### Table 2: Test case

"... In PAGE 11: ...able 1: Evaluation criteria .............................................................................24 Table2 : Test case .... ..."

### Table 5: Test cases tested with

### Table 1: Test cases.

"... In PAGE 10: ... 3. The test cases were selected for comparison with results from references [20] and [21] and are presented in Table1 . The symbol num represents the numerical angle of attack, exp the corresponding experimental angle of attack, M1 the freestream Mach number, Re the chord based Reynolds number, x=c the location of the numerically tripped transition to turbulence (activation of numerical turbulence modelling), and ! represents the relaxation parameter in the original version of the code.... In PAGE 12: ...2 RAE-2822 Airfoil The RAE-2822 airfoil is a supercritical airfoil with a moderate amount of aft camber which can pose di culties in achieving VII convergence. In addition, the test cases (summarized in Table1 ) simulate critical transonic ow conditions. Therefore, these cases constitute a challenging validation criterion for the enhanced code.... In PAGE 12: ... Therefore, these cases constitute a challenging validation criterion for the enhanced code. For Case 2 of Table1 convergence of the aerodynamic coe cients (with a tolerance of 0.001 in absolute di erence) has been achieved after 5 PDS iterations using 18 coe cients and after 6 PDS iterations using 10 transpiration coe cients (once again neglecting wake e ects), while the original code required 41 global iterations.... ..."

### Table 1: Test cases.

"... In PAGE 11: ... 3. The test cases were selected for comparison with results from references [20] and [21] and are presented in Table1 . The symbol num represents the numerical angle of attack, exp the corresponding experimental angle of attack, M1 the freestream Mach number, Re the chord based Reynolds number, x=c the location of the numerically tripped transition to turbulence (activation of numerical turbulence modelling), and ! represents the relaxation parameter in the original version of the code.... In PAGE 13: ...2 RAE-2822 Airfoil The RAE-2822 airfoil is a supercritical airfoil with a moderate amount of aft camber which can pose di culties in achieving VII convergence. In addition, the test cases (summarized in Table1 ) simulate critical transonic ow conditions. Therefore, these cases constitute a challenging validation criterion for the enhanced code.... In PAGE 13: ... Therefore, these cases constitute a challenging validation criterion for the enhanced code. For Case 2 of Table1 convergence of the aerodynamic coe cients (with a tolerance of 0.001 in absolute di erence) has been achieved after 5 PDS iterations using 18 coe cients and after 6 PDS iterations using 10 transpiration coe cients (once again neglecting wake e ects), while the original code required 41 global iterations.... ..."

### Table 1: Test cases.

1995

"... In PAGE 16: ...adius, r=1.0 and r=2.0, we can have have di erent densities ( ) for the coe cient matrix, 70 % and 53% respectively. Representative cases shown in Table1 . The values used for l and d were 6.... ..."

Cited by 3

### Table 1. Test Cases.

"... In PAGE 18: ... We will call this the \large quot; test problem. We use a random vector x0 as the true solution of (1) and compute the right-hand side b according to b = Ax0 + e; where e is a random vector with kek2 = relerre kAx0k2: We used the 18 problems from Table1 to test our regularization algorithms. The columns 1 and n show the values of the largest and the smallest sin-... ..."

### Table 1 Test case

1999

"... In PAGE 3: ... In this experiment, concrete, SFRC and ECC (with two diC128erent W/C ratios) were used as the repair mate- rials. Table1 illustrates the combinations of the repair material and the surface condition of test specimens. The numbers of specimens are also shown in Table 1.... ..."

### Table 1: Test cases.

1996

"... In PAGE 4: ... Here the inlet is located at x = ?5D. The jet is pitched and skewed at 45 with Vj=V1 = 2:0 (case 8 in Table1 ). At this stage of the vortex development, the two vortices produced through the rolling up of the ow around the jet have not yet developed into a single vortex[4].... ..."

Cited by 1

### Table 1: Test cases.

1995

"... In PAGE 16: ...adius, r=1.0 and r=2.0, wecanhavehave di#0Berent densities #28#0E#29 for the coe#0Ecient matrix, 70 #25 and 53#25 respectively. Representative cases shown in Table1 . The values used for l and d were 6.... ..."