ACDS — Aircraft Conceptual Design System

ACDS

AIRCRAFT CONCEPTUAL DESIGN SYSTEM

DERIVEDDERIVED — equations

ESTIMATEDESTIMATED — assumptions

INPUTINPUT — user value

click row to reveal equation

Atmosphere at Cruise Altitude

Air Density ρDERIVED0.9629kg/m³

Outside Air Temp (OAT)DERIVED-0.8°C

Speed of Sound aDERIVED330.8m/s

Weight Breakdown

MTOW—

Empty Weight We—

Payload Wp—

Empty Fraction We/W₀—

Payload Fraction Wp/W₀—

Fuel / Energy Mass—

Wing Geometry & Aerodynamics

Wing Area S—

Wing Loading W/S—

Wing Loading W/S (SI)—

Wingspan b—

Aspect Ratio AR—

Oswald Efficiency e—

Zero-Lift Drag CD₀—

CLmax—

Best-Efficiency CL*—

Maximum L/D—

Stall Speed (SL)—

Stall Speed (cruise alt)—

Cruise Performance

Mach Number—

CL at Cruise—

CD at Cruise—

L/D at Cruise—

Cruise Drag D—

Propulsion Sizing

T/W Ratio—

Thrust Available—

Thrust Required—

Power Required—

Power / Weight—

Propulsive Efficiency η—

Climb & Field Performance

Rate of Climb—

Rate of Climb (SI)—

Climb Gradient γ—

Ground Roll (simplified)—

Ground Roll (metric)—

Liftoff Speed V_LOFDERIVED—

Range & Endurance

Range—

Range (statute miles)—

Endurance—

Diagnostics (1)

Enter MTOW, or any two of: empty weight / payload.

MTOW—

V_CRS—

ALT8000 ft

RANGE—

T/W—

L/D—

ROC—

MACH—

ACDS v1.0 · ISA 1975 · Raymer / Roskam / Breguet methods · 79/79 tests passing