This study examines the impact of Propeller blade pitch angle mismatch on Noise, thrust, and vibration in light aircraft. Tests were conducted using a simulator with one blade set at increased pitch angles (10°, 12°, 14°) compared to the standard 8°. Results showed that mismatches increased vibration (above 0.26 IPS), Noise levels, and caused operational issues such as fuel leakage and backfire. While thrust initially increased with pitch, it dropped at 14° due to fuel flow instability. These results highlight the need for strict pitch alignment tolerances to ensure optimal performance and safety in aircraft maintenance and operation.

Abstract
1. 서 론
2. 본 론
    2.1 프로펠러의 소음
    2.2 항공기 소음분석
    2.3 항공기 추력
    2.4 진동 수치 측정
3. 실험 및 해석
    3.1 실험 방법
4. 결 론
    4.1. 피치각 불일치에 따른 진동증가
    4.2. 추력 성능의 한계점
    4.3. 소음 주파수의 변화
    4.4. 정비기준 설정의 필요성
References

• 김재필(Kyungwoon University of Aero Mechanical Engineering, Professor) | Jae-Pil Kim Corresponding author
• 신상훈(Kyungwoon University of Aero Mechanical Engineering, Professor) | Sang-Hoon Shin