Aerodynamic characteristics at supersonic speeds of a series of wing-body combinations having cambered wings with an aspect ratio of 3.5 and a taper ratio of 0.2: Effects of sweep angle and thickness ratio on the static lateral stability characteristics at M = 2.01 Page: 2 of 39

                                
NASA TchnIoal UL  .
NACA RM L52E23l W                            I 77
3 1176 01436 4740
NATIONAL ADVISORY COMMITTEE FOR AERONAUTICS
"~ -                      RESEARCH M ORANDUM
AERODYNAMIC CHARACTERISTICS AT SUPERSONIC SPEEDS OF A
SERIES OF WING-BODY COMBINATIONS HAVING CAMBEIED
WINGS WITH AN ASPECT RATIO OF 3.5
AND A TAPER RATIO OF 0.2
EFFECTS OF SWEEP ANGLE AND THICKNESS RATIO
ON THE STATIC LATERAL STABILITY
CHARACTERISTICS AT M = 2.01
By Clyde V. Hamilton
SUMMARY
An investigation has been conducted in the Laigley 4- by 4-foot
supersonic pressure tunnel at a Mach number of 2.01 and a Reynolds
number of 2.2 x 106 to determine the effects of sweep angle and
thickness ratio on the static lateral stability characteristics of a
series of wings having a taper ratio of 0.2 and an aspect ratio of
3.5. The wings, which-were tested on a body of revolution, had sweep
angles of 10.80, 35, and 470 for a thickness ratio of .4 percent and
thickness ratios of 4, 6, and 9 percent for a sweep angle of 470. In
addition, the wing with a thickness ratio of 6 percent and a sweep
angle of 470 was tested with and without nacelles installed.
The results of these tests indicate that at a Mach number of 2.01
both the lateral-force parameter   Cy  and the directional-stability
parameter  Ca   tend to increase with lift coefficient. The effect of
increasing the sweep angle or thickness ratio is to increase the
positive value of  C   - and decrease the positive value of  Cn_
The effect of nacelle installation is to increase the positive values
of C     and  Cn   and the negative value of C0   -
.i-us.