In accordance with Air Ministry letter, reference B.9242/39/A.D./R.D.L. dated 4th November 1939, performance trials have been carried out to compare this aeroplane with the standard Spitfire I fitted with a 2-pitch airscrew.

1.0 Comments on Trials.

            As delivered, this aeroplane was fitted with a bullet proof windscreen, armour plating over the fuel tank, and a domed top on the sliding hood to allow of more headroom for the pilot. None of these modifications had been made to K.9793 fitted with a two-pitch metal airscrew the performance of which is given in Part of Report M.692,b dated 12th July, 1939. Consequently changes in performance, particularly in level speed cannot be attributed solely to the change in airscrew.

2.0 Take-Off.

            The take-off run in zero wind and under standard atmospheric conditions is better than that of the 2-pitch airscrew Spitfire. The accompanying table gives the take-off for the 3-types of airscrews.

AirscrewTake-off run
(yards)
Distance to clear
50' screen (yards)
   Rotol225370
   2-Pitch Metal320490
   Wooden Fixed Pitch420790

3.0 Climb

            It was found that the best climbing speed as determined from partial climbs was not suitable owing to the instability, uncomfortably steep attitude, and poor view obtaining at this speed. This climbing speed was increased by 22 m.p.h. to a more suitable speed which improved the handling qualities of the aeroplane on the climb.

            The following table gives comparative times in minutes to reach various heights for the best climbing speed and the recommended climbing speed. Also included are the times to height for Spitfires with 2-Pitch and fixed pitch airscrews.

AirscrewTime to Height (Feet.)
10,00015,00020,00025,00030,000
   Rotol Best Climb3.45.37.711.116.1
   Rotol Recommended3.55.47.711.016.4
   2-Pitch Metal5.58   11.3  15.923.8
   Wooden Fixed Pitch4.46.69.413.822.4

Best climbing speed:-140 m.p.h. A.S.I. to 12,000' thereafter
decreasing by 1 m.p.h. per 1000 feet.
 
Recommended climbing speed:-162 m.p.h. A.S.I. to 12,000' thereafter
decreasing by 2½ m.p.h. per 1000 feet.

4.0 Level Speeds.

            In addition to the routine speed tests on this aeroplane as it was delivered, subsidiary tests were made to determine the effect of the bullet proof windscreen, and engine r.p.m. on the top level speed.

4.1 Windscreen test.  The bullet proof windscreen was replaced by the prototype Spitfire pattern of windscreen.

            As delivered the aeroplane was fitted with a bullet proof windscreen which has a flat front panel protruding about 1½ inches beyond the framework. After level speed tests had been completed this was replaced by the prototype pattern of windscreen. This consists of a windscreen with a curved front panel and is perhaps slightly better aerodynamically than the production pattern which has a flat, though flush-fitting front panel. Photographs are included at the end of this report showing both bullet-proof and prototype windscreens. As shown in Fig.2 the loss of speed resulting from the projecting bullet proof windscreen is 6 m.p.h.

4.2 Controlling R.P.M.  Speed tests were made at three heights below full throttle height with the boost pressure maintained constant at 6¼ lb. per sq.inch whilst the R.P.M. was varied over a range from 2600 to 3000.

            The results show that the maximum level speed is reached with the airscrew controlling at 2800 engine r.p.m. On increasing the r.p.m. to 3000 the speed was reduced, on the average by 4 m.p.h.

            For the particular engine fitted there is a reduction of 17 b.h.p. at constant boost (+6¼ lb) when the r.p.m. are increased from 2800 to 3000. The loss of speed is therefore probably due to the loss of power accompanied by a slight decrease in airscrew efficiency. The matter is being further investigated by Messrs.Rolls-Royce and Messrs.Rotols. It will be noted that reducing the R.P.M. from 3000 to 2800 lowers the full throttle height by 2000 feet.

4.3 Engine Power.  The engine installed in the aeroplane develops slightly less power under test bed conditions than that in K.9793, the aeroplane fitted with the 2-pitch airscrew. This could have the effect of reducing the top level speed by about 2 m.p.h.


SUMMARY OF TRIALS

AEROPLANESpitfire INo. N.3171
SPEC. NO.16/36
CONTRACTORVickers-Armstrong (Supermarine)Ltd.

TYPELandplaneDUTY    Single Seater Fighter.
 
ENGINES.Merlin IIINormal B.H.P    950/990 at Rated Altitude 12,250 ft
 
At     2,600     R.P.M.     at rated boost pressure +6¼ lb/sq.in. boost

 lb.
Tare weight4713.0
Weight light4476.5
Fixed military load  236.5
Service Load  657.5
Fuel   84   gallons*  630.0
Oil    5½    49.5
Flying weight on trials.6050

* 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.---
  2,000-0.72820
  5,000-1.82850
  10,000320.53.52895
  15,000339   5.32430
  20,000353.57.71840
  25,000345   10.9  1250
  30,000319   16.4    660

Service Ceiling34,700 ft.Landing speed- M.P.H.
Take off run225 yds.   Time - secs.Distance from rest to clear 50 ft. screen 370 yards
Stalling speed flaps up78 M.P.H.Gliding in A.S.I.87 M.P.H.
                      "-  Down68 M.P.H.
Best landing A.S.I.66 M.P.H.
 
Landing and take off tests corrected to zero wind and standard atmosphere.


AIRCRAFT.Spitfire I.     N-3171
ENGINEMerlin III.

Airscrews

  PositionCentre
  Variable Pitch airscrewRotol
  TypeMerlin.
  Serial No.2572.
  Makers No.-
  Diameter10'-9"
  No. of Blades3.
  Direction of BladesRt.Hd.
  A.M. Serial Nos. Hub2572.
  A.M. Serial Nos. Blade 1A-4184.
  A.M. Serial Nos. Blade 2A-4185.
  A.M. Serial Nos. Blade 3A-4136.
  Basic Pitch Setting-
  Pitch Range.35° 0'
  High Pitch Setting58° 20' (estimated)
  Low Pitch Setting23° 20'


CLIMBING TRIALS

Spitfire N.3171

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 Level0     Controlled
at 2600
 
  1,0000.42810163   161   -0.7-.16.4
  2,0000.72820165   161   -0.7-.16.4
  3,0001.12830167.5161   -0.7-.26.4
  5,0001.82850172.5161   -0.7-.26.4
  6,5002.32860176.5161   -0.7-.36.4
10,0003.52895186.5161   -0.7-0.46.4
11,0003.92905189   161   -0.7-.56.4
13,0004.62665193.5159.5-0.4-0.75.2
15,0005.32460195.5155.5+.2-0.73.9
16,5006.02250197.0152.5+.7-0.83.1
18,0006.72075198.5149.5+1.2-0.82.2
20,0007.71840201.0146   +1.8-0.91.0
23,0009.51480205.0140   +2.9-1.0-0.8
26,00011.8  1130209.0134.5+3.9-1.0-2.5
28,00013.8    895212.0130.5+4.7-1.1-3.6
30,00016.4    660214.0126.5+5.4-1.1-4.7

Estimated absolute ceiling         35,600Greatest height reached      30,000
R.P.M. stationary on ground     2850Boost pressure lb./sq.in.    +6½
* Full throttle height
Service ceiling   34,700' feet


SPEED TRIALS

at 3000 R.P.M. and 6¼ lbs.per sq.inch boost (nominal)
Spitfire N.3171
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.
P.E.C.E.
Sea Level     Controlling at
3000 R.P.M.
 
1,000     
2,000     
3,000     
5,000     
6,500     
10,000320.5286   -8.5-2.1+6.1  
13,000332   283.5-8.5-2.9+6.1  
15,000339   280.5-8.5-3.4+6.1  
16,500345   279   -8.5-3.8+6.1  
18,000350.5277.5-8.5-4.2+6.1  
20,000353.5271   -8.5-4.6+5.25
23,000350   255.5-8.4-4.8+3.15
26,000341.5237.5-8.0-4.7+1.1  
28,000332   222.5-7.4-4.5-0.3  
30,000319   205   -6.3-4.0-
18,900354   276   -8.5-4.4+6.1  

Landing and take off tests corrected to zero wind and standard atmosphere.
Take off run       225
Distance from rest to clear       50     foot screen       370 yds.
Gliding in A.S.I.     87     M.P.H.Stalling speed       -
Best landing A.S.I.     66     M.P.H.
Distance to rest (with brakes) after passing over 50 ft. screen     -     yds.
Landing run with brakes     310     yds.Landing run without brakes     -     yds.

T.O. and Landing Runs under actual conditions of tests, i.e:- wind 4 m.p.h., Temp. +8°C., Press. 30.0" Hg
 
T.O. Run 195 yds. in 9.1 secs.
Distance to 50' screen 335 yds.
Landing run 265 yds. in 16.7 secs.
 
*Full throttle height


Conclusions.

1.           This aeroplane has a much better take-off and climbs faster than other Spitfires fitted with wooden fixed pitch or metal two pitch airscrews.

2.           There is a drop of 13 m.p.h in maximum level speed compared with the 2-pitch airscrew aeroplane but of this, 8 m.p.h. can be attributed to sources other than the airscrew.

3.           Below full throttle height an increase in speed of about 4 m.p.h. can be attained by controlling the engine R.P.M. at 2800 instead of 3000.

4.           The limiting diving speed can be reached much more rapidly with this aeroplane than with Spitfires fitted with fixed pitch wooden and 2-pitch metal airscrews.

Fig. 1 Rate of Climb, Time & Boost to Height
Fig 2. Level Speeds & Boost at Heights
Oil Cooling & Glycol Cooling Test
Inspection and Test Certificate

Fig. 1 Rate of Climb, Time & Boost to Height   Fig 2. Level Speeds & Boost at Heights   Inspection and Test Certificate

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