Accession Number:

AD0915551

Title:

An Investigation of Model Scaling Effects at Mach Numbers from 0.60 to 1.40

Descriptive Note:

Final rept. 13 Mar-21 Jul 1973

Corporate Author:

ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AFB TN

Personal Author(s):

Report Date:

1973-12-01

Pagination or Media Count:

134.0

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.

Subject Categories:

  • Aerodynamics
  • Attack and Fighter Aircraft
  • Test Facilities, Equipment and Methods

Distribution Statement:

APPROVED FOR PUBLIC RELEASE