Notes and comparison with other flight trials:


    The below papers form part of a the Rechlin state aviation test centre`s flight test results performed on a Bf 109G-1, at the start of 1943. The Bf 109G-1`s performance figures below are also valid for the late-production (ie. non-retractable tailwheel) pressurized G-3, and non-pressurized G-2 and G-4 subtypes, as they only differ in the presence of pressurized cocpit and/or radio set.

    The below figures were accepted as official performance specifications of the Bf 109G-1, and were released in an unchanged form in the Kennblatt für das Flugzeugmuster Bf 109 G-1 mit Motor DB 605A vom 8.März 1943 type datasheet in March 1943.

    The aforementioned Kennblatt notes the increased mainwheel size 660 x 160 being present from February 1943, and the increased tailwheel size 350 x 135 from January 1943, that resulted it being non-retractable and causing additional drag - equivalent of 12 km/h speed loss at Sea Level as per other Mtt documents. These changes in early 1943 were the likely reason to perform the Rechlin trials, to establish the performance under the new airframe conditions. Therefore it is believed the below figures are with non-retractable tailwheel and bulges on the wing. 
http://www.kurfurst.bravehost.com/
      This is supported by comparison with previous specifications from Datenblatt Me 109 G-1 Ausführung with the Messerschmitt's calculated performance figures for the serial production G-1 model, from 23.5.1942, at when  the retractable tailwheel was standard. The Messerschmitt Datenblatt state 537 km/h at SL (Rechlin: 525 km/h), and 660 km/h at 7km rated altitude (Rechlin: 650 km/h at 6,4 km). The difference, esp. in view the SL figures, points to non-retractable enlarged tailwheel being present on the Rechlin-tested G-1.

    Soviet trials on Bf 109G-4 WNr. 19 968 tested by the NII VVS in October 1943. The aircraft had non-retractable tailwheel and achieved 508 km/h achieved at Sea level and 650 km/h at 7 km. Another Bf 109G tested by the NII VVS, Bf 109 G-2, WNr. 14 513, but with retractable tailwheel, achieved 524 km/h achieved at Sea level and 666 km/h at 7 km. Soviet results agree well with the Rechlin figures, except for Sea level, however it is a general trend on all Soviet Bf 109 trials to show sharply recurving speed curves near ground level for some unknown reason. Bf 109 G-2 WNr. 14 783, tested in Finnland in April 1943, achieved 522 km/h at SL, and 636 km/h at 6300m altitude. Speeds achieved at altitude show a marked drop-off on this plane. Aircraft had non-retractable tailwheel. All abovementioned performance trials were performed using Steig- und Kampfleistung 30-min power (ie. 1.3ata, 2600 revs/min).
  http://www.kurfurst.bravehost.com/
    Leistung Fw 190 (Versuchs-Bericht Fr.M.01 L 43), dated 29.6.43 and prepeared by Messerschmitt A.G. Augsburg,  in June 1943, comparing the performance of the FW 190A-5 to that of the Bf 109G-1, notes that results of 13 measurements on serial production planes at Regensburg ('Messerschmitt Regensburg') and Wiener-Neustadt ('W.N.F.') Bf 109 factories underline Rechlin's data :

'Ergebnisse aus Regensburg und der Wiener-Neustadt (ca. 13 Messungen) erhärten die Rechliner Werte,
sodaß diese als maßgebend anzusehen sind. Lediglich weicht die VDH (Mittelwert 6700m) der 13 Messungen von dem Rechliner Wert ab.'

Translated to English :
'Results from Regensburg and from Wiener-Neustadt  (ca. 13 measurements) confirm the Rechlin values,
therefore these are to be to regarded as representative. Only the FTH of the 13 measurements (average : 6700m) deviates from the Rechliner values.'
http://www.kurfurst.bravehost.com/
     Similiar factory trials at the Erla factory further confirm the figures (Erflogene Geschwindigkeiten der Erla Maschinenwerke, April 1943). The avarage value of the 13 tested fighters showed 652 km/h at 6,7 km, excluding three machines that would be rejected by BAL for not meeting minimum acceptance specs (with inclusion of those 643 km/h).

The results are to be understood as without the use of GM-1 dinitrous-oxide boost for high altitudes.
     Use of GM-1 gave a very prounounced boost above 8km altitude, increasing engine output by 300 (!!) PS. Preparations for use of GM-1 were present on all G-1 and G-3 pressurized fighters; several hundred of the other 109G subtypes were converted for it's use from the factory line. To give some idea of the potential, R. Klein had achieved 680 km/h at 12 000 m and a ceiling of 13 800 m in a Bf 109G-1/R2 with GM-1 injection.




http://www.kurfurst.bravehost.com/

Rechlin E`Stelle Erprobungsnummer 1586.
1943

Flugzeugmuster Bf 109 G-1
mit Motor DB 605A


- Original page -

Flughöhe
RCINA
 Höchstgeschwindigkeit
wirklich         Anzeige		 Geschw. b. Steigens
Va
 Steigzeit
 Steiggeschw.
km
 km/h
 km/h
 km/h
 min
 m/sec
 0
 525
 525
 280
 -
 21
 1
 544
 517
 280
 047
 21
 2
 563
 510
 280
 135
 21
 3
 583
 502
 280 224
 19,8
 4
 602
 492
 280 316
 18,6
 5
 622
 482
 280 411
 17,4
 6
 642
 470
 280 514
 15,2
 7
 649
 452
 280 623
 13,3
 8
 648
 424
 275
 746
 10,9
 9
 643
 398
 270
 936
 8,3
10*
 640*
 367
 265
 1154
 6,9
11
 609
 332
 260
 1541
 3,5
12
 555
 280
 255
 2402
 1,0

Die angegebenen Leistungen beziehen sich auf Kampf- und Steigleistung, d.h. n = 2600 U/min; PLade = 1,3 ata. Start- und Notleistung ist für DB 605/A zumzeit noch nicht freigegeben.
Geschwindigkeitseinfluß von Bombe, Behälter und Flügelgondelwaffen s. Reichweitentabelle.
Volldruck-Höhe bei Vollgas-Waagerechtflug....................... 6,4 km
     "      "  im Steigflug  ................................... 5,7 km
Startstrecke   bis 20 m Höhe normal ............................ 525 m (Gras)
     "          "        "   mit Bombe ......................... 740 m   "
Landestrecke  aus 20 m Höhe normal gebremst .................... 770 m   "

http://www.kurfurst.bravehost.com/

* The speed 640 km/h at 10km  is a typo in the orignal Rechlin table, however the attached curves (below) show the speed correctly as
630 km/h at 10 km. The official Kennblatt issued as of 8 March 1943, also list correctly as 630 km/h at 10 km.


Translation

                    Flughöhe                           -   Flying altitude
Höchtsgeschwindigkeit              -   Maximum level speed
              Anzeige              -   Indicated
              Wirklich             -   True
Geschw. b. Steigens                -   Best climb speed
Steigzeit, Min.                    -   Time to climb, in Minutes
Steiggeschw. m/sec                 -   Climb rate, in meter/sec

The given performances refer to Kamp- und Steigleistung, this means
revolutions = 2600/min, manifold pressure = 1,3 ata.
The Start und Notleistung for the DB 605/A is not yet cleared.

Rated altitude at full-throttle in level flight ......... 6,4 km
  "       "            "        in climb ................ 5,7 km
Take-off run up to 20m alt.     normal .................. 525 m (on grass)
       "            "           with bomb ............... 740 m     "
Landing run from 20 m alt, normal breaking .............. 770 m     "



http://www.kurfurst.bravehost.com/




Flight performance
with Steig- u. Kampfleistung
(1.3 ata, 2600 revs/min)
http://www.kurfurst.bravehost.com/
Va = indicated airspeed (IAS)
Vw = true airspeed      (TAS)

The 3 graphs below show the distances in the abovementioned take-off/landing runs.


Same graph from a Focke-Wulf document,
comparing performance to existing and projected FW 190s.
(via G.G. Hopp)



Last updated 14 July 2006.
Work in progress.
All rights reserved.
email at : kurfurst@atw.hu
Total Site Page loads :