Boundary Lyer Theory

XTII. I.nntinnr l)o~~rldnry 1:iyrrs in romprmsihlr flow
'J'lrc sul)sc.ript wp rcfrrs to the point of srp:~mtion, thr subscri1)l 0 ~~~~~~~ibrs the
shte upstream of the sl1oc4c wavc, and subscript 1 clenotes the state at the edge
of thr I)ou~itlary Inycr.
'I'lrc pressure coeffirirnt at separat,ion turns out to 11,zve the form
whcrc R lT a./v, ant1 TI,,, Mtr do~~ot.o tho pressure and Mach numbor, respect-ivcly,
~tpst,rr:r~n of 1.11~ shodc w:~vc.
Numerical solut.ions which contain tl~e zone of interaction between n separated
laminar bountlary lnycr and n frictionless suprrsonic &ream were perforrned by V. N.
Vaka arlcl S. I). Rrrtke [I 011, as well xs by 0. R. Burggraf [9J, G. S. SetdJes, S. M.
12ogtlot1olT and 1. E. Vns 193a.J.
111 Ackcrct,, J., I~cldnrnnn, F., and Rott, N.: IJr~tcrs~~chrlngcn an Verdichk~ngsstiissen nnd
~~~II~.~CII~~III.~II
in nc:l~ncll hcwcgtcn Cnsen. Itcport No. 10 of L~IC Inst. of Aerotlynamics
I:'IxII Ziirich 1!)4(i: nee also NACA '1'M 11 13 (1!)47).
121 Applrt,on, .I. I'., uncl I)nvics, fl. J.: A note on tho intcmot.ion of n nortnal slroclc wavc with n
tl~crtnnl hotr~~tlnry Inycr. JAS 25, 722---723 (1958).
[:$I J