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基本信息

【范围】

The prediction of vehicle tem peratures during ascent through the earth’s atm osphere requires an accurate knowledge of the aerodynam ic heating rates occurring at the vehicle surface. Flight param eters required in heating calculations include the local airstream velocity, pressure, and tem perature at the boundary layer edge for the vehicle location in question. In addition, therm odynam ic and transport air properties are required at these conditions. Both lam inar and turbulent boundary layers occur during the boost trajectory. Experience has shown that lam inar and turbulent heating are of equivalent im portance. Lam inar heating predom inates in im portance in the stagnation areas, but the large afterbody surfaces are most strongly affected by turbulent heating. Once the local flow conditions and corresponding air properties have been obtained, the convective heating rate may be calculated for a particular wall tem perature. This assum es that the boundary layer flow regim e (that is, turbulent, laminar, or transitory) has also been established, so that a heating theory corresponding to the particular flow conditions may be selected. This section presents theoretical methods for com puting boost vehicle surface aerodynam ic heating rates. First, procedures are given for com puting the local flow distributions around the vehicle. Second, methods are given for com puting the convective heating rates, using the flow param eters found previously.

【与前一版的变化】

包含缩略语

Abs：
Abs：
AED C：
Aero.：
AIAA J.：
Alt：
ARAP：
ARDC：
ARL：
ARS：
atm：
axi：
BF：
BL：
B2O3：
Btu：
C：
cm：
CN：
CO2：
CO：
Co.：
conf：
Const：
convec：
cps：
deg：
dia：
dim：
Div：
E：
Eng：
Eq.：
°F：
Fe：
FF：
FPRE：
ft/s, FT/S：
ft：
ft-lb：
g：
gas rad：
GE-AETM：
GE-MSD：
GE-RSD：
Hemi：
Hg：
H20：
h：
Hz：
l2：
IAS：
in：
iso：
J.：
K：
K：
Lab.：
lb：
lb/ft3：
Li：
LMSD：
In：
log：
Mg：
Mass.：
Max, max：
Mo：
MSSD：
MSVD：
N：
Na：
NACA：
NASA：
NBS：
Ni：
No., no.：
N2：
O2：
p.：
pp.：
°R：
rad.：
rad (RAD.)：
s：
S：
SiC：
SiO2：
Tech.：
TGA：
Ti：
TIS：
TN：
TR：
Vol：
WADC：
WADD：
%：
～：
≈ or ≈：
＞＞：

包含图表

FIGURE 1 - Typical B	(Eq.1)	(Eq.2)
(Eq.3)	(Eq.4)	(Eq.5)
(Eq.6)	(Eq.7)	(Eq.8)
(Eq.9)	(Eq.10)	FIGURE 2-Isentropic
FIGURE 3 - Normal Sh	(Eq.11)	(Eq.12)
FIGURE 4-Pressure Ra	FIGURE 5-Temperature	FIGURE 6-Mach Number
FIGURE 7-Two-Dimensi	FIGURE 8-Real Gas Te	FIGURE 9-Real Gas Pr
FIGURE 10-Real Gas D	FIGURE 11-Frozen Flo	(Eq.13)
(Eq.14)	(Eq.15)	(Eq.16)
FIGURE 12-Modified N	FIGURE 13-Prandtl-Me	(Eq.17)
(Eq.18)	(Eq.19)	(Eq.20)
(Eq.21)	FIGURE 14-Cone Surfa	FIGURE 15-Cone Surfa
FIGURE 16-Mach Numbe	FIGURE 17-Real Gas C	FIGURE 18-Real Gas C
(Eq.22)	(Eq.23)	(Eq.24)
(Eq.25)	FIGURE 19-Property R	FIGURE 20-Reynvids N
FIGURE 21-Flow Field	FIGURE 22-Example of	(Eq.26)
(Eq.27)	(Eq.28)	(Eq.29)
(Eq.30)	(Eq.31)	(Eq.32)
(Eq.33)	FIGURE 23-Viscosity	FIGURE 24-Thermal Co
(Eq.34)	(Eq.35)	(Eq.36)
(Eq.37)	(Eq.38)	(Eq.39)
(Eq.40)	(Eq.41)	(Eq.42)
(Eq.43)	(Eq.44)	FIGURE 25-Laminar Ad
FIGURE 26-Turbulent	(Eq.45)	(Eq.46)
(Eq.47)	(Eq.48)	FIGURE 27-Reference
(Eq.49)	(Eq.50)	(Eq.51)
(Eq.52)	(Eq.53)	(Eq.54)
(Eq.55)	(Eq.56)	(Eq.57)
(Eq.58)	(Eq.59)	(Eq.60)
formula 1	(Eq.61)	(Eq.62)
(Eq.63)	formula 2	FIGURE 28-Air Compre
(Eq.64)	(Eq.65)	(Eq.66)
FIGURE 29 - Lam ina	FIGURE 30 - Blunted	FIGURE 31 - Blunt
FIGURE 32 - Blunted