For this problem, we find U = 3.35 W/m²KĬonsider now the addition of the radiative flux. Tair – Tlox = 9 1 hco Aco Aal + + + Ксо Kal hci Q UAġ Ralcony + Ralcony + Rcoconv + Rcocond U i.e., thermal resistances in series add. ![]() с u 0 Ambient Air 300K T-SE - ESE LOX 90K r k 3mm 5mm Fig. What is the steady-state heat flux into the LOX tank?Ī А. The booster tank diameter of 8 ft is sufficient to render wall curvature effects negligible, and its length is enough to allow end effects to be ignored. The ground and outside air temperatures are both approximately 300 K, and the sky is overcast with high relative humidity. The tank is composed of an aluminum wall of Aal = 5 mm thickness and an outer layer of cork with Aco 3 mm. It is desired to estimate propellant top-off requirements, for which the key determining factor is the heat flux into the tank. The LOX is maintained at a temperature of 90 K in the tank by allowing it to boil off as necessary to accommodate the input heat flux it is replaced until shortly before launch by a propellant feed line at the pad. ![]() ![]() ![]() Transcribed image text: Example 9.1 Consider the insulated wall of a vertically standing launch vehicle liquid oxygen (LOX) tank, illustrated schematically in Fig.
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