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).
Page of formulas and definitions for calculating engine heat loss and cooling performance, comparing sea level and altitude conditions.
| Identifier | ExFiles\Box 149a\2\ scan0329 | |
| Date | 15th January 1936 | |
| -2- Hs{Lord Ernest Hives - Chair}/Std.1/JH.15.1.36. I.H.P. = H.{Arthur M. Hanbury - Head Complaints} B.H.P. = .9H = ... friction losses etc. Heat loss = .6H. = friction losses + heat of combustion etc = .1H + .5H. I.H.P. at altitude = kH. ... Heat loss at altitude = .1H + .5kH. ... = (.1H + .5kH)/.6H = .167 + .834k --------(a) (2) (3) & (4) Cooling ∝ (ρV)^.83 θ where V = velocity of air through matrix. ρ = density of air. θ = temp. difference between mean water and mean air temps. But v is constant since comparisions are at same car and engine speeds. Also, since engine speeds are constant for comparisons, water flow is constant. ... θ ∝ Δ where Δ = temp. difference between inlet water and inlet air temps. ... cooling ∝ ρ^.83 Δ Inaddition to previous notation, for given radiator. Let ΔG = temp. difference between inlet water and air temps. to disspate H under sea level condition. " ΔA = corresponding temp. difference at altitude. " YG = critical air temp. (sea level condition) " TA = " at altitude under altitude conditions. | ||