Modifications for V 2.0
May 1995

MISES V 2.0 is a fairly major rework from V 1.4.  
Specific major changes are:

A) The inlet/outlet condition specification has been extended
and conceptually simplified.  The inlet/outlet conditions can 
now be specified anywhere in the domain, not just at the grid
inlet/outlet planes.  The outlet condition is also on a true
mixed-out state, rather than some ad-hoc mass-averaged quantity.
The mixed out losses are also computed from this mixed-out state.

The ises.xxx input file has a new format.  The small program 
isconv.f will overwrite an "old" ises.xxx file with the equivalent
"new" ises.xxx file.

Usage:

 % make isconv
 % isconv xxx


B) A modified version of the Abu-Ghannam--Shaw bypass transition model
has been implemented.  The standard AGS model has been found to be
ill-posed (see writeup in  ./doc/ags.ps ).  For high to moderate 
turbulence levels in favorable pressure gradients, this will typically 
cause transition before the standard e^n envelope method.  In fact, 
bypass transition can occur before e^n (TS wave) instability sets in.  
The implementation was an ad-hoc addition to the existing e^n formulation.
When the local Rtheta approaches the AGS critical Rtheta, a very rapid 
fictious growth rate is added to the usual e^n amplication rate so that 
transition is achieved within a small number of BL thicknesses.

C) The internal boundary layer routines have been generally "cleaned up",
and now reside in their own source directory  ./blsrc .  There is now 
one general BL access routine MRCHBL (in blsrc/mrchbl.f), used by MISES 
in various ways.  This routine can also be run as a conventional BL code 
independent of MISES.  A full call list description is in the routine's
comment header.


Modifications for V2.1

A) The block matrix solver has been replaced with a "vector-skyline"
solver which accepts a fairly general matrix form.  This now allows
general offset grids over the inlet and outlet.  

B) The old arcane grid generator has been replaced with a much
more friendly version adapted from the multielement MSES code.
A 2-D panel solution is used to generate the initial streamlines
and to properly block-off the offset grids and the inlet and/or outlet.

C) A new ISMOM=4 option has been implemented, which makes the flow 
isentropic everywhere except where dissipation is active.  Losses are 
now generated only where they should be generated -- i.e. at shocks.
Subsonic regions are guaranteed to be isentropic.

D) Streamtube-thickness variation modes have been implemented.
It is possible to have ISES implicitly determine the outlet
streamtube contraction to match a specified outlet pressure,
for example.

E) The idat.xxx file now contains only the minimum amount of
information needed to define the case flowfield.  Previously, 
the entire contents of STATE.INC were written out up to the array 
dimensions, which made idat.xxx unnecessarily large for smaller
cases.  Secondary variables like Q(I,J) and PI(I,J) are also
no longer written out.  Now there is little drawback to making 
the primary array dimensions in STATE.INC comfortably large.

F) The treatment of Mixed- and Modal-Inverse parameters in EDP
has been cleaned up.  The manual has a more extensive writeup
on these two approaches.


June 18, 1995

Most everything seems to be in order.  All codes compile on
DEC, IRIS, HP, RS machines with no complaints other than
a few nuisance warnings.  The DEC Alpha OSF compiler failed
on a few of the source files with -O2 and above.  Beware
of over-zealous optimizers!

The following cases have just been checked out:

uti
t7
dfvlr


The arltandem is experiencing erratic behavior on the splitter 
wake at the outflow boundary.  I'm not totally happy with the
exit BCs there, but any fix will have to wait until Fall '95.

Modal-Inverse and Mixed-Inverse cases have been also checked out,
for both inviscid and viscous cases.

The streamtube-thickness variation modes are working as expected.


Aug 31, 1995

ISET has been found to have problems with low-solidity blades
which don't overlap (i.e. the stagger distance exceeds the
blade chord).  This "uncovered" gap causes the streamwise
grid node allotment logic to fail.  A simple fix has been 
implemented.


Modifications for v 2.2

The AGS transition correlation Rts(H,Tu) has been re-tuned to better
match the original correlation data.  The ISMOM=4 option has been
made somewhat more reliable.  IPLOT has been cleaned up significantly,
with much nicer streamtube plots, and a new inviscid wake profile plot
menu.


Modifications for v 2.3

a) The MASS (total mass flow) global variable has been replaced with 
the MINL (inlet Mach number) global variable.  This makes the
code much better behaved for cases with inlet Mach near unity.

b) The dissipation coefficient function  mu(M,Mcrit) has been modified
slightly to give better shock-propagation behavior.

c) A "polar" driver program POLAR has been added.  This is essentially
ISES with a DO-loop wrapped around it.  The DO-loop reads in a
specified operating parameter (Mach, P2/Po, etc.) from a spec.xxx file,
converges the solution for that parameter, and writes out the results
to a summary file and a surface-quantity dump file.  It can therefore 
conveniently generate a loss curve or operating line without 
laboriously running ISES manually for each point.  PPLOT and PXPLOT
for plotting the polar output files are not available yet.
Maybe for v 2.4, 2.5, 2.6 ...?

d) ISET now allows the inlet slope to be specified via a leading-edge
Kutta condition, which is an easy way to get a well-behaved grid
near small-radius leading edges.

e) Prescribed losses can now be input via the loss.xxx file.
This contains a ln(Po) vs m' function which is superimposed on
the flow equations.  In effect, this is a nonzero prescribed entropy
function.  See the User's Guide for more info.

f) Supersonic-axial inlet and outlet boundary conditions have
been reformulated.  These actually appear to work now.

g) The Supersonic/subsonic-axial absorbing inlet boundary conditions
have been reformulated to permit nonuniform r(m') and b(m') distributions
over the inlet part of the grid.



Modifications for v 2.4  (unofficial release)

a) An arbitrary geometry definition capability is now supported.
A blade shape can now be defined via a bparm.xxx file instead of 
blade.xxx.  The bparm.xxx file contains an arbitrary set of
geometric parameters which are interpreted by a few black-box 
user-supplied routines BPREAD, BPWRIT, BLDGEN.  MISES doesn't 
care what these routines do internally --- it just uses them
to determine the blade m',theta coordinates from the parameters.

b) There is a new Parametric-Inverse option which allows MISES
to drive the user-defined geometry parameters to obtain a best fit 
to a specified target pressure distribution.  This allows MISES 
to be used as an inverse-design engine with ANY geometry-definition 
system.  This flexibility can be further enhanced by providing
a SUBROUTINE BPCON which allows imposing geometric constraints 
(like area, thickness, bending inertia, etc.) on the 
Parametric-Inverse calculation.

c) An arbitrary number of streamtube thickness b(m') variation modes
is now supported, although the number is still dimensioned to 2 via 
the NBVRX parameter in STATE.INC.  This can be easily changed if desired.
However, the format of the ises.xxx input file will also need to be 
slightly modified to accept more than two modes.  A more general means 
to use these modes will likely be provided in future versions.

d) BLDSET can now read a blade shape in one of four ways:
   i) x,y coordinates from a blade.xxx file (as before)
  ii) x,y coordinates from an idat.xxx file (new)
 iii) geometry parameters from an idat.xxx file (new)
  iv) geometry parameters from a bparm.xxx file (new)

It can write out either the usual blade.xxx file or a bparm.xxx file,
the latter being possible only if options iii) or iv) were used
to in the parameters.

e) Color has been added to more plots to improve visualization.


Addendum  (2/11/97  MD)

f) A new solver routine is now the default (the "old" solver is 
ises/src/solve.old).  The new one uses the black-box routines 
LUDCMP,BAKSUB to perform the block-row inversion operations, 
instead of the usual inline code.  Using these routines has been 
found to give more than a 2x speedup of the MSES airfoil code solver, 
but here it gives only about a 15% speedup -- disappointing, but
I'll take it.  No idea whether this new solver has better or worse 
numerical roundoff behavior.




Modifications for v 2.53   (12/5/98  MD)

The MISES v 2.5 series have a number of very significant modifications
from 2.4 and earlier versions.

* BL Suction can now be imposed in a number of separate "slots"

* Wall cooling/heating can be specified.  Previously, 
  only adiabatic walls could be represented.

* The boundary layer formulation has been significantly revamped,
  primarily because the previous formulation was not very well
  suited to the non-adiabatic case.  The basic profile parameter 
  is now Hb rather than Hk.  The profile and correlation 
  parameterization is described in document  doc/blform.ps

* The e^n and AGS transition criteria have been revised.
  The freestream turbulence level Tu, or the implied Ncrit factor,
  are now referenced to the inlet velocity V1, rather than the
  local velocity Ue(s).  The standard methods, which used Ue,
  imply that the freestream turbulence rms velocities are 
  proportional to Ue, which makes no physical sense.  With the
  new formulation they are assumed to be constant.  The local 
  n(s) variable is still referenced to the local Ue(s), though,
  so that n(s) will decrease as Ue(s) increases simply from the
  changing reference value.  Transition is therefore delayed 
  somewhat from the previous results when the flow accelerates,
  although only intense acceleration like in turbine blading 
  will produce a noticable effect.  The modified formulation
  is described in document  doc/ags2.ps

* The handling of the built-in geometry perturbation modes has
  been cleaned up and generalized.  The modes are now defined
  in a modes.xxx file, rather than being hard-wired.  The mode
  shapes can be plotted in EDP.

* Overall translation,scaling,rotation modes can now be defined
  for each blade.  This nicely complements the geometry perturbation
  modes which cannot move the overall blade.

* Constraints on the inlet and outlet tangential velocities can
  now be imposed.  Imposing the inlet tangential velocity but
  not the total Mach number admits the unique-incidence condition.



Modifications for v 2.56  (20 Aug 04  MD)

* Fixed a number of linearization bugs in the suction implementation



Modifications for v 2.57   (7 Dec 04   MD)

* Changed the way M and Cp axis plot limits are set and changed in IPLOT
* Fixed surface node spacing in ISET so that symm airfoils have symm spacing
* Added Xshock constraint 21, useful for running flaky transonic polar sweeps
* Added Xshock constraint 21 to the list of constraints recognized by POLAR
* Added Xshock,Mshock inputs (optional) to 5th line of ises.xxx file
* Added a few additional parameters to the polar output file


Modifications for v 2.58   (20 Mar 05   MD)

* Added commands to IPLOT for dumping flowfield or BL to text files.
* Removed most of wall heat flux influence in Ctau_EQ expression.
  This gave unrealistically large Ctau_EQ for very cold walls, 
  and unrealistically small Ctau for very hot walls.  The modified 
  expression gives more realistic numbers for non-adiabatic cases.  
  The change has no effect for adiabatic cases.


Modifications for v 2.59   (22 Dec 06   MD)

* Fixed a few OOB errors (crashed with some compilers)
* Slightly extended some of the plot menus
* Changed the default blade side plot colors to blue and red.
  The yellow sometimes didn't show up well on white backgrounds.
* Updated User's Guide


Modifications for v 2.60   (15 Jul 07   MD)

* The text-format read routines can now detect tab characters, which
  are treated as spaces.  Previously, a tab would cause a read error.


Modifications for v 2.61  (5 Nov 07   MD)

* Fixed a serious equation-indexing bug in ISES which showed up 
  only for cases with
   a) more than one blade (e.g. with a splitter), AND 
   b) a shifted grid in the exit, AND
   c) a negative exit slope.
  Any case which didn't meet conditions a,b,c was completely unaffected.
  I've never before run such a combinations of conditions, which is why 
  I never saw the problem.


Modifications for v 2.62  (12 Dec 07  MD)

* Fixed stagnation point displacement thickness updating.
  No effect, except occasionally it would mess up the normal-offset
  vector smoothing routine (DSTELL).

* Fixed stagnation point setup in ISET, which would sometimes end up
  just inside the blade for blades with extremely small LE radii.


Modifications for v 2.63  (30 Jan 08  MD)

* Fixed ISET, which would sometimes fail the grid initialization
  for extreme-turning blade shapes having sharp trailing edges.

* Added output of text file sens.xxx, which contains sensitivities
  of various global variables (S1,S2,p2,omega... etc), with respect to
  global specified parameters (S1spec, p2spec, geometry modes, etc).
  This is in effect a short version of the unformatted dump file sensx.xxx, 
  which also contains sensitivities of the surface pressures, Hk, 
  and geometry.

* Updated and cleaned up the sensitivity-calculation procedure in 
  the LSinv.ps document.  Also updated the main mises.ps document.


Modifications for v 2.64  (15 Jan 09  MD)

* Added re-read/re-plot commands (item 99) to the Surface-plot
  and Contour-plot menus in IPLOT.  These are useful when monitoring
  iteration or optimization progress, since you can replot a new solution
  without needing to quit and then restart IPLOT.


Modifications for v 2.65  (2 Nov 09  MD)

* Added Stanton number Ch(x) plot to surface plot menu.
  This is simply overlaid on the Cf(x) plot as a dashed line.