DA-40
Performance Calculator
DIAMOND DA40 · IO-360-M1A · G1000 NXi
AFM 6.01.01-E REV 10 SEC 5.3 BUILD v6.1

⟶ ATMOSPHERIC INPUT

STEP 01
Source · METAR
Paste raw METAR from ForeFlight / AWC / SkyVector · auto-parses
ICAO auto-fetch
— paste METAR above, or fetch by ICAO —
Or · Manual Entry
Field Elev ft
Altimeter inHg
OAT at Field
Wind ddd/ss[Gss]
Cruise Plan
Cruise Alt MSL · ft
Course/Track ° true
Computed Atmosphere
Field PA
—ft
Field DA
—ft
ISA Dev
—°C
Cruise PA
—ft
Cruise DA
—ft
Cruise OAT
—°C
Head/Tail
—kt
Crosswind
—kt
Aircraft Mass
Flight Mass
1050kg 2315 lb
850900950 100010501100 1150↑1200
kg
lb
✓ Normal Category · within Utility
Flight Profile
Climb Mode
Cruise % Power
Cruise RPM
Mixture
Glidepath ° (3.0 ILS std)
Descent Speed
Descent FF gph
▸ Data sources & interpolation methods
• 5.3.2 Engine Performance · full MP + FF table transcribed literally
• 5.3.1 IAS/CAS · digitized from chart Flaps UP/T/O/LDG curves
• 5.3.7 Take-off Climb · chart digitized at PA 0/2k/4k/6k/8k/10k + OAT grid
• 5.3.8 Cruise Climb · chart digitized same grid
• 5.3.9 Cruising TAS · chart digitized at DA 0/2/4/6/8/10k × Power%
• Mass scaling · linear from chart mass-correction nomograph
• ISA temp correction · ±3% per ±15°C (AFM 5.3.2 note)
• Density alt · σ = (1−6.876e-6·DA)^4.2561
Bilinear interpolation between grid points.
Source · DA 40-180 AFM Doc. # 6.01.01-E Rev. 10 · 18-Sep-2023

⟶ PERFORMANCE OUTPUT

STEP 02
◀ CLIMB
CRUISE CLIMB · 73 KIAS · Flaps UP
Climb TAS
AFM 5.3.1 · IAS→CAS→TAS
—kt
Climb Fuel Flow
2400 RPM Full Throttle · sim: 13.6 @ PA 4500 anchor
—gph
Climb Rate
AFM 5.3.7 or 5.3.8 · at midpoint PA/OAT
—fpm
Ground Speed
—kt
Time to Climb
—min
Distance
—NM
◀ CRUISE
55% · 2400 RPM · Best Econ
Cruise TAS
AFM 5.3.9 · at cruise DA
—kt
Cruise Fuel Flow
AFM 5.3.2 · ISA temp corrected
—gph
Manifold Pressure
AFM 5.3.2 · at cruise PA
—inHg
Ground Speed
—kt
◀ DESCENT
Flaps UP · 3.0° glidepath · cruise → field
Descent TAS
AFM 5.3.1 · at midpoint DA
—kt
Descent Fuel Flow
User input · low cruise / partial throttle
—gph
Descent Rate
ROD = GS × (6076.12/60) × tan(γ) · γ=3.0°
—fpm
Ground Speed
—kt
Time to Descend
—min
TOD from Field
—NM
◀ TAKE-OFF DISTANCE
MAX PWR · 2700 RPM · Flaps T/O · paved dry
Ground Roll
AFM 5.3.6 · at field PA/OAT · mass + wind corrected
—ft
50 ft Obstacle
AFM 5.3.6 · ground roll × 1.77
—ft
◀ LANDING DISTANCE
IDLE · HIGH RPM · paved dry
Ground Roll
AFM 5.3.10 · at field PA/OAT · mass + wind corrected
—ft
50 ft Obstacle
AFM 5.3.10 · ground roll × 2.13
—ft
▸ FOREFLIGHT PERFORMANCE PROFILE
Clb TAS
—
Clb FF
—
Clb FPM
—
Crz TAS
—
Crz FF
—
Des TAS
—
Des FF
—
Des FPM
—
⚠ Planning reference only. Bilinear chart interpolation; always cross-check with the AFM chart in the aircraft before flight. Performance assumes good aircraft/engine condition and ISA deviations within ±30°C. Wheel fairings assumed installed (−5% TAS if removed per AFM 5.3.9 caution).