Stability and Control Tests of a 0.05-Scale RF-4C Aircraft Model Modified for Testing the AEDC 10-deg Transition Cone
Abstract
An investigation of the aerodynamic characteristics of a 0.05-scale RF-4C aircraft was conducted in the AEDC-16ft transonic Propulsion Wind Tunnel (16T) for the purpose of comparing a configuration with a Class II modification to that of the basic aircraft in preparation for flight testing. The class II modification entailed the addition of a pivoting nose boom and the AEDC 3-ft- long, 10-deg transition cone to the nose of the aircraft. Data were taken at Mach numbers 0.20, 0.60, 0.80, 0.90, 0.97, 1.05, 1.20, and 1.50 at an angle-of- attack range from -4 to 24 deg and a sideslip angle range from -10 to 10 deg. Test results show very little change attributable to the addition of the cone for most of the aircraft speed range, this change falling within the range of measurement uncertainty for the test. Insufficient data were acquired to fully investigate the effects of the modification at low speeds, where the aircraft would be in most critical attitudes; therefore, further tests of the aircraft at landing and approach speeds at high angles of attack are recommended.
Document Details
- Document Type
- Technical Report
- Publication Date
- Jan 01, 1976
- Accession Number
- ADA020305
Entities
People
- A. C. Easterling
- N. S. Dougherty Jr.
Organizations
- Arnold Engineering Development Complex