Daimler Benz DB 601A-1
last updated 16 February 2013
I. Datasheets
Increasing the revs of the engine types DB 601A and
601N in the Me 109, 14 November 1940.
Further increasing the revs of the engine types DB
601A
This paper is a later DB 601A-1 datasheet via Messerschmitt AG, Augsburg dated
25 July 1941. Of special interests is that the paper notes a further increase in
permissable RPM: by July 1941 the latest, up to 2800 rpm is possible above rated
altitude, as opposed to the 2600 rpm mentioned in the previous paper.
Furthermore the increased RPM was by now obtainable with automatic RPM control
(i.e. the automatic propeller pitch control or "Verstellautomatik") as opposed
to the previously used manual override/pitch control.
Liquid cooled four-stroke Otto engine with direct fuel
injection DB 601A/B. type 1.
1, Description:
12-cylinder inverted Vee-engine
Volume 33,93 liter, Fuel 87
octane
Propeller driven by reduction gear, flange shaft, 180 dimater
Reduction gear ratio for 601 A: 1,55 : 1
601 B: 1,88 : 1
Rotation of the propller: left (seen from the
power transition side DIN 9001)
Single stage supercharger with stageless, controllable supercharger drive
Mechanical mixture enrichment at 1' (110%) output
2. Dimensions:
Lenght 1852 mm from the propeller flange shaft to and
including the electric starter
1722 mm from the propeller flange shaft to the
rear of the supercharger housing
Width 739 mm
Height 1027 mm
3. Weight:
RLM unit weight:
610 kg + 3%
(without clearance)
4. Performance, revolutions,
fuel consumption, flying altitude:
Near ground level: PS
revs/min gr/PSh
0 km
Incr. brief output (1') 1100
2400 250/270
0 km
Brief output (5') 990
2400 220/232
0 km
Incr. cont. output (30') 910
2300 220/232
0 km
Max. cont. output 810
2200 220/232
Near rated altiude: PS
revs/min gr/PSh
4.5 km
Brief output (5') 1020
2400 incre- 220/232
sable to 2800
4.5 km
Incr. cont. output (30') 960
2300 220/232
5.0 km
Incr. cont. output (30') 960
2400 220/232
4.88 km Max.
cont. output 860
2200 220/232
5.7 km
Max. cont. output 890
2400 230/242
5.5 km
Cruising output ~ 800
2200 210/222
Barometric control of the supercharger RPM from 2.1 km
5.Heat dissipation: Coolant heat ~ 305 kcal/PSh
at rated altitude at 2400n (5'-rat.)
Lubricant heat ~28 "" near ground level at
2400n (5'-rat.)
Lubricant heat ~24.5 "" at rated altitude at 2400n
(5'-rat.)
6. Propeller:
VDM propeller w. external pitch mechanism and control unit,
Installation of the electro-mechanical automatic pitch control is possible.
7. Weapons:
2 connector for single or double forks; Installation of engine
cannon ispossible.
8. Fuel system:
Seperate fuel pumps in the machinery section
9. Coolant system: Closed (max. 0.75 atü)
coolant cross-circulation with coolant
tank in the main or aux. electric circuit
10. Sparkplugs: Normal
11: Misc:
Output figures are understood for
The 2800 rpm is to be flown only with Automatic override ON
and above the rated altitude
12. Development: In serial
production.
II. Power output and fuel consumption
Source: Betriebs- und Wartungsvorschrift zum Mercedes-Benz Flugmotor DB 601 A u.
B, Ausgabe C, Oktober 1940.
Daimler-Benz Aktiengesellschaft, Stuttgart-Untertürkheim.
III. Power output curves
Power curve for DB 601A-1 with early type supercharger with 4 km rated altitude:
Power curve for DB 601A-1 with new type supercharger with 4,5 km rated altitude:
Source: Betriebs- und Wartungsvorschrift zum Mercedes-Benz Flugmotor DB 601 A u.
B, Ausgabe C, Oktober 1940.
Daimler-Benz Aktiengesellschaft, Stuttgart-Untertürkheim.
Power curve for DB 601A-1 with new type supercharger with 4,5 km rated altitude,
showing rammed power of 0 to 1200 kg/sq.m and specific fuel consumption:
Source: Daimler-Benz Aktiengesellschaft, curve no. 9-601-2213, 12 August 1940.
Messerschmitt Aktiengesellschaft, Augsburg.
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