Introduction.

                These trials have been made during the period August 18th to December 12th 1938. Speed trials were made with Spitfire K.9788 to determine wheter there was any reduction of speed due to fitting flash eliminators on the guns. No difference in speed could be measured when the guns were fitted with the flash eliminators, four of which protruded in front of the leading edge, or muzzle caps all of which were inside the wing. The speeds measured during these trials confirmed exactly the speeds given in this report. All speed trials were made with the gun channels open and guns in position.

Results of Trials.

                A comparison is made in the table below between this production aeroplane and the prototype K.5054.

  Prototype
K.5054
Production
K.9787
 Maximum speed349 at 16800362 at 18,500 ft.
 Maximum cruising speed (at 15,000 ft.)    311 m.p.h.    318 m.p.h.
 Time to 15,000 ft.   5.7 mins.   6.5 mins.
 Time to 30,000 ft.17.0 mins22.4 mins
 Service ceiling35,400 ft.31,900 ft.
 Weight5332 lb.5819 lb.

Night Flying.

                It is considered that the exhaust manifolds tested are unsuitable.


SUMMARY OF TRIALS

AEROPLANESpitfireNo. K.9787
SPEC. NO.16/36
CONTRACTORSupermarine Aviation Works (Vickers) Ltd.

TYPELandplaneDUTY    Fighter.
 
ENGINES.Merlin IINormal B.H.P    966 at Rated Altitude 12,250 ft
 
At     2,600     R.P.M.    

 lb.
Tare weight4482
Weight light4246
Fixed military load  236
Service Load  658
Fuel   84   gallons*  630
Oil    5½    49
Flying weight on trials.5819

* Based on 7.5 lb. per gallon.

At Full Throttle
Height
Feet
Top
Speed
M.P.H.
Time
To
Climb
Mins.
Rate
of
Climb
Ft./Min.
    S.L.  2090
    2,0002951.02195
    5,0003072.32295
  10,0003284.32490
  15,0003486.52062
  20,0003609.41480
  25,00034913.6    900
  30,00031522.4    325

Service Ceiling31,900 ft.Landing speed         M.P.H./Kts.
Take off run420 yds.   Time   secs.Distance from rest to clear 50 ft. screen 720 yards
Stalling speed             M.P.H./Kts.Gliding in A.S.I.80    M.P.H./Kts.
Best landing A.S.I.60    M.P.H./Kts.
 
Landing and take off tests corrected to zero wind.


CLIMBING TRIALS

Height in
Standard
Atmosphere
Feet
Time
From
Start
Min.
Rate
of
Climb
Ft./Min.
True
Air
Speed
M.P.H.
A.S.I.
M.P.H.
P.E.C.Comp.R.P.M.Boost
lb.sq.in.
Sea Level02090171.5174.5-2.8 2095+6.4
  1,0000.52130174   174.5-2.8-2130+6.4
  2,0001.02195176.5174.5-2.8-0.12165+6.4
  3,0001.42215179.5174.5-2.8-0.12200+6.4
  5,0002.32295185   174.5-2.8-0.22270+6.4
  6,5003.02355189   174.5-2.8-0.32320+6.4
10,0004.32490199.5174.5-2.8-0.62440+6.4
13,0005.52300207   172.5-2.5-0.72475  +4.45
15,0006.52065208.5168.0-1.8-0.82465+2.8
16,5007.21890210   164.5-1.3-0.82460  +1.75
18,0008.11710211.5161.0-0.7-0.92455+0.8
20,0009.41480213.5157.00-1.02440-0.4
23,00011.7  1135216.5150.0+1.1-1.12420-2.0
26,00014.8    790220   143.5+2.3-1.12390-3.4
28,00017.8    555222   139.0+3.1-1.22365-
30,00022.4    325225   135.0+3.9-1.22345-
32,00032.9      95227   130.5+4.8-1.32315-
 
  11,000*4.82530202.5174.5-2.8-0.624756.4
    31,900**31.7    100227   130.5+4.8-1.32315-

Estimated absolute ceiling         32,800Greatest height reached      32,400
R.P.M. stationary on ground     2175Boost pressure lb./sq.in.    +6½
* Full throttle height
** Service ceiling   


SPEED TRIALS

Height in
Standard
Atmosphere
Feet
True
Air
Speed
M.P.H.
A.S.I.
M.P.H.
Compressibility and
Position
Error
Correction
M.P.H.
R.P.M.Boost
lb/sq.in.
True Air
Speed at
Normal
Revs.
P.E.C.Comp.
Sea Level        
  1,000291   295   -8.5-0.22335+6.4 
  2,000295   295.5-8.5-0.42370+6.4 
  3,000299   295   -8.5-0.52400+6.4 
  5,000307   294.5-8.5-1.02475+6.4 
  6,500313   294   -8.5-1.52530+6.4 
10,000328   292   -8.5-2.22650+6.4320   
13,000340   289.5-8.5-3.02755+6.4319   
15,000348.5288.5-8.5-3.52820+6.4318   
16,500355   287   -8.5-4.02875+6.4317.5
18,000361   285.5-8.5-4.52930+6.4316   
20,000360.5276.5-8.5-4.82940+5.1315   
23,000355   259.5-8.5-5.02920+2.6313   
26,000345   240   -8.2-4.92855+0.1310   
28,000333.5223.5-7.5-4.52780-1.5308   
30,000315   202   -6.0-3.82660-3.1306   
  18,500*362.5284.5-8.5-4.72945+6.4316   

Landing and take off tests corrected to standard atmosphere and zero wind
Take off run       420     yds.
Distance from rest to clear       50     foot screen       720 yds.
Gliding in A.S.I.     80     M.P.H.Stalling speed       -     M.P.H.
Best landing A.S.I.     60     M.P.H.
Distance to rest (with brakes) after passing over 50 ft. screen     -     yds.
Landing run with brakes     380     yds.Landing run without brakes     -     yds.

Take off speed by Panoramic camera - 86 m.p.h.
 
Take-off and landing results uncorrected.
    Wind 8 m.p.h.     Temperature 20°     Pressure I.C.A.N. +120 ft.
    Take-off run     367 yds.
    Distance from rest to 50 ft. screen     640 yds.
    Landing run with brakes.     315 yds.
 
*Full throttle height


Night Flying.

                Night flying was made at full load with two types of exhaust manifold, 1. Ejector Type. 2. Streamline with special exits. (See photographs).

                The usual glim flare path with "Chance" floodlight was laid out in accordance withh A.&.O.A261/38.

Results.

1.             Comparing the streamline and ejector manifold it was found that the former were slightly superior. There is considerable flame from both types at full speed in level flight and at cruising speed; although this does not interrupt the view directly ahead, any object in a position slightly below and to one side of the observers path would be hidden. There is no flame noticeable at all with the engine throttled back to any speed below about 1650 r.p.m.

                It is considered that the exhaust manifolds cannot be accepted as satisfactory for night flying in the present condition.

2.     Cockpit.

                The cockpit lighting is found to be satisfactory and switches are conveniently placed. It is noted that the switch controlling the undercarriage position indicator is easily knocked into the "off" position when the throttle is being closed, this would undoubtably be very disconcerting to a pilot who had throttled back to put down the undercarriage and inadvertently knocked the switch. Although the undercarriage indicator lighting is very bright it is considered that it should be dimmed as it is important that is should be noticeable; it can be easily switched off if necessary.

3.     Landing lights.

                The landing lights are satisfactory for position but should preferably be more powerful, the lamps fitted are 240 watt.

4.     Take-off.

                The take-off is very long and in night flying this is rather uncomfortable for the pilot. In this connection it is recommended that a flare path of at least 800 yards in length should be used, and obstruction lights should be used on the highest obstructions around the whole boundary of the aerodrome.

                At take-off there is considerable flame from the exhausts, but this is not inconvenient until the aeroplane has passed the last flare when the position of the nose combined with the exhaust flames makes forward view extremely difficult.

                The slight swing taking off can be checked easily.

Approach and landing.

                The approach and landings were made using the aircraft lights or the Chance light. The approach is rather flat which makes landing easier, and a good estimate of height above the ground can be made. With the engine throttled back there is no flame from the exhaust and at 1600 r.p.m. there is sufficient speed in had to adjust the approach. By using a slight crab-sideslip the line of flares can be kept in view during the approach.

                The landing is normal but owing to the poor view ahead landings have to be made well out from the line of flares and it is recommended that the heat of the "T" of the flare path be increased to 300 yards.

Taxying.

                The aeroplane in taxying tends to reach the limiting coolant temperature very quickly, and for this reason it is necessary that as little time as possible be spent on the ground with engine running; on no occasion should the aeroplane be left stationary with engine running, unless pointing directly into the wind.

Fig. 1 Rate of Climb & Time to Height
Fig 2. Level Speeds & R.P.M. at Heights
Inspection and Test Certificate.

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