Aviation Flight Calculators
Quick-reference tools for flight planning and airwork calculations
Flight planning reference →Inputs
Use planned groundspeed and a consistent fuel burn rate. Enter positive distance, speed and burn; extra fuel must be 0–100%. This simplified estimate does not determine legal reserves.
Results
A dash means an input is missing or outside the supported range.
Calculation notes updated 1 October 2026. ETA uses a steady-wind triangle with true wind/track directions; leave wind speed empty only to assume calm. Density altitude uses an approximation (pressure altitude −2,000 to 20,000 ft; temperature −80 to 60°C).
Study sources: FAA Pilot’s Handbook · Explore the wind triangle
Understand the result
Fuel uses groundspeed
A 120 nm segment at 100 kt takes 1.2 hours. At 30 litres per hour it uses 36 litres. Adding 25% produces 45 litres for that arithmetic example. It does not establish a legal or sufficient fuel load: required allowances depend on the operation, jurisdiction and aircraft.
ETA includes crosswind correction
To hold a track, some airspeed counters sideways drift. With 100 kt true airspeed and a direct 20 kt crosswind, groundspeed is about 98 kt, not 100 kt. With a direct 20 kt headwind it is 80 kt. A wind that prevents forward progress produces no ETA.
Wind components have a reference
With wind from 280° at 20 kt and runway direction 240°, both measured from the same north reference, the headwind is 15.3 kt and the crosswind is 12.9 kt from the right. A runway number is rounded; use the published direction for precision.
Density altitude is an approximation
At pressure altitude 3,000 ft, the approximate standard temperature is 9°C. At 29°C, the 20°C difference adds about 2,400 ft: density altitude approximately 5,400 ft. The result is an input to aircraft performance assessment, not a takeoff-distance calculation.