From the Rolls-Royce experimental archive: a quarter of a million communications from Rolls-Royce, 1906 to 1960's. Documents from the Sir Henry Royce Memorial Foundation (SHRMF).
Cooling tests for a Hawker double skin wing surface condenser.
| Identifier | ExFiles\Box 179b\3\ img394 | |
| Date | 28th March 1933 guessed | |
| -2- corresponded very closely with the figures obtained on the installation hangar. From the Installation Hangar tests the cooling for the Hawker double skin wing surface condenser amounted to 2 3/8 pints condensate/3 mins. for 10.5 sq. ft. area or 3.5 ft. leading edge profile at 96 M.P.H. mean air speed and 10°C. Air Temperature. This corresponds to .2225 pints of condensate/min/ft. of outer surface at 100 M.P.H. and 15°C. Air temperature, or since the density of condensate was approximately 1.23 lbs/pint = .2735 lbs. condensate /min. Note: The inside surfaces were heat insulated by packing with cotton waste. Taking the heat flow figure for an engine to be 2.4 lbs. condensate /min./100 HP. this condenser would cool 11.4 HP./Ft. profile at 100 M.P.H. and 15°C. air temperature at ground level density. Previous tests have been done, both on the hangar and on sections in an air jet, of the plain leading edge condensers and of finned leading edge condensers. The results are given in Table 1. for the cooling of the different types at 100 M.P.H. and 15°C. air temperature. Hs{Lord Ernest Hives - Chair}/T.A.Gibson. | ||