Landing roll / 50 ft | Basis |
|---|---|---|---|
| Cessna 172S Skyhawk | 960 / 1,630 ft | 575 / 1,335 ft | C172S POH performance specs [POH] |
| Cessna 152 | 725 / 1,340 ft | 475 / 1,200 ft | C152 POH performance specs [POH] |
| Piper PA-28-161 Warrior II | 900 / 1,600 ft | 610 / 1,080 ft | Representative published figures [REP] |
| Cirrus SR22 | 1,082 / 1,868 ft | 1,178 / 2,340 ft | Manufacturer specifications [MFR] |
Presets are starting points for study and what-if planning. Your airplane's serial-specific POH/AFM is authoritative — especially for the [REP] figures.
2,400 lb, pressure altitude 2,000 ft, OAT 20°C, 9 kt headwind, paved, level, short-field technique. Density altitude = 2,000 + 120 × (20 − 11.0) ≈ 3,075 ft. Factors: weight 0.886 × DA 1.308 × wind 0.90 = 1.042. Ground roll: 960 × 1.042 ≈ 1,001 ft; over the 50-ft obstacle: 1,630 × 1.042 ≈ 1,699 ft. Try it in the Takeoff tab — you should get the same numbers.
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