PRELIMINARY BASE PRESSURES OBTAINED FROM THE X-15 AIRPLANE AT MACH NUMBERS FROM 1.1 TO 3.2
Abstract
Base pressure measurements were made on the fuselage, 10 degree-wedge vertical fin, and side fairing of the X-15 airplane. Data are presented for Mach numbers between 1.1 and 3.2 for both powered and unpowered flight. Comparisons are made with data from small-scale-model tests, semiempirical estimates, and theory. The results of this preliminary study show that operation of the interim rocket engines reduces the base drag of the X-15 by 25 to 35% throughout the test Mach number range. Values of base drag coefficient for the side fairing and fuselage obtained from X-15 wind-tunnel models were adequate for predicting the over-all full-scale performance of the test airplane. The leading-edge sweep of the upper movable vertical fin was not an important factor affecting the fin base pressure. The power-off base pressure coefficients of the upper movable vertical fin are in general agreement with the small-scale blunt-trailing-edge-wing data of several investigators and with two-dimensional t eory. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Aug 01, 1961
- Accession Number
- AD0261195
Entities
People
- Edwin J. Saltzman
Organizations
- National Aeronautics and Space Administration