Airworthiness compliance validating technique for wind tunnel test of a civil aircraft low speed flutter model

Modern civil aircrafts must be designed strictly according to airworthiness requirements. The aeroelastic design of domestic modern civil aircrafts is mainly based on the item CCAR25.629 "Aeroelastic Stability Requirement" and the advisory circular AC25.629-1A "Aeroelastic Stability Substantiation of Transport Category Airplane". Low speed flutter model wind tunnel test is a necessary technical means for the aeroelastic design of a civil aircraft, it is conducted to identify the subsonic flutter characteristics of a civil aircraft, their sensitive parameters and their effects on the flutter features, and to validate the theoretical analysis results. Meanwhile, the low speed flutter model wind tunnel test is also a necessary means for a civil aircraft design to show its airwothiness compliance. Here, the airworthiness compliance technique of low speed flutter model wind tunnel test for civil aircrafts was discussed based on the design and manufacturing experience of a certain aircraft type, and an effective scheme of airworthiness compliance design and verification for low speed flutter model wind tunnel test was put forward.