GENERAL SUMMARY

1.   Introduction:
 
               Although a long time has elapsed since the introduction of the Merlin XX engine into the Hurricane, and although several reports have already been issued on the results of tests made of Hurricane IIís, this report deals with the results of tests made on the aeroplane as a type and is designed to be used as a basis for comparative results either already obtained or to be obtained in the future.

2.   Condition of aeroplane relative to tests:

               The aeroplane appears as a Mark IIA, B, or C. The Mark IIA is further sub-divided into Series 1 and 2 according to whether the longerons are unstrengthened or strengthened. The suffix A denotes the installation of 8 - .303 guns in the wings, the B denotes 12 - .303 inch guns in the wings and C denotes 4-20 mm guns in the wings. From the above it will be seen that one of the aeroplanes tested had 12 - .303 inch guns installed and the other 8 - .303 inch guns. Throughout the tests the gun ports were sealed.

               One of the aeroplanes Z.3564, was first used for tests of under-wing fuel tanks, but for the tests detailed in this report the under-wing tanks were removed and the aeroplane made standard. All performance measurements were made on Z.3564 but this aeroplane was taken away for special tests at the firm and handling trials were completed on Z.2346.

               Other conditions applicable to both aircraft were as follows: no snowguard was fitted, a rear-view mirror was mounted on top of the pilotís hood outside, and triple-ejector exhausts were fitted (without fishtails).

3.   Loading of aircraft:

               Throughout the trials the aircraft were loaded as follows:

AeroplaneLoadingWeight
(lb)
C.G.
(inches aft of datum)
Z.3564Extended aft limit739759.6
Z.2346Forward limit655856.3

               The typical service load produces the aft limit so the 1% A.M.C. extension was added to the C.G. position of Z.3564 in order to save re-loading the aeroplane later for handling tests. The extension was arrived at by the addition of 64 lb. of ballast.

4.   Results of tests:


SUMMARY OF TRIALS

AEROPLANEHurricane IIbNo.    Z.3564.
 
SPEC. No.
CONTRACT.
CONTRACTOR.Hawker Aircraft Co.

TYPESingle-engine monoplaneDUTY    Fighter.
 
ENGINES.Merlin XX.Normal B.H.P     1255     at Rated Altitude 10,000 ft.
  "          "         1190     at Rated Altitude 18,500 ft.
 
At     2,850     R.P.M.     and +9 lb. boost
  "      2,850     R.P.M.     and +9 lb. boost

 lb.
Tare weight5559
Weight light
Fixed military load
Service Load (including 64 lb. ballast)1058
Fuel 97 gallons*  699
Oil  9    81
Flying weight on trials.7397

* Based on 7.5 lb. per gallon.

At Full Throttle
Height FeetSpeed M.P.HTime to Climb MinsRate of Climb ft/min
S.L    0      
  2,000 0.7  2710
  5,000  1.8  2710
10,000294 3.7  2510
15,000303 5.9  2150
20,0003268.5  1740
25,000330 8.8  1690
30,000    309.517.0      720

Service ceiling 35,900 ft.Landing speed         M.P.H
Take off run     Time.     secsDistance from rest to clear ft. screen yds.
                   
Stalling speed M.P.HGliding in A.S.I. M.P.H.
Best landing A.S.I. M.P.H Distance to rest (with brakes)
After clearing 50 ft. screen .
 
Landing and take off tests corrected to


AIRCRAFTHurricane II. Z.3554.
ENGINEMerlin XX. No. 26687/188972.

AIRSCREWS.

PositionCentre.   
Variable Pitch Airscrew.Rotol C.S.   
Type.R.S.5/3.  
Serial No.18436   
Diameter.11' 3"   
No. of Blades3
Direction of rotation.R.H.   
Serial Nos.- Hub.18436   
    "       "         "   Blade No.1JP 10461   
    "       "         "       "     No.2JP 10190   
    "       "         "       "     No.3JP 10460   
Basic pitch setting.Not stated.
Pitch range.35°
High pitch setting. (Measured)65°   -   7'
Low pitch setting.30°   -   7'


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.
Compressibility &
Position
Error
Correction
Comp.   |   P.E.C.
R.P.M.Boost
lb./sq. in.
Radiator
Blower
Sea Level0         Controlling
at
2850
R.P.M.
 M
  1,0000.42710145.5142   0  +1.4+9.8  
  2,0000.72710147.5142   0  +1.4+9.8  
  3,0001.12710150   142   -0.1+1.4+9.8  
  5,0001.82710154.5142   -0.1+1.4+9.8  
  6,5002.42710156   142   -0.2+1.4+9.8  
10,0003.72510166.5142   -0.3+1.4+8.7  
13,0005.02610174.5142   -0.4+1.4+7.0  
15,0005.92150180   142   -0.5+1.4+9.4  S
16,5006.62150184.5142   -0.5+1.4+8.8  
18,0007.41940186.5140   -0.6+1.5+7.8  
20,0008.51740190.5138   -0.7+1.6+6.3  
23,00010.3   1440186.5135   -0.7+1.9+4.2  
26,00012.7   1130202.5132   -0.9+2.1+2.0  
28,00014.6     920207   130   -1.0+2.3+0.8  
30,00017.0     720212   128   -1.1+2.5-0.5  
32,00020.4     510216.5126   -1.1+2.6-1.7  
34,00025.6     300215   120   -1.1+3.2-2.8  
35,00029.8     200205.5111   -0.9+4.1-3.3  
 * 8,300   3.02710162.5142   -0.2+1.4+9.8  M
** 15,700     6.22160182   142   -0.5+1.4+9.4  S

Estimated absolute ceiling 38,800'Greatest height reached. 35,900 ft
R.P.M. stationary on ground. Boost pressure lb./sq.in.
* Full throttle height. *8,300 ft. in 'M' blower. **15,700 ft. in 'S' blower.
** Service ceiling. 35,900' (Estimated)
Note1:- For position error correction curve and position of pressure
head see Fig. 13 in 15th Part of Report A.& A.E.E./689.


SPEED TRIALS

Height in
Standard
Atmosphere
Feet
True
Air
Speed
M.P.H.
A.S.I.
M.P.H.
Compressibility
and
Position
Error
Correction
P.E.C.   |   Comp.
R.P.M.Boost
lb./sq. in.
Blower gear.
Sea Level      3000  
  1,000         
  2,000         
  3,000         
  5,000           
  8,000288   261.5-5    -1.3+9     M
10,000294   259   -4.9  -1.6+9     
13,000305   256.5 -4.8  -2.1+9     
15,000303   247   -4.5  -2.3+7.4  
16,500301.5240   -4.2  -2.4+6.0  
18,000316.5247   -4.7  -3.2+8.8  S
20,000326   246   -4.5  -3.5+8.8  
23,000329   235.5-4    -3.7+7     
26,000324   220.5-3.4  -3.8+4.7  
28,000318   208  -2.8  -3.7 +3.1  
30,000309.5194.5-2    -3.5+1.6  
* 20,800   330   246   -4.5  -3.6+8.8  
Landing and take off tests corrected to zero wind and standard atmosphere.
Take off run (a)   280     (b)   235 yds with (a)   5°     (b)   35° FlapTime   -   secs.
Distance from rest to clear 50 foot screen (a)   420 yds.
Gliding in A.S.I.       M.P.H.Stalling speed (b)   440 M.P.H./Kts.
Best landing A.S.I.   M.P.H.
Distance to rest (with brakes) after passing over 50 ft. screen     yds.
Landing run with brakes yds.Landing run without brakes     yds
 
    Under conditions of test.   that is, Wind 9.0 m.p.h. pressure 29.99 "Hg. Ground temperature 17°C.
 
    Take off run. (a) 210, (b) 195 yds
 
    Distance from rest to clear 50 ft. screen = (a) 400, (b) 375 yds.
 
* Full Throttle Height
Note 1:- For position error correction curve and position of pressure head see Hurricane II curve Fig.13 in 15th Part of Report AAEE/689.
 
WEIGHT AND LOADING DATA
CG DIAGRAM
RATE OF CLIMB & TIME TO HEIGHT
LEVEL SPEEDS & BOOST AT HEIGHTS

WWII Aircraft Performance