H=0 km & Ma=0 test was conducted for aero-engine at altitude simulated test facility(ATF).The reasons for the difference between altitude cell pressure and standard atmospheric pressure were analyzed.Moreover

the effects on the engine test of H=0 km & Ma=0 at a pressure difference between altitude cell and international standard atmosphere(ISA) sea level static(SLS)

caused by exhaust gas ejection and cooling-air flow in altitude cell

were also studied.A scheme was thus put forward for the influence of ambient pressure change on the engine test results of H=0 km & Ma=0.Furthermore

several research tests were conducted in two or three test beds of H=0 km & Ma=0 using a turbojet engine and a turbofan engine.The test results show that

corrected results for engine test of H=0 km & Ma=0 at ATF

when ambient pressure is about 70 kPa and ram ratio is between 0.99 to 1.02

are consistent with those under standard atmosphere

sea level static.