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).
Mathematical formulas and summary concerning radiator performance at various altitudes.
| Identifier | ExFiles\Box 149a\2\ scan0331 | |
| Date | 7th January 1936 guessed | |
| -4- Hs{Lord Ernest Hives - Chair}/Std.1/JH:13:156 but since Ta = B - (100 - Tg) ( .187 + .834k) _______________________ r^.83 from (b) ∴ Tc = .002h + (100-.001h) - (100-Tg) (.167 + .834(1-.00003k)) __________________________________ (1-.000025h)^.83 ∴ Tc = 100 + .001h-(100-Tg) (1-.000025h)^.83 ___________________________________ (1-.000025h)^.83 = 100 + .001h - (100-Tg) (1-.000025h)^.17 from (c) From expression (c) the altitude corrected critical air temperatures can be calculted for any given altitude. Sheet (1) shows the variation of boiling point, air temperature density and power factor with altitude up to 10000 ft. Sheet (2) shows the variation of altitude corrected critical air temperature with altitude up to 10,000 ft, for three different radiators. For example:- From sheet (3) taking Radiator No.1 boiling will occur at 5000 ft. when the sea level air temperature is 36.7°C. Summary:- If a radiator is adequate for cooling a car under sea level conditions it will be adequate for the car under altitude conditions. HS{Lord Ernest Hives - Chair}/Std | ||