Wolfram|Alpha Engineering



compute airflow around a standard airfoil
NACA 0012 airfoil
specify angle of attack
NACA 3412 airfoil, 12deg


compute indicated airspeed from true airspeed
true airspeed = 550 knots, altitude = 35000 ft
compute true airspeed from impact pressure
compute true airspeed given p0=22inHg, 20000ft
compute true airspeed given Mach number
Mach 0.7 @ 45,000ft


calculate straight-line distance to an airplane
slant range to aircraft 40deg, altitude=35000ft
adjust one of the parameters interactively
slant range to aircraft, look angle=20 deg