Me 109 G Flight Testing

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 Ø20,997 ft. (6400 m))Desired value
Intake 155 Ø20,997 ft. (6400 m))n Intake = 0,9
Early intake20,505 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 (pdf)
Volldruckhöhe Me 109 G mit DB 605 A (html)
Full Throttle Height Me 109 G with DB 605 A (Translation)
 

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:FlightVwVnVnkRemarks
    2323  (520)321  (517)323  (520)Paint easily cracked
    3322  (518)327  (526)329  (529)Böig
    4319  (514)326  (525)328  (528)
    5321  (517)327  (526)329  (529)Wiederholung v.3
    6323  (520)326  (525)328  (528)
 
    7319  (514)320  (515)322  (518)
    8323  (520)322  (519)322  (519)
    9321  (517)323  (520)323  (520)
  10321  (517)320  (515)322  (518)
 
  (Speeds given in MPH, values in parenthesis in km/h)

  Vw represents the true speed on the test day at test altitude with actual engine power, while Vn 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 Vnk 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:
 
  W.Nr.V mph SLV km/h 0m
13438319513
13439313504
13440318512
13442318512
13448317510
13496319514
13506320515
13500317510

For the full report see:
 
Geschwindigkeitsmessungen an Flugzeuge mit sonderbehandelten und serienmässigen Oberflächen (pdf)
Geschwindigkeitsmessungen an Flugzeuge mit sonderbehandelten und serienmässigen Oberflächen (html)
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 Properties

 
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.
 
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)
Geschwindigkeitseinfluß der Fahrwerkrestabdeckung 109 G (html)
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% taero, 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% taero.
 
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.
 
For the full report see:
Schnellflugmessung des Wasserkühlers 109 G (pdf)
Schnellflugmessung des Wasserkühlers 109 G (html)
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 levelVo   =   319 mph
Speed with DB 605 A at sea level Vo   =   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 EH     =   40,354 ft.
Service ceiling at 98 ft/min with DB 605 AH     =   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
Speed Performance with DB 605 A

For the full report see:

Leistungsmessung 109 G mit DB 605 A und DB 601 E (pdf)
Leistungsmessung 109 G mit DB 605 A und DB 601 E (html)
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
 
For the full report see:
Schnellflugmessung des vertieften Wasserkühlers Me 109 G (pdf)
Schnellflugmessung des vertieften Wasserkühlers Me 109 G (html)
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

 
ResultsThe test flights resulted in the values listed below in the following table:
 
  VersionNr.Vw mph (km/h)Δ V km/h
  V Tail Unit1321 (516)-0-
2320 (515) 
  Standard Tail Unit3318 (512)- 2.5
4319 (514) 

 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.
 
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:Vamax  = 458 mph (737 km/h) at 14,764' (4.5 km)
 Maximum true airspeed reached:Vwmax = 563 mph (906 km/h) at 19,029' (5.8 km)
 Maximum Mach Number reached: Mmax   = 0.805 at 22,966 (7.0 km)

Dive test true airspeeds
Dive test Mach Number
 
For the full report see:
Hochgeschwindigkeitsversuche mit Me 109 (pdf)
 
See also:
Dive flight from Bf 109 G-2, G-4, G-6 Bedienungsvorschrift, page 26
Dive speed limitations from Technical Instructions of the Generalluftzeugmeister
Vorläufige Fluggenehmigung BF 109 G-6
 

Messerschmitt AG.
Augsburg		Influence of the engine cowling
shape on the speed of the ME 109 G		 Test Report
 Nr. 109 06 L 43
 Date 22.4.43
 Copy
 Dept. Flight Testing
 Group  Performance

 
Results:1.Standard production 109 G – engine cowling: Vno = 306 mph (492 km/h)
 
 2.Standard production 109 G – engine cowling with double
bumps for MG 131: Vno = 300 mph (483 km/h)
 
 3.Enlarged, faired engine cowling Vno = 304 mph (489 km/h)

Sea level speed = 309 mph (498 km/h) after corrections.
 
For the full report see:
 
Einfluss der Form der Motorhaube auf die Geschwindigkeit der Me 109 G (pdf)
Einfluss der Form der Motorhaube auf die Geschwindigkeit der Me 109 G (html)
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 weaponsabout       7 mph
2 x ETC 50 racksabout0 – 2 mph
2 x 50 kg Bombabout      4 mph    
1 Sandfilter6 – 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.:Vno  =   304 to 306 mph
Full throttle height21,063 ft.:Vn    =   379 mph
Full throttle height 21,654 ft. without Sandfilter. In fastest condition (without wing weapons, Sandfilter, with wheel covers) is Vno = 318 mph.

 4.Results of the take-off and landing measurments, see Page 5; from it:
SRS20weight
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)
Level Speed
 

For the full report see:

Leistungsmessung Me 109 G-6 Tropen mit DB 605 A; Einfluß verschiedener Anbauten. (pdf)
Leistungsmessung Me 109 G-6 Tropen mit DB 605 A; Einfluß verschiedener Anbauten. (html)
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 mockupVw = 326 mph   (525 km/h)
 
 Speed with mockupVw = 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.
 
For the full report see:
Geschwindigkeitseinfluß von 2 MK 108 unter den Flächen der Me 109 G. (pdf)
Geschwindigkeitseinfluß von 2 MK 108 unter den Flächen der Me 109 G. (html)
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.

      ConditionV 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.
 
For the full report see:
 
Widerstand des unverkleideten 160 l Außenbehälters unter dem Rumpf. (pdf)
Widerstand des unverkleideten 160 l Außenbehälters unter dem Rumpf. (html)
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 armament2 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:

 Vnw
 mphft/min
    at 0 ft.3143,427
    at FTH21,654 ft.
391		18,701 ft.
2,644
    Ceiling38,386 ft

 

Climb rate of the basic model Me 109 G
Speed of the basic model Me 109 G 1

See also:

Leistungszusammenstellung Me 109 G

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

For the full report see:

Leistungen Me 109 G mit DB 605 AS (pdf)
Leistungen Me 109 G mit DB 605 AS (html))
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

 
Results: Aircraft with drop tankVw = 473 km/h
Aircraft without drop tankVw = 486 km/h
-----------------
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 SpeedClimb Speed
Va
mph (km/h)		Time to Climb
min.		Climb Rate
ft/min (m/sec)
TAS
mph (km/h)		IAS
mph (km/h)
0326   (525)326   (525)174   (280)-4,113   (21)  
3,281   (1)338   (544)321   (517)174   (280)0474,113   (21)  
6,562   (2)350   (563)317   (510)174   (280)1354,113   (21)  
9,843   (3)362   (583)312   (502)174   (280)2243,780   (19.8)
13,123   (4)  374   (602)306   (492)174   (280)3163,643   (18.6)
16,404   (5)  386   (622)300   (482)174   (280)4113,408   (17.4)
19,685   (6)  399   (642)292   (470)174   (280)5143,094   (15.8)
22,966   (7)  403   (649)281   (452)174   (280)6232,605   (13.3)
26,247   (8)  403   (648)263   (424)171   (275)7462,135   (10.9)
29,528   (9)  400   (643)247   (398)168   (270)9361,625   (8.3)
  32,808   (10)  398   (640)228   (367)165   (265)11541,175   (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; PLade = 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 flight20,997 ft.  (6.4 km)
Full throttle height in climb18,701 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
 

VB-109-06-L-42, Geschwindigkeiteinfluss der Kühlerklappenstellung bei F- Kinematik
VB-109-15-L-42, Widerstand des Wasser- und Ölkühlers an Me 109 G
VB-109-08-L-43, Einflüsse verschiedener Anbauten auf die Horizontalgeschwindigkeit der Me 109 G
VB-8-18-205-001, Einfluß der Wasserkühlerklappenstellung auf die Flugleistungen der Me 109 G mit DB 605 AS
Versuch Nr: 10 18 105 428
VB Fr.M.01 L 43, Leistung Fw 190 (Vergleich Fw 190 - Me 109 G-1)
Flugbericht M 44/33 Me 109 G, W.Nr. 18550
Mtt Erla Me 109 G
Me 109 G-2 Finnish Curves
Russian report on Me 109 G-2 No. 14513
Немецкие самолет: Мессершмитт Ме-109 Г-2
M.E. 109 G-2. Summary of Technical Trials carried out in Middle East
Pilot’s Comments on ME 109G, AAF No. EB-102
Tactical Trials - Me.109G-6/U-2
Me 109 G-6, G-6/AS, G-6/U4: GL/C-E 2, 13 August 1944
GL/C-E2 Flugzeug-Entwicklungs-Blatt: BF 109 G-5, G-6, G-6/AS
Bf 109 G-6/DB 605A level speed curves with combat and emergency power
Level Speeds with MW50, Me 109 GJ+FX with DB605 A-S
Drag Analysis of an Me 109 G, Dr.-Ing S. F. Hoerner
R.L.M. message GL/C-TT No.1374/42 of 12.6.42 as translated by British Air Intellegence.
Bf109 G-2 mit Motor DB 605 Bedienungsvorschrift-F1 Juni 1942     Page 15
Bf109 G-2 Bedienungsvorschrift-F1 Juli 1942
DB 605 A-B Moteren-Karte 9 October 1942
Bf 109 G-2 Meßrief - 8.9.1942
Bf 109 G-4 Meßrief
Bf 109 G-6 Meßrief - 8.4.1943
Bf 109 G-2, G-4, G-6 Bedienungsvorschrift-F1 Ausgabe Juni 1943     Page 12
Bf 109 G-2 Flugzeug-Handbuch Ausgabe Oktober 1943
Bf 109 G-4/R3, G-6/R3 Bedienungsvorschrift-F1 Ausgabe Februar 1944
Dive flight from Bf 109 G-2, G-4, G-6 Bedienungsvorschrift, page 26
Dive speed limitations from Technical Instructions of the Generalluftzeugmeister
Vorläufige Fluggenehmigung BF 109 G-6

WWII Aircraft Performance