Heat transfer for Mach numbers up to 2.2 and pressure distributions for Mach numbers up to 4.7 from flight investigations of a flat-face-cone and a hemisphere-cone Page: 3 of 61
This report is part of the collection entitled: National Advisory Committee for Aeronautics Collection and was provided to Digital Library by the UNT Libraries Government Documents Department.
The following text was automatically extracted from the image on this page using optical character recognition software:
2 NACA RM L58B18
The aerodynamic-heating characteristics of blunt noses are of basic
importance in the design of long-range ballistic missiles. The Langley
Pilotless Aircraft Research Division is conducting investigations to
determine the heating characteristics for various blunt noses. (See
refs. 1, 2, and 3.) Presented herein are the results of flight tests
made at the Langley Pilotless Aircraft Research Station at Wallops
Island, Va., for two noses: a truncated cone having a half-angle of
14.50 and nose-to-base radius ratio of about 0.6 where the base diameter
is 17.6 inches, and a hemisphere-cone (half-angle of 14.50) having a
nose-to-base radius ratio of about 0.7 where the base diameter is also
17.6 inches. Basic flight data and heat-transfer data for the hemisphere-
cone have already been published for Mach numbers from 2.32 to 3.14 in
reference 4. The lower Mach number data not given in reference 4 were
reduced and are presented herein in order that a more realistic compari-
son could be made with the data of the truncated cone.
Heat-transfer data for both models are presented for Mach numbers
up to 2.2 and free-stream Reynolds number based on a length of 1 foot
up to 14.5 x 106 whereas the pressure data for both models are presented
for Mach numbers up to approximately 4.7.
Cp pressure coefficient,
O. 7p . 2
cf local skin-friction coefficient
Cp specific heat, Btu/lb-OR
h altitude, ft
M Mach number
NSt Stanton number
PlP27 P6 pressure stations (see figs. 2(a) and 3(a))
p pressure, lb/sq in. abs
.. ..- . +~
Here’s what’s next.
This report can be searched. Note: Results may vary based on the legibility of text within the document.
Tools / Downloads
Get a copy of this page or view the extracted text.
Citing and Sharing
Basic information for referencing this web page. We also provide extended guidance on usage rights, references, copying or embedding.
Reference the current page of this Report.
Speegle, Katherine C.; Chauvin, Leo T. & Heberlig, Jack C. Heat transfer for Mach numbers up to 2.2 and pressure distributions for Mach numbers up to 4.7 from flight investigations of a flat-face-cone and a hemisphere-cone, report, May 8, 1958; (digital.library.unt.edu/ark:/67531/metadc63975/m1/3/: accessed November 12, 2018), University of North Texas Libraries, Digital Library, digital.library.unt.edu; crediting UNT Libraries Government Documents Department.