Accession Number:
AD0256027
Title:
AERODYNAMIC CHARACTERISTICS OVER A MACH NUMBER RANGE OF 1.40 TO 2.78 OF A ROCKET-PROPELLED AIRPLANE CONFIGURATION HAVING A LOW 52.5 DEGREE DELTA WING AND AN UNSWEPT HORIZONTAL TAIL
Descriptive Note:
Corporate Author:
NATIONAL AERONAUTICS AND SPACE ADMINISTRATION WASHINGTON D C
Personal Author(s):
Report Date:
1961-05-01
Pagination or Media Count:
1.0
Abstract:
A free-flight investigation of an airplane configuration having a low 52.5 degrees delta wing and an unswept horizontal tail was conducted over a Mach number range of 1.40 to 2.78. At a fixed tail setting of -3.0 degrees, the trim lift coefficient and angle of attack varied from about 0.12 to 0.04 and 3.8 degrees to 2.0 degrees, respectively. The base drag was approximately 5 percent of the total drag at trim lift. Lift-curve slope, static longitudinal stability, and damping in pitch were obtained only at Mach numbers of 2.59 to 2.74. Theoretical calculations of lift-curve slope and aerodynamic-center location were in good agreement with experimental results. Author