In accordance with the instructions received in Air Ministry letter, reference 385627/35/R.D.A, dated 16.12.35 short performance and handling trials have been made, the results of which are given in the accompanying pages as follows:- | |
Pages. | |
Climbing trials | 1, 9. |
Speed trials | 1, 10. |
Take-off and landing trials | 1, 10. |
Airscrews | 6. |
Handling trials | 18, 18a,b,c,d,e |
Diving trials | 19. |
Design and Construction | 39. |
Power unit and Installation | 40, 40a,b. |
Summary of flying qualities | 43. |
TEST REPORT No. M/689 | |
Date. April 1936 |
AEROPLANE | Hawker monoplane | No. K5083 |
SPEC. No. | F.36/34 | |
CONTRACT. | 357483/34. | |
CONTRACTOR. | Hawker Aircraft Ltd.. |
TYPE | Landplane | DUTY | High Speed Single Seater Fighter. |
ENGINES. | Merlin C No. 111144 | Normal B.H.P | 1029 at Rated Altitude 11,000ft |
At 2,600 R.P.M. at rated boost pressure +6 lb/sq.in. |
Tare weight | Lb. |
Weight light | |
Fixed military load | |
Fuel (Firm’s figure) 107.5 gallons* | |
Oil (Firm’s figure) 7 | |
Flying weight on trials. | 5672 |
At Full Throttle | |||||||||||||||||||||||||||||||
Height Feet | Speed M.P.H | Time to Climb Mins | Rate of Climb ft/min | ||||||||||||||||||||||||||||
S.L | 253 | 0 | 2550
2000 | 261.5 | 0.75 | 2650
| 5000 | 274 | 1.89 | 2810
| 10000 | 295.5 | 3.63 | 2680
| 15000 | 314 | 5.70 | 2150
| 20000 | 311 | 8.40 | 1620
| 25000 | 301.5 | 12.08 | 1100
| 30000 | 282.5 | 18.10 | 570
| |
Service ceiling (estimated) 34,500 ft. | Landing speed (from camera) 59 M.P.H |
Take off run 265 yds. Time. 11.5 secs | Distance from rest to clear 50 ft. screen 430 yds. |
Stalling speed (A.S.I.) 57 M.P.H | Gliding in A.S.I. 78 M.P.H. |
Best landing A.S.I. 70 M.P.H | Distance to rest (with brakes) flap open After clearing 50 ft. screen 475 yds. |
Landing and take off tests corrected to wind of 5 M.P.H
In View of the urgency of the trials and as the aircraft was received ballasted by the firm to represent from the weight and C.G. point of view the aircraft with eight gun wings and other service equipment, no attempt was made to weigh the aircraft light or determine the tank capacities. It should be noted that the ballast to represent the guns was carried in the fuselage. |
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. | Position Error Correction And ** Compressibility Correction | R.P.M | Boost Lb/sq.in. |
Sea Level | 0 | 2550 | 151.5 | 150 | +1.5 0 | 2100 | +6 |
1,000 | 0.38 | 2600 | 154 | 150 | +1.5 0 | 2125 | +6 |
2,000 | 0.76 | 2650 | 156 | 150 | +1.5 0 | 2125 | +6 |
3,000 | 1.15 | 2710 | 158.5 | 150 | +1.5 0 | 2180 | +6 |
5,000 | 1.89 | 2810 | 163.5 | 150 | +1.5 0 | 2235 | +6 |
6,500 | 2.43 | 2880 | 167 | 150 | +1.5 0 | 2275 | +6 |
10,000 | 3.63 | 2680 | 173.5 | 148 | +1.6 -0.5 | 2305 | +4.15 |
13,000 | 4.8 | 2370 | 177.5 | 144 | +1.9 -0.5 | 2305 | +2.25 |
15,000 | 5.7 | 2150 | 181 | 142 | +2.0 -0.5 | 2305 | +1.1 |
16,500 | 6.4 | 2000 | 183 | 140 | +2.1 -0.5 | 2300 | +0.3 |
18,000 | 7.25 | 1840 | 186.5 | 139 | +2.2 -0.5 | 2300 | -0.5 |
20,000 | 8.4 | 1620 | 189.5 | 136.5 | +2.3 -0.5 | 2295 | -1.5 |
23,000 | 10.4 | 1310 | 195 | 133 | +2.5 -0.5 | 2285 | -2.9 |
26,000 | 13.0 | 990 | 199.5 | 129.5 | +2.7 -1.0 | 2265 | -4.3 |
28,000 | 15.2 | 790 | 204 | 127.5 | +2.9 -1.0 | 2245 | - |
30,000 | 18.1 | 570 | 208 | 125 | +3.0 -1.0 | 2210 | - |
7,600 | 2.76 | 2950 | 170 | 150 | +1.5 0 | 2300 | +6 |
Estimated absolute ceiling. 35,400 ft. | Greatest height reached. 30,000 ft |
R.P.M. stationary on ground. 1,990 | Boost pressure lb./sq.in. +6 |
** Additional correction to allow for compressibility effect on A.S.I. reading. | |
* Full throttle height. | |
Note 1 :- For position error correction curve and position of pressure head see Figs. 13 and 13a. |
Height in Standard Atmosphere Feet | True Air Speed M.P.H | A.S.I. M.P.H. | Position Error Correction And ** Compressibility Corrections | R.P.M | Boost Lb/sq.in. | Appoximate True Air Speed at 2750 R.P.M. |
Sea Level | 253 | 258 | -4.9 0 | 2505 | +6 | |
1,000 | 257.5 | 259 | -5.0 0 | 2535 | +6 | |
2,000 | 261.5 | 259 | -5.0 -0.2 | 2560 | +6 | |
3,000 | 265.5 | 259 | -5.0 -0.3 | 2590 | +6 | |
5,000 | 274 | 258.5 | -5.0 -0.6 | 2645 | +6 | |
6,500 | 280.5 | 258.5 | -5.0 -1.0 | 2685 | +6 | |
10,000 | 295.5 | 257.5 | -4.9 -1.7 | 2785 | +6 | |
13,000 | 308 | 246 | -4.2 -1.9 | 2870 | +6 | |
15,000 | 314 | 243 | -4.0 -2.2 | 2930 | +6 | |
16,500 | 315 | 237.5 | -3.7 -2.4 | 2960 | +5.7 | 273 |
18,000 | 313.5 | 231 | -3.3 -2.5 | 2940 | +4.3 | |
20,000 | 311 | 222 | -2.7 -2.5 | 2910 | +2.7 | |
23,000 | 306 | 207.5 | -1.9 -2.5 | 2860 | + .55 | |
26,000 | 298.5 | 192.5 | -1.0 -2.5 | 2795 | -1.4 | |
28,000 | 291.5 | 182 | -0.4 -2.5 | 2745 | -2.65 | |
30,000 | 282.5 | 170 | +0.3 -2.4 | 2680 | -3.90 | |
16,200* | 315 | 239 | -3.7 -2.4 | 2960 | +6 |
Landing and take-off tests corrected to wind of 5 m.p.h. | |
Take-off run (flaps shut) 265 yards. | Time11.5 secs. |
Distance from rest to clear 50 foot screen 430 yds. | |
Gliding in A.S.I 78 M.P.H. | Stalling speed (flaps shut) 77 M.P.H. A.S.I. |
Landing A.S.I. 70 M.P.H. | Stalling speed (flaps open) 57 M.P.H. |
Distance to rest (with brakes) after passing over 50 ft screen 475 yds. | |
Landing run with brakes 205 yds. | Landing run without brakes 525 yds. |
Note: Landing runs quoted with flaps open. | |
Take-off airspeed from camera measurements 81 m.p.h. | |
Landing airspeed from camera measurements 59 m.p.h. | |
** Additional corrections to allow for air compressibility on A.S.I reading. | |
* Full throttle height. | |
Note 1 :- For position error correction curve and position of pressure head see figs 13 and 13a. | |
Note 2:- For take-off and landing flight paths see fig 17. | |
RATE of CLIMB ~ TIME to HEIGHT | |
LEVEL SPEEDS & RPM at HEIGHTS |