TY - JOUR
T1 - Analysis on Aerodynamic Performance of Single-skinned Parawing in the Hypersonic Rarefied flow
AU - Rao, Q. J.
AU - Fang, S. Z.
AU - Zhang, S.
N1 - Publisher Copyright:
© 2020 IOP Publishing Ltd. All rights reserved.
PY - 2020/7/9
Y1 - 2020/7/9
N2 - In consideration of the serious aerodynamic heating and overload in the return process of the space vehicles, a single-skinned parawing suitable for the whole return process is proposed, which uses lift deceleration to realize flexible reentry. A three-dimensional steady numerical simulation of the single-skinned parawing with different leading edge sweep angles was conducted by using the direct simulation Monte Carlo method, and the effects of different Mach numbers and altitudes on the aerodynamic performance of the parawing were studied in the hypersonic rarefied atmosphere. The results show that with the increase of the leading edge sweep angle, the aerodynamic performance of the parawing decreases obviously, but the ability of stall resistant is improved. The lift-drag ratio decreases monotonously with the increase of Mach number and altitude. The effect of Mach number on lift-drag ratio is not obvious, but the effect of altitude is more obvious. The maximum lift-drag ratio of parawing is 0.45 at 90 km, but only about 0.1 at 110 km. The peak heat flux always appears near the head, which will decreases obviously by decreasing the flight speed or increasing the flight altitude.
AB - In consideration of the serious aerodynamic heating and overload in the return process of the space vehicles, a single-skinned parawing suitable for the whole return process is proposed, which uses lift deceleration to realize flexible reentry. A three-dimensional steady numerical simulation of the single-skinned parawing with different leading edge sweep angles was conducted by using the direct simulation Monte Carlo method, and the effects of different Mach numbers and altitudes on the aerodynamic performance of the parawing were studied in the hypersonic rarefied atmosphere. The results show that with the increase of the leading edge sweep angle, the aerodynamic performance of the parawing decreases obviously, but the ability of stall resistant is improved. The lift-drag ratio decreases monotonously with the increase of Mach number and altitude. The effect of Mach number on lift-drag ratio is not obvious, but the effect of altitude is more obvious. The maximum lift-drag ratio of parawing is 0.45 at 90 km, but only about 0.1 at 110 km. The peak heat flux always appears near the head, which will decreases obviously by decreasing the flight speed or increasing the flight altitude.
UR - http://www.scopus.com/inward/record.url?scp=85089548507&partnerID=8YFLogxK
U2 - 10.1088/1757-899X/887/1/012038
DO - 10.1088/1757-899X/887/1/012038
M3 - Conference article
AN - SCOPUS:85089548507
SN - 1757-8981
VL - 887
JO - IOP Conference Series: Materials Science and Engineering
JF - IOP Conference Series: Materials Science and Engineering
IS - 1
M1 - 012038
T2 - 2020 4th International Conference on Aeronautical Materials and Aerospace Engineering, AMAE 2020
Y2 - 14 May 2020 through 17 May 2020
ER -