By John J. Bertin
First-class reference resource for estimating re-entry warmth rather a lot. After examining the textual content you're left with the sensation that you just 'have an excellent deal with at the topic matter'. that is approximately the simplest you could say for this sort of ebook. The few examples that hide stagnation element temperature estimation have a number of steps that may be increased to higher illustrate the place the numbers got here from and the way they're used. No complains right here. even though.
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Additional resources for Hypersonic aerothermodynamics
6 P r e s s u r e d r a g of a r i g h t circular c y l i n d e r as a f u n c t i o n of Mach n u m b e r , as t a k e n from Ref. 6. the pressure drag for the blunt, right circular cylinder reaches its limiting value by Moo = 4 (Fig. 5), whereas the limiting values of the aerodynamic coefficients for the "more slender" lifting re-entry body are not achieved until the Mach number exceeds 7 (Fig. 6). This is consistent with the requirement that Moo sin 8b >> 1 for Mach number independence. 01. Data presented by Koppenwallner are reproduced in Fig.
Cheng ~° suggests 330,000 ft (100 kin) as the maximum altitude for the continuum assumption for a 1-ft sphere. 35 kin. Based on this discussion, it should be clear that there is no single, definitive criterion for an upper-limit altitude above which the continuum model for the flow is no longer valid. Furthermore, since the Knudsen number is a characteristic dimensionless parameter for low-density flows, these limits depend on vehicle size. If the radius were increased by a factor of 10, the corresponding density would be decreased by a factor of 10, and the curve could move upward an amount indicated by the density scale shown at the right of the graph in Fig.
X , - , - , . , . , , , \ \ ~ , , \ , , \ , , ~ o , " 60 FU|Iyl m e f l l d N- i 4 110" t .. . Ilyel" I '~" 1 lO'b Shock thickens - . - 8x10 "4 I / -~ 2x10 "4 -- / ~'. ~ 30: I. ,,,-, -I 8x10 "4 I I I ~ I I 1 20 25 30 35 40 45 50 Velocity "J10"3 55 (kft/s) Fig. 8 Boundaries for high-altitude flowfield regimes, as t a k e n f r o m Ref. 8. GENERAL CHARACTERIZATION OF HYPERSONIC FLOWS 13 the viscous region becomes comparable to that within the boundary layer. The limits of applicability for the continuum-flow model and for a discrete particle model, as presented by Moss and Bird, 9 are reproduced in Fig.
Hypersonic aerothermodynamics by John J. Bertin