Accession Number:

AD0804047

Title:

COMMERCIAL SUPERSONIC TRANSPORT PROGRAM. PHASE II-A. COMPREHENSIVE REPORT. VOLUME XIV-A. AIRCRAFT SYSTEM CONCEPT.

Descriptive Note:

Corporate Author:

BOEING CO RENTON WA AIRPLANE DIV

Personal Author(s):

Report Date:

1964-11-01

Pagination or Media Count:

33.0

Abstract:

The improved performance location of the engines reduces engine exhaust noise on the tail and fuselage, while virtually eliminating noise impingement on the wing. Sound suppression techniques are used and the structure is designed to be fully capable of coping with the temperature and noise for the design life of the airplane, even with occasional hot-day augmented operation under static and takeoff conditions. Passengers are located completely ahead of the engine exhaust nozzle noise cone. The aerodynamic pitchup tendency at high-angles-of-attack has been resolved in wind tunnel tests at both NASA Ames and Boeing. Risk of engine ingestion of debris and slush is eliminated by the use of deflectors and by providing greater distance between inlet and ground. Distribution of hydraulic system power to the control surfaces is balanced so that any failure of a power system does not result in asymmetric control surface operation. Spring-actuated mechanical locks are provided on the aileron and rudder control surfaces to prevent flutter in the event of hydraulic powr failure. Primary flight control system complexity has been reduced. Formal design reviews, system mockups, an extensive equipment quality analysis program, and an integrated test plan using large developmental test rigs provide early detection of problems and permit verification of system operation through prompt revision and refinement.

Subject Categories:

  • Civilian Aircraft
  • Jet and Gas Turbine Engines

Distribution Statement:

APPROVED FOR PUBLIC RELEASE