An Investigation of Model Scaling Effects at Mach Numbers from 0.60 to 1.40
Abstract
Wind tunnel investigations of three scale models were conducted to determine the effects of model scaling in the subsonic and transonic flow regimes. The models were 4.7-, 13-, and 17-percent scale F-15 fighter equivalent body models. The data were obtained at Mach numbers from 0.60 to 1.40 and free- stream Reynolds numbers from 1.0 to 5.3 million for model angles of attack from 0 to 5 deg. The results show that at subsonic Mach numbers the zero-lift pressure drag coefficient of the basic configurations was a function of Reynolds number and Mach number. However, the pressure drag coefficient for the fuselage- alone configuration and the alternate wing configuration was essentially invariant with Mach number for Mach numbers below 0.90. The data obtained with the cylindrical afterbody model and integrated aft-end pressure drag increments show that the transonic interference resulting from model size was primarily confined to the contoured fuselage afterbody.
Document Details
- Document Type
- Technical Report
- Publication Date
- Dec 01, 1973
- Accession Number
- AD0915551
Entities
People
- David E. A. Reichenau
Organizations
- Arnold Engineering Development Complex