本文主要以實驗方法對航空用油冷卻器作熱傳與壓降性能測試及分析。工作流體分別在管側為燃料油（JP-10），在殼側為液壓油（MIL-H-5606），來測試油冷卻器，兩側的工作溫度，在燃料油為40 oC、60 oC、80 oC，而液壓油為80 oC、100 oC、120 oC，而兩側的流量，燃料油為0.9~4 l/min，液壓油為0.9~7.2 l/min。紐賽爾數隨雷諾數變化的情形，於文中詳細探討。 經由壓降與流量的關係圖，可以發現燃料油對液壓油兩側之壓降大致和流量之平方成正比，與一般流體在管內流動之特性相同。但熱傳性能較其他現有熱傳增強管佳。 Abstract This thesis used an experimental method to test heat transfer performance and pressure drop of aviation oil cooler. The working fluids were fuel oil (JP-10) included in tube side and hydraulic pressure oil (MIL-H-5606) that contained in shell side. To test heat transfer effect of our cooler, we taken experimental work temperature to 40oC、60oC、80oC in fuel oil and set hydraulic pressure oil work temperature to 80oC、100oC、120oC.We also set fuel oil side flow rate form 0.9~4l/min and hydraulic pressure oil side from 0.9~7.2l/min.We discussed the relation of Nu number to Re number in detail. Through all plots of pressure drop to flow rates, we investigated both sides pressure drop of fuel oil and hydraulic pressure oil had proportion to square of flow rate, agreed with viscosity fluid, but heat transfer performance was better than present enhanced heat transfer tubes.
