Me 109 G Flight Tests

Messerschmitt AG.
Augsburg

Full Throttle Height
Me 109 G with DB 605 A

Test Report
Nr. 109 09 L 42
Date 16.6.42
Copy 3

Dept. Flight Testing
Group Performance

Results:

1.)

Full throttle height in high speed with combat power corrected to normal temperature.

Intake 150 Ø	20,997 ft. (6400 m))	Desired value
Intake 155 Ø	20,997 ft. (6400 m))	n Intake = 0,9
Early intake	20,505 ft. (6250 m))	22,966 ft. (7000 m)

	2.)	The total pressure at the intake entrance, ~ 50 kg/m² higher than in the free flow, is due to prop wash.
	3.)	The air temperature in the intake lies 2° above the ambient temperature. The heating thus lies within the measuring accuracy.
	4.)	The supercharger air temperature at 8 km is 92°, the desired value is 107°. (after engine manual with consideration of the ambient temperature, lay 7° over CINA, and Stauauf heating.)
		Currently, the known possible airframe-related reasons for the bad FTH have been examined and found to be in order, consisting of: 1.) Heating from exhaust gases, 2.) too narrow plenum chamber, 3.) insufficient ram in front of the intake. Apparently, however, the supercharger air temperature, ~15° too low, can be attributed to the poor static head of the supercharger.

Augsburg, den 16.6.42
FEV/EK/Go.

For the full report see:

Volldruckhöhe Me 109 G mit DB 605 A
in German (pdf) Full Throttle Height Me 109 G with
DB 605 A(Translation-html)

Messerschmitt AG.
Augsburg

Speed Measurements on
Airplanes With Specially Treated
and Standard Production Surfaces

Test Report
Nr. 109 11 L 42
Date 9.7.42
Copy 3

Dept. Flight Testing
Group Performance

Results:	Flight	V_w	V_n	V_nk	Remarks
	2	323 (520)	321 (517)	323 (520)	Paint easily cracked
	3	322 (518)	327 (526)	329 (529)	Böig
	4	319 (514)	326 (525)	328 (528)
	5	321 (517)	327 (526)	329 (529)	Wiederholung v.3
	6	323 (520)	326 (525)	328 (528)
	7	319 (514)	320 (515)	322 (518)
	8	323 (520)	322 (519)	322 (519)
	9	321 (517)	323 (520)	323 (520)
	10	321 (517)	320 (515)	322 (518)

(Speeds given in MPH, values in parenthesis in km/h)

	V_w represents the true speed on the test day at test altitude with actual engine power, while V_n represents the speed on a Normal Day at 820 ft altitude with 1,30 kg/cm² boost and 1.80 kg/cm² blower pressure. With V_nk a speed loss of 2 mph (3 km/h), caused by the radiator indicators, is taken into account.
	For average comparison values, 327 mph (527 km/h) at 820 ft altitude and 323 mph (520 km/h) at Sea Level is obtained with specially treated machines. The corresponding values of the standard production machines are 322 (519) and 318 mph (512 km/h). The speed increase thus averages 5 mph (8 km/h).

Sea level speeds after corrections: (Link to image)
	W.Nr.	V mph SL	V km/h 0m
	13438	319	513
	13439	313	504
	13440	318	512
	13442	318	512
	13448	317	510
	13496	319	514
	13506	320	515
	13500	317	510

For the full report see:

Geschwindigkeitsmessungen an
Flugzeugemit sonderbehandelten und
serienmässigenOberflächen (pdf) Speed Measurements on Airplanes With
Specially Treated and Standard
Production Surfaces (Translation)

Messerschmitt AG.
Augsburg

Me 109 G slats

Test Report
Nr. 109 10 E 42
Date 13.7.42
Copy

Dept. Flight Testing
Group Performance

Results:	For faultless opening operation the following points should be noted:
	1.)	The slat’s trailing edge must lie quite tight against the wing, it must be so stiff that it can not be lifted by air pressure.
			The slats of the 109 G do not meet this requirement properly. In addition to the fact that they are built with too much play, the rear edge is so flexible on some machines, that it is sucked out considerably. Therefore, the cover of the slats should be strengthened and special attention has to be paid to a tight contact with the trailing edge during installation.
	2.)	The slat roller track must be installed properly.
			The measurements - center connecting bolts to wing surface - must be adhered to as closely as possible. In order to ensure that the slats open early enough for even somewhat bad installations, a slight tilting of the roller tracks would be required. (For measurements see page 5).
	3.)	The slats themselves must be set up correctly.
			The tilting of the slat is to be used where possible to compensate for different opening times of the left and right slats.
	The investigations have shown that the poor opening times of the slats on the 109 G are caused by difficulties in manufacturing; when the slats are perfectly stiff and installed correctly, flawless opening operation in climb and turning flight results. Apparently, however, the supercharger air temperature, ~15° too low, can be attributed to the poor static head of the supercharger.

For the full report see:

Vorflügel 109 G (pdf)

Messerschmitt AG.
Augsburg

Speed influence of the 109 G landing gear doors

Test Report
Nr. 109 16 L 42
Date 15.8.42
Copy 2

Dept. Flight Testing
Group Performance

Results:	After adjusting an imprecision in the installation, the kinematics functioned properly. The landing gear doors were neither torn off at 650 km/h indicated airspeed, nor did any difficulties appear during retraction of the landing gear within the permissible speeds, even with the aircraft in a light slip. An estimated extra 8 - 10 seconds is needed for lowering the landing gear than in the case without landing gear doors.
	The increase in speed with the landing gear doors installed is 8 km / h (+ - 3 km / h).

For the full report see:

Geschwindigkeitseinfluß der Fahrwerkrestabdeckung 109 G (pdf) Speed influence of the 109 G landing gear doors (Translation)

Messerschmitt AG.
Augsburg

Longitudinal stability of the Me 109 G
with DB 605 A engine

Test Report
Nr. 109 14 E 42
Date 18.8.42
Copy 2

Dept. Flight Testing
Group Properties

Results:

Up to 30% t_aero, the machine was clearly stable in level flight with combat and cruise power. During climb, however, it can only be described as slightly stable or neutral. The neutral threshold for climbing with combat power can be assumed to be 30% t_aero.

For the full report see:

Längsstabilität 109 G mit DB 605 A (pdf)

Messerschmitt AG.
Augsburg

Quick test flight of the 109 G radiator

Test Report
Nr. 109 18 L 42
Date 9.9.42
Copy

Dept. Flight Testing
Group Performance

Results:	The tested radiator is sufficient at high speed flight near the ground for European summer temperature with an acceptable speed loss. However, for tropical conditions, it is completely inadequate, since the flaps open fully already at +42°, which causes a speed loss of 48 km / h. At an air temperature of +50° + 5° the coolant reaches 115°. This temperature is not permissible because high speed flight combat power can last longer than 10 min.

	Sea level speed = 313 mph (503 km/h) after corrections. (Link to image)

For the full report see:

Schnellflugmessung des Wasserkühlers 109 G (pdf) Quick test flight of the 109 G radiator (Translation)

Messerschmitt AG.
Augsburg

Performance Measurment Me 109 G
with DB 605 A and DB 601 E.

Test Report
Nr. 109 19 L 42
Date 19.9.42
Copy 3

Dept. Flight Testing
Group Performance

Results:	Speed with DB 601 E at sea level	V_o = 319 mph
	Speed with DB 605 A at sea level	V_o = 315 mph
	Speed with DB 601 E at FTH = 19,685 ft.	v = 386 mph
	Speed with DB 605 A at FTH = 20,013 ft.	v = 389 mph
	Service ceiling at 98 ft/min with DB 601 E	H = 40,354 ft.
	Service ceiling at 98 ft/min with DB 605 A	H = 41,339 ft.

	The values stated above are measured at Climb and Combat power and are converted to normal day and correct setting of the supercharger regulator.
	The influence of the radiator flap position on temperature and speed can be seen on page 9. The coolant temperatures of both measured engines are similar, i.e. any large heat removal of the DB 605 is balanced by higher air and water speed.
	Climb Performance with DB 605 A. (Link to image)
	Speed Performance with DB 605 A. (Link to image)

For the full report see:

Leistungsmessung 109 G mit DB 605 A und DB 601 E (pdf) Performance Measurments of the Me 109 G with DB 605 A and DB 601 E Engines (Translation)

Messerschmitt AG.
Augsburg

Quick test flight of the Me 109 G
with deepened radiator.

Test Report
Nr. 109 03 L 43
Date 25.2.43
Copy 3

Dept. Flight Testing
Group Performance

Results:	The deepened radiator leads to worse cooling in high speed flight than the production radiator. However, this is partly attributed to the difference, rotated - rolled. (Test Report 109 05 T 43). The speed on sheet 2 is not converted. A speed comparison with the measurements in Test Report 109 18 L 42 is not possible since the two measurements are too far apart in time. The flatter profile of the speed is due to the larger drag of the airflow through the deepened radiator.
	Influence of the radiator flap position on temperature and speed. (Link to image)

For the full report see:

Schnellflugmessung des vertieften Wasserkühlers Me 109 G (pdf) Quick test flight of the deepened radiator Me 109 G (Translation)

Messerschmitt AG.
Augsburg

Speed difference between
V and standard tail unit on ME 109 G

Test Report
Nr. 109 04 L 43
Date 22.3.43
Copy

Dept. Flight Testing
Group Performance

Results:

The test flights resulted in the values listed below in the following table:

Version	Nr.	V_w mph (km/h)	Δ V km/h
V Tail Unit	1	321 (516)	-0-
V Tail Unit	2	320 (515)	-0-
Standard Tail Unit	3	318 (512)	- 2.5
Standard Tail Unit	4	319 (514)	- 2.5


	H = 620, B = 706 m Hg, t = + 2°
	r = 1,191 kg/m³, n = 2600 rpm, p = 1.30 ata.

	All flights are converted to the values of the first flight. They are comparable only among themselves, may not thus be consulted for calculations.

Sea level speed = 314 mph (504 km/h) after corrections. (Link to image)

For the full report see:

Geschwindigkeitsunterschied zwischen V- und Normalleitwerk an Me 109 G (pdf) Speed difference between V and standard tail unit on ME 109 G (Translation)

Messerschmitt AG.
Augsburg

High speed tests with the Me 109

Test Report
Nr.109 05 E 43
Date 15.4.43
Copy 3

Dept. Flight Testing
Group Properties

Results:

Maximum values reached with an initial altitude of 35,105' (10.7 km) above sea level and a flying weight of 6,393 lbs. (2900 kg.) The dive was commenced at a horizontal speed of Va = 240 km/h and forward trimmed tailplane to +1° 15 ' by downturn and 100 % engine power. The dive angle was about 70-80° (statement of the pilot.)

	Maximum indicated airspeed:	Va_max = 458 mph (737 km/h) at 14,764' (4.5 km)
	Maximum true airspeed reached:	Vw_max = 563 mph (906 km/h) at 19,029' (5.8 km)
	Maximum Mach Number reached:	M_max = 0.805 at 22,966 (7.0 km)

Dive test true airspeeds(Link to image)
Dive test Mach Number(Link to image)

For the full report see:

Hochgeschwindigkeitsversuche mit Me 109 (pdf)

For the full report see:

Einfluss der Form der Motorhaube auf die Geschwindigkeit der Me 109 G (pdf) Influence of the engine cowling shape on the speed of the ME 109 G (Translation)

Messerschmitt AG.
Augsburg

Performance measurement ME 109 G-6
Tropical with DB 605 A; Influence
of various attachments.

Test-Report
Nr. 109 10 L 43
Date 16.6.43
Copy

Dept. Flight Testing
Group Performance

Results:	1.	Influence of the attachments.
		Level speed is reduced through:
		2 x underwing weapons	about	7 mph
		2 x ETC 50 racks	about	0 – 2 mph
		2 x 50 kg Bomb	about	4 mph
		1 Sandfilter		6 – 7 mph
		and increases through wheel covers about 6 to 7 mph. Details see page 4.

2.	Climb performance on page 6; from it:
	Ceiling :	36,516 ft.
	With take-off weight:	7,187 lbs.

3.	Level speed with combat power (fully equipped.):
	Flight height	0 ft.:	Vn_o = 304 to 306 mph
	Full throttle height	21,063 ft.:	Vn = 379 mph
	Full throttle height 21,654 ft. without Sandfilter. In fastest condition (without wing weapons, Sandfilter, with wheel covers) is V_no = 318 mph.

Results of the take-off and landing measurments, see Page 5; from it:

	S_R	S₂₀	weight
Take-off	1,407 ft.	2,247 ft.	7,297 lbs.
Landing	1,654 ft.	3,750 ft.	7,297 lbs
The indicated distances are average values from 7 take-off and landing measurements. They are not converted to zero wind.

Climb Performance (with Sandfilter) (Link to image)
Level Speed (Link to image)

For the full report see:

Leistungsmessung Me 109 G-6 Tropen mit DB 605 A; Einfluß verschiedener Anbauten (pdf) Performance measurement ME 109 G-6 Tropical with DB 605 A; Influence of various attachments (Translation)

Messerschmitt AG.
Augsburg

Speed influence of 2 MK 108
under the wings of the ME 109 G.

Test Report
Nr. 109 14 L 43
Date 12.8.43
Copy

Dept. Flight Testing
Group Performance

Results:	Speed without mockup	V_w = 326 mph (525 km/h).
	Speed with mockup	V_w = 322 mph (519 km/h)
	Speed loss due to mockups	ΔV = 4 mph (6 km/h)
	n = 2600 U/min; p – 1,30 ata; B = 717 mm Hg;
	t = 19°C; H = 480 m.

Sea level speed = 316 mph (509 km/h) after corrections. (Link to image)

For the full report see:

Geschwindigkeitseinfluß von 2 MK 108 unter den Flächen der Me 109 G. (pdf) Speed influence of 2 MK 108 under the wings of the ME 109 G (Translation)

Messerschmitt AG.
Augsburg

Drag of 160 liter external tank,
without fairing, beneath the fuselage.

Test Report
Nr. 109 15 L 43
Date 15.8.43
Copy 3

Dept. Flight Testing
Group Performance

Results:

The following values are not converted, since air conditions did not change during the test.

Condition	V mph	V/mph
Smooth machine	327	0
Mounting bracket without tank	324	- 3
Mounting Bracket with 160 l-Tank	308	-19

	B = 729 mm Hg, t = + 14 °, y = 1,179 kg/m³,
	p₄= 1,30 ata, p₂ = 1,72 ata.

	Tests with an un-faired 300 liter external tank on a Me 109 E/3 (vgl Test Report from 30.7.40) resulted, after conversion to an Me 109 G, in a speed loss of 31 km/h. This calculation is still confirmed by a test. A decrease in size of the tank thus brought no speed gain. A fairing is in the works. A significant improvement is anticipated from this measure.

Sea level speed = 314 mph (506 km/h ) after corrections. (Link to image)

For the full report see:

Widerstand des unverkleideten 160 l Außenbehälters unter dem Rumpf. (pdf) Drag of 160 liter external tank, without fairing, beneath the fuselage. (Translation)

Messerschmitt AG.
Augsburg

Performance Summary
Me 109 G

Date 14.1.44
Copy

Dept. Flight Testing
Group Performance

Description of the basic model Me 109 G 1.

Building specification:

Airframe:

Pressurized cockpit, strengthened wing (cross-beam, ribs, skin) roller-stored slats, lines for GM 1 installation in the wing and as well as fittings for long range and weapons release installations and under wing weapons; automatic water and oil coolers, oil reservoir enlarged 36 l. Rear armor and head protection, radiator armor and Leichtmetallpnzerung.

Chassis:

Tail wheel not retractable. Bumps at top surface to accomodate landing gear. Without wheel covers.

Power plant:	Engine: DB 605
	Propeller: 3 flg. VDM adjustable propeller
	Fuel tank: 400 l SG
	Oil tank: 36 l
	Oil cooler: Bauchkühler
	Radiator: 2 in wings,

Equipment:	Fuselage armament	2 MG 17
	Fuselage armament (In engine)	1 MG 151
	Surface (Fläche) armament:	without

Surface:

Standard camouflage paint. No special treatment.

Weight:

6,724 lbs.

Photographs:

Deviations from the G 1 model: air vents have been thickened and turned horizontal. The standard cockpit shown conforms to the aerodynamic form of the pressurized cabin. 4 vents for spark plug ventilation are missing. Edge caps were enlarged.

Performance:

	V_n	w
	mph	ft/min
at 0 ft.	314	3,427
at FTH	21,654 ft. 391	18,701 ft. 2,644
Ceiling	38,386 ft

Climb rate of the basic model Me 109 G. (Link to image)
Speed of the basic model Me 109 G 1. (Link to image)

For the full report see:

Leistungszusammenstellung Me 109 G. (html)

The full report is 38 pages. In order to calculate the performance of each modified version of the series, a detailed description and performance data of basic model are given. All modifications of armament, armor-plating and equipment are listed in detail, and instructions for the calculations are included. Tables and graphs show the influence of weight and of drag of exterior modifications on the performance of the Me 109 G. The data shown above is the report's summary of the 109 G-1 basic model (page 3).

Messerschmitt AG.
Augsburg

Performance of the Me 109 G with DB 605 AS.

Test Report
Nr. 109 20 L43
Date 22.1.44
Copy 4

Dept. Flight Testing
Group Performance

Result:	For comparison the corresponding performance of the Me 109 G in the same condition is shown in parentheses.
	1.) Speed at sea level	315 mph	(314)
	2.) Speed at FTH	406 mph	(391)
	3.) Full throttle height	27,231 ft.	(21,654)
	4.) Climb rate at FTH	2,350 ft/min	(2,546)
	5.) Climb full throttle height	23,950	(18,700)
	6.) Climb ceiling	39,698 ft.	(37,730)
	Performance is converted to standard temperature. Combat power without GM 1

Performance Curves. (Link to image)

For the full report see:

Leistungen Me 109 G mit DB 605 AS. (pdf) Performance of the Me 109 G with DB 605 AS. (Translation)

Messerschmitt AG.
Augsburg

Drag of the 190 liter drop tank mock-up.

Test Report
Nr.109 01 L 44
Date 7.1.44
Copy

Dept. Flight Testing
Group Performance

Result:	Aircraft with drop tank	V_w = 473 km/h
	Aircraft without drop tank	V_w = 486 km/h
		-----------------
	Aircraft without drop tank	ΔV = 13 km/h

B	=	731 mmHg
t	=	-7°C
y	=	1,275 kg/m³
n	=	2600 min^-1
p4	=	1,29 kg/cm²
p2	=	2,0 kg/cm²
N	=	1269 PS

The flight with drop tank is corrected to the flight without drop tank.

For the full report see:

Widerstand der 190 L Behälter-Attrappe (pdf)

Rechlin E'stelle
Test Nr. 1586
E.B.Nr......./43
G.Kdos.

Aircraft Model Bf 109 G-1
with DB 605 A engine

Kennblatt

Page 7

12.) Flight Performance:

Alt. ^HCINA ft. (km)	High Speed		Climb Speed V_a mph (km/h)	Time to Climb min.	Climb Rate ft/min (m/sec)
Alt. ^HCINA ft. (km)	TAS mph (km/h)	IAS mph (km/h)	Climb Speed V_a mph (km/h)	Time to Climb min.	Climb Rate ft/min (m/sec)
0	326 (525)	326 (525)	174 (280)	-	4,113 (21)
3,281 (1)	338 (544)	321 (517)	174 (280)	0⁴⁷	4,113 (21)
6,562 (2)	350 (563)	317 (510)	174 (280)	1³⁵	4,113 (21)
9,843 (3)	362 (583)	312 (502)	174 (280)	2²⁴	3,780 (19.8)
13,123 (4)	374 (602)	306 (492)	174 (280)	3¹⁶	3,643 (18.6)
16,404 (5)	386 (622)	300 (482)	174 (280)	4¹¹	3,408 (17.4)
19,685 (6)	399 (642)	292 (470)	174 (280)	5¹⁴	3,094 (15.8)
22,966 (7)	403 (649)	281 (452)	174 (280)	6²³	2,605 (13.3)
26,247 (8)	403 (648)	263 (424)	171 (275)	7⁴⁶	2,135 (10.9)
29,528 (9)	400 (643)	247 (398)	168 (270)	9³⁶	1,625 (8.3)
32,808 (10)	398 (640)	228 (367)	165 (265)	11⁵⁴	1,175 (6.0)
36,089 (11)	378 (609)	206 (332)	162 (260)	15⁴¹	685 (3.5)
39,370 (12)	345 (555)	174 (280)	158 (255)	24⁰²	196 (1.0)

The performance indicated relates to climb and combat power, i.e. n = 2600 rpm; P_Lade = 1.3 ata. Take-off and emergency power for the DB 605/A is still not released at this time.

For speed influence of bomb, drop tank and under-wing guns see range table.

	Full throttle height with full throttle level flight	20,997 ft. (6.4 km)
	Full throttle height in climb	18,701 ft. (5.7 km)
	Take-off distance to 66 ft. (20 m), normal	1,919 ft. (585 m)
	Take-off distance to 66 ft. (20 m), with bomb	2,428 ft. (740 m)
	Landing distance from 66 ft. (20 m), normal braking	2,526 ft. (770 m)

Flugzeugmuster BF 109 G-1 mit Motor DB 605A. (Link to image)

Messerschmitt Bf-109 G

Flight Tests

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See Also:

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