Data and performances

Important note: the following values are the values used for the 1% flight model of the virtual G55. The aim is to use true and accurate data and actually many of the following data belong to the real aircraft and derive from reliable sources. However, in some cases, when data were not available or sources disagree, some assumptions are made to provide the necessary data to the flight model. In these cases the data are marked in italic.
Many data are still object of research and discussion. Please, read carefully the notes.

Contents

• Dimensions and weight
• Engine specifications
• Armament, loads and other equipments
• Performances

Notes. Data about dimensions are coherent in all sources [1, 2 and 3]. The Serie I and the G56 mounted a different vertical tail that had the rudder area slightly increased. The vertical tail and rudder aereas are calculated by available drawings.
About Serie I weights, the max loaded weight and the normal loaded weight are from [2]. Another source [10] reports a slightly greater max loaded weight of 3770 Kg. The empty equipped weight is from [1] (in many photos the same value is clearly visible written on the G55 tail); the empty weight is calculated by subtracting from the empty equipped weight the weights of the equipments as defined by the 1% spreadsheet [9]; the empty equipped weight reported by [2] is slightly different, but it can be obtained as a different combination of equipments.
For the Sottoserie 0 some weight data are guessed. As for the Serie I, many Sottoserie 0 had the empty equipped weight written on the tail and is clearly visible on many photos: this value, also reported by [1] is assumed as a starting point. The very empty weight and the normal loaded weight are calculated by subtracting or adding equipments weights as they are defined by the 1% spreadsheet [9]. Another source [8] reports for the second prototype a "flying weight" of 3700 Kg, this seems high as a normal load, but is close to the max loaded weight reported for the Serie I, maybe 3700 kg can be interpreted as a possible maximum flying weight. See also the notes about armament loads.

Notes. The data for the early produced RA1050's are taken from [3]. Apart of the absence of the emergency settings, they correspond to the data of the original DB engine [6]. The early RA engines were limited to 2600 rpm due to detonation problems and piston failures. Actually, The RA was afflicted by the same problems of original DB's: both an DB605A handbook [6] (October 1942) and a manual of the Bf109G2 [7] (March 1943) reports that emergency settings were disabled. Lately the problems on German engines were solved by strengthening some parts and by the adoption of a new type of sparkplugs. A source about the RA engine itself [4] and another about the Serie I [2], report an RA engine fully capable of 2800 rpm, and [1] explicitely says that the limitation on RA engines was released in early 1944. Still we don't have a direct source (a flight manual, for instance) to confirm the operative use of the emergency settings. Moreover, a source about the G55A/B produced after the war reports as max power 1350 hp [11]. In conclusion, while it is not a confirmed fact, it can be considered plausible that in war time, during the brief operative life of the G55 in the ANR (January-July 1944), the emergency settings were available. See also the notes about performances.

Notes. Ammo loads for the Serie I are from [2]. The value for the rounds available for the nose mounted 20 mm seems high (at least if compared with similar installations), but it actually matches the normal loaded weights. Data for the Sottoserie 0 are from an evaluation report of the second prototype [8].
About the G56 the nose mounted 30 mm cannon was an option in place of the 20 mm Mauser, as reported by [1].
The fuel available for Sottoserie 0, as reported by [1] is 10 liters less than the quantity reported by [2] for Serie I. It is possible that a little more room for the fuel tank located between the wings was available when the Breda's mounted in the bottom of the forward fuselage were removed. Another source [8] reports a total of 625 liters for the second prototype. A possible explanation of the different data is that initially wing tanks were larger, but were reduced before production series foreseeing the installation of wing guns.
Tanks were selfsealing. The process used was known as SEMAPE, the duralumin tanks were covered by a layer of special rubber pressed by a layer of canvas.

Notes. The data about Serie I climb rate are from [2]. A better climb ability is reported by [1] that says 7'12" as the time to reach 7000 m. Research is on going to confirm this data.
For Sottoserie 0 many values are assumed equal to Serie I. It is worth to note that, for few performance data, [1] and [2] report the same values, but [1] with a limited RA engine and [2] assuming a full capable one.