1. Introduction.
This report summarizes the results obtained on the prototype Mark 21 fitted with a Griffon 61 engine.
2. Summary of Results
At an all up weight of 9000 lb. and wtih combat rating of 2750 r.p.m. and 18 lb. boost:-
| (a) | Maximum level speed | 455 m.p.h. at 25,600 ft. |
| (b) | Maximum rate of climb | 4800 Ft./Min. at 7700 ft. |
| (c) | Time to 30,000 ft. | 7.85 mins. |
| (d) | Service ceiling | 42,800 ft. |
| (e) | Coolant and oil suitabilities: | Full tropical under combat climb conditions. |
3. Condition of Aircraft
| (a) | Griffon 61 engine No. 1266 fitted with a .45 airscrew reduction gear. |
| (b) | 11 ft. 0 in. dia. 5 blade Jablo Rotol airscrew with faired roots. Blades to Drg. No. RA.10129/JJ. |
| (c) | Morris type QEW (port and QEY (starboard) radiators. |
| Morris type QEV intercoller radiator. | |
| Morris type QEZ oil cooler. | |
| The duct static exit areas are: closed mean 0.76, open mean 2.02 sq. ft. | |
| (d) | Tropical type of air intake to Drg. No. 35638 Sht. 35 was fitted. |
| (e) | Multi-ejector exhausts fitted. |
| (f) | Windscreen with a curved front panel as on production rear view fuselage. |
| (g) | T.R.1133 whip type aerial fitted. |
| (h) | Undercarriage-wheel flaps fitted for final flight. Retractable tail wheel. |
| (i) | Four 20 m/m cannon armament. |
| (j) | All up weight 9000 lb. C.G. 3.3" inches aft of datum. |
4. Reduction of Results
Results have been reduced to I.C.A.N. standard conditions in accordance with A.D.M. 555.
5. Results
The results are shown on Figs. 1-4.