Experimental Study at Low Supersonic Speeds of a Missile Concept Having Opposing Wraparound Tails

Transcription

1 NASA Technical Memorandum 4582 Experimental Study at Low Supersonic Speeds of a Missile Concept Having Opposing Wraparound Tails Jerry M. Allen and Carolyn B. Watson November 1994

2 NASA Technical Memorandum 4582 Experimental Study at Low Supersonic Speeds of a Missile Concept Having Opposing Wraparound Tails Jerry M. Allen and Carolyn B. Watson Langley Research Center Hampton, Virginia National Aeronautics and Space Administration Langley Research Center Hampton, Virginia November 1994

3 This publication is available from the following sources: NASA Center for AeroSpace Information National Technical Information Service (NTIS) 8 Elkridge Landing Road 5285 Port Royal Road Linthicum Heights, MD Springeld, VA (31) (73)

4 Abstract A wind-tunnel investigation has been performed at low supersonic speeds (at Mach numbers of 1.6, 1.9, and 2.16) to evaluate the aerodynamic characteristics of a missile concept capable of being tube launched and controlled with a simple one-axis canard controller. This concept, which features an axisymmetric body with two planar canards and four wraparound tail ns arranged in opposing pairs, must be in rolling motion to be controllable in any radial plane with the planar canards. Thus, producing a constant rolling moment that is invariant with speed and attitude to provide the motion is desirable. Two tail-n shaping designs, one shaved and one beveled, were evaluated for their eciency in producing the needed rolling moments, and the results showed that the shaved ns were much more desirable for this task than the beveled ns. Introduction Tactical missiles that do not require high maneuverability (air-to-ground or antitank) can make use of more simple stability and control techniques than are required for missiles needing high maneuverability (air-to-air or surface-to-air). One such simplied technique is to have the missile airframe rolling in ight. This spinning motion not only enhances stability but also allows the missile to be controlled in any radial plane by small planar canards driven by a single-axis controller (i.e., no dierential deections). Another desirable feature for this class of missile is the ability to fold all the ns, which could include canards, wings, or tails, into or around the body for compact tube storage. The ns would then be deployed as the missile exits the launch tube. Examples of current systems using folding ns can be found in reference 1 and include: (1) the Redeye missile, which has ns that fold rearward; (2) its replacement, the Stinger missile, which has short-span tail ns that fold into a necked-down region of the body; and (3) the TOW missile, which has wings that fold rearward and tails that fold forward. Another method of accomplishing compact tube storage for tail ns is to have them wrapped around the body circumferentially before and during launch. The aerodynamics of wraparound tail ns is thus of great interest for this class of missile and has been the subject of numerous studies for many years by the Department of Defense (refs. 2{4), NASA (refs. 5 and 6), and others (refs. 7{9). The traditional wraparound-n conguration has four curved ns mounted in a cruciform arrangement, with each n curving in the same direction and wrapped around approximately 25 percent of the body circumference before deployment. The previous studies cited in the aforementioned references were all conducted using this traditional arrangement, which is illustrated in the sketch in gure 1(a). This arrangement produces a nonsymmetric conguration and is known to produce nonlinear and sometimes erratic aerodynamics, especially in rolling moment, even at small angles of attack. (See refs. 2{5.) One current system that employs the traditional wraparound folding arrangement in a design consisting of three tail ns is the Dragon missile (ref. 1). In the present study, a novel n arrangement designed to overcome these undesirable aerodynamic features is investigated. This arrangement has wraparound tail ns mounted in opposing pairs, as shown in the sketch in gure 1(b). When unopened, the opposing n pairs overlap and t inside a body cavity to allow storage within a constantdiameter launch tube. This arrangement has several potential aerodynamic advantages over the traditional wraparound arrangement, and these are listed as follows: 1. Because of overlapping, the n spanwise arc length is not limited to 25 percent of the body circumference. 2. Symmetry on the model is established, which should eliminate some of the undesirable aerodynamic characteristics of the traditional wraparound ns. 3. Deployment of these ns by blasting them into the open position can be accomplished by using two side-mounted scarfed nozzles located underneath the overlapping ns, whereas four such nozzles would be required for the traditional wraparound ns.

5 This opposing-pair arrangement retains the wraparound concept while producing symmetry on the model. Because all the n surfaces are mounted streamwise in a symmetric arrangement and dierential deections are not permitted by the single-axis canard controller, no inherent roll is expected on the conguration. This arrangement thus does not produce the desirable steady roll rate that is necessary for this conguration to be controlled by the planar canards. One method of producing the necessary roll is to shape the leading and trailing edges of the tail ns. In previous studies, beveling of the n leading edges has been used. In this paper, both shaved and beveled leading edges are examined for their eectiveness in creating this desired roll. The purpose of this paper is to experimentally examine at low supersonic speeds the static aerodynamic stability and control characteristics of a tactical missile concept that incorporates the planar canards, opposing pairs of wraparound tails, and tailshaping features mentioned previously. This conguration was designed for a peak Mach number of about 2.. This force and moment test was conducted in the low Mach number test section of the Langley Unitary Plan Wind Tunnel at Mach numbers of 1.6, 1.9, and 2.16 at a unit Reynolds number of 2: per foot. Symbols The measurements and calculations in this experiment are made in U. S. Customary Units, and force and moment coecients are referred to the body-axis system. The capitalized expression in parentheses next to the symbol is the computer-printout equivalent of that symbol that is used in the aerodynamic data presented in tables 2{28. C A (CA) axial-force coecient, F A qs ref C A;C (CAC) chamber axial-force coecient, F A;C qs ref C l (CLB) rolling-moment coecient, M X qs ref d C m (CM) pitching-moment coecient, M Y qs ref d C N (CN) normal-force coecient, C n (CNB) yawing-moment coecient, M Z qs ref d F N qs ref C Y (CY) side-force coecient, d F A F A;C F N F Y M M X M Y M Z body diameter, 2.6 in. model axial force, lb chamber axial force, (p c p1)s ref,lb model normal force, lb model side force, lb F Y qs ref free-stream Mach number model rolling moment, in-lb model pitching moment, in-lb model yawing moment, in-lb p c chamber pressure, lb/in 2 p1 free-stream static pressure, lb/in 2 q r S ref free-stream dynamic pressure, lb/in 2 radius of curvature, in. model reference area, d2 4, 5.31 in 2 (ALPHA) model angle of attack, deg canard-deection angle, positive leading edge up, deg model roll angle, positive right wing down, deg Conguration code: B body C1 canard with trailing-edge plate C2 canard without trailing-edge plate T1 tail ns with shaved edges T2 tail ns with beveled edges Abbreviations: Conf. conguration dia. diameter MS model station, in. rad. radius Tests and Procedures Model The baseline conguration consists of an axisymmetric body with a blunt nose, planar canards, and 2

6 wraparound tails arranged in opposing pairs. Figure 2 shows a photograph of this baseline conguration mounted in the low Mach number test section of the Langley Unitary Plan Wind Tunnel. A three-view sketch showing pertinent dimensions of the model is presented in gure 3. The cavities in the body between the opposing pairs of wraparound tails were designed to simulate side-mounted scarfed nozzles and to allow room for folding of the opposing pairs of tail ns. In this investigation, in which only xed-n hardware was used, the ns were attached to the body to simulate an unfolded conguration. For conguration buildup data, the tail ns were removed and the mounting holes were lled, but no attempt was made to fair over the body cavities. The canards of the baseline conguration had small plates attached perpendicularly along the trailing edges. These plates were intended to simulate a free-oscillation suppression device for these canards. The canards would have a tendency to oscillate unless restrained aerodynamically because the hinge line was located near the leading edge and the canards were free to oscillate except during roll orientations when they would be actuated. No attempt was made in this study to allow the canards to oscillate as they would in ight, and thus dynamic eects could not be measured. As a result, no conclusions can be drawn concerning the eciency of these plates as free-oscillation suppression devices. The forward hinge-line location on these canards was designed to allow them to be folded aft into the body for compact storage. An alternate set of canards without the trailing-edge plate was tested to study the eects of the plate. Canard dimensions are shown in gure 4, and a photograph of both sets of canards is shown in gure 5. Each tail n of the baseline conguration contained a shallow shaved region along its leading and trailing edges that was designed to produce the rolling moments needed for control of this conguration with the planar single-axis canards. For each set of opposing ns, one n was made slightly smaller than its mate to simulate the ability of those ns to fold together around the body for storage. Sketches of the aft end of the model and of the baseline tail ns are shown in gure 6. The shaved regions on the tails are shown as the shaded areas in gure 6. The streamwise slope of these regions was about 4, which resulted in the length of the shaved region ranging from about 45 percent of the n chord at the root to about 1 percent at the tip. Fins 1 and 3 were shaved near the leading edge of the convex surface, as seen in the gure, and near the trailing edge of the concave surface (not shown). Fins 2 and 4, on the other hand, were shaved in the reverse pattern so that rolling moments in the same direction would be generated on all four ns. Previous research (ref. 2) on traditional wraparound tails indicated that incorporating sharp bevels along the leading edges does not produce reliable rolling moments. To investigate the relative eciency of the shaved-n design, an alternate set of tails was tested that incorporated sharp 45 bevels along the leading edges. The length of the bevel ranged from about 2.8 percent of the tail chord at the root to about 8.4 percent at the tip. For these alternate ns, the bevels were located on the leading edge only and were arranged to generate rolling moments in the same direction on all four ns. A photograph of the shaved and beveled ns is shown in gure 7. Wind Tunnel This investigation was conducted in the low Mach number test section of the Langley Unitary Plan Wind Tunnel. This tunnel is a variable-pressure, continuous-ow facility with two test sections that cover a Mach number range from 1.47 to Mach number is controlled by an asymmetric sliding block which forms the oor of the nozzle and test section. The low-speed test section has a Mach number range from 1.47 to 2.9. The test section is approximately 4-ft wide by 4-ft high by 7-ft long, and it is formed by the downstream section of the nozzle. A more detailed description of this facility can be found in reference 1. A schematic drawing of the Langley Unitary Plan Wind Tunnel complex, taken from reference 1, is shown in gure 8. Measurements and Corrections Aerodynamic forces and moments on this model were measured by a six-component strain gauge balance that was housed inside the body of the model. This balance had a nominal rated accuracy of 6:5 percent of the full-scale value on each component. For the test conditions of this study, this resulted in the following accuracies in the data coef- cients: C N = 6:9, C A = 6:24, C m = 6:116, C l = 6:12, C n = 6:46, and C Y = 6:6. The balance was mounted on a sting, which was, in turn, attached to the permanent tunnel-support mechanism downstream of the model. (See g. 2.) Model angle of attack was corrected for deection of the balance and sting due to aerodynamic loads and for test section ow misalignment. 3

7 Pressures inside the model were measured by two pressure tubes located inside the balance chamber. The model internal diameter was beveled to the outer diameter at the base of the body to allow the internal pressure to act over the entire base. (See g. 6.) Axial-force data were corrected for the dierence between the internal chamber pressure and freestream static pressure (C A;C ). The model moment center was located on the body centerline at 53.1 percent of the body length, or in. aft of the model nose. To induce boundary-layer transition to turbulent ow, transition strips were applied to the model by using the technique established in reference 11. These strips consisted of No. 5 sand grains (.128 in.) sprinkled in acrylic plastic. The strips were about.62 in. wide and were located about 1.2 in. aft of the nose and.4 in. aft of the leading edges (measured streamwise) on all n surfaces. Test Conditions This investigation was conducted primarily at free-stream Mach numbers of 1.6 and 1.9, although additional tail-n shaving eects were obtained at a Mach number of For all runs, the Reynolds number was per foot, and the model angle of attack ranged from about 4 to 2. In ight this conguration would be in continuous rolling motion, but for this investigation, the model was tested in a static condition in which the roll angle was xed. The test was conducted primarily at model roll angles of,45, and 9, with some additional testing of the baseline conguration at 22:5 and 67:5. Canard-deection angles ranged from 15 to 15 in 5 increments. Presentation of Data The six-component model force and moment data obtained in this investigation were reduced to coecient form in the body-axis system and are tabulated in this paper. Table 1 shows a summary of the data locations in the subsequent tables as a function of the test variables, and the data listings are contained in tables 2{28. Selected data from these tables have been plotted and are analyzed in the following sections of the paper to explore the eects of the test variables. Results and Analysis Analyses of the data obtained in this investigation are made by using plots of selected data from tables 2{28. The eects of the test variables are examined by analyzing graphs of normal-force, axialforce, pitching-moment, and rolling-moment coecients as a function of angle of attack. Because this conguration has planar canards and is expected to y at angles of attack below about 1, the lateral loads are expected to be small, and thus no analyses of the side-force and yawing-moment data are made in this paper. In gures 9{13, all four of the primary aerodynamic parameters are plotted on the same page, and all graphs are plotted to the same scale to facilitate comparisons among the test variables. Figure 14 is a summary of the rolling-moment coecients plotted with magnied scales. Component Buildup The eects of the model components that make up the complete baseline conguration (BC1T1), are analyzed by comparing component buildup data at = with undeected canards for M =1:6 and 1.9, as seen in gure 9. These data show that the rolling moment on this conguration is coming from the tail ns. The body and canards do not contribute to the rolling moment because of their symmetry. The pitching-moment data show that the most unstable combination of components is the body-canard combination, as would be expected, and that the body alone is also unstable. In contrast, the body-tail combination is very stable except at the higher angles of attack. The body-canardtail conguration is slightly stable at M =1:6 and slightly unstable at M =1:9. Hence, for the expected supersonic ight regime of this conguration, near-neutral stability exists, and thus this conguration would not need large control surfaces to provide maneuverability. The addition of the canards to the body results in small increases in both normal and axial forces, whereas the addition of the tails results in a much larger increase. The largest normal and axial forces were created by the complete body-canard-tail conguration. Eect of Canard Trailing-Edge Plate Figure 1 shows the eects of the canard trailingedge plate for = and = at M =1:6 and 1.9. In order to isolate the plate eects, tail-o data for the two canard designs are shown. The only noticeable eect of the plate occurs in the axial-force data. The addition of the plate adds only about.2 to the axial-force coecient, and this value stays 4

8 fairly constant with angle of attack and Mach number. The other parameters show a negligible eect of the plate. Eect of Roll Angle Because this conguration is designed to spin in ight, the eect of roll angle on the aerodynamics is one of the major parameters of interest. Figure 11 shows the eect of roll angle on the baseline conguration at M =1:6 and =. Roll angle is seen to have a strong eect on pitching moment. A systematic change in stability is shown in the data as the model is rolled from to 9. The pitching-moment curve at =9 is, in fact, similar to that seen in the body-tail data shown in gure 9(a). At =9, the canards are in the vertical plane and thus produce no normal force. Hence, the conguration at this roll angle gives pitching moments similar to those seen in the body-tail combination. On the other hand, roll angle has little eect on the normal-force and axial-force coecients. In fact, the small dierences in axialforce coecient with roll angle seen in gure 11 were traced to dierences in the measured chamber pressures. The rolling-moment coecients stay in the range from.4 to.1 at all roll angles up to about =8, but at about =1, the curves sharply diverge. The rolling moments at =22:5 at the higher angles of attack were the largest measured in this investigation, and these curves begin to diverge at an angle of attack where vortices should begin to develop over the body and canards. Thus, the erratic trends in rolling moment above =1 are probably caused by the tail ns passing through vortices as the model is rolled from to 9. Because this conguration was designed to y at <1, these erratic trends are not important in this study. Eect of Canard Deection As shown in table 1, the canards were deected from 15 to 15 in 5 increments in this study. For clarity, only the largest deection angles (615 ) are examined in this section. Figure 12 shows the eects of canard deection for the baseline conguration at = for M =1:6 and 1.9. Positive deection is dened as leadingedge up. The normal-force curves show that positive deection produces only slightly more normal force than the undeected canards, and that negative deection produces slightly less. At =, both the positive and negative canard deections show the same increase in axial force caused by the deected canards, although the trends of the two curves are dierent with angle of attack. At the lower angles of attack, the positive-deection data show increasing axial force, whereas the negative deection data show decreasing values. This trend is due to the fact that for positive canarddeection angles, the magnitude of the eective de- ection angle () is increasing, whereas it is decreasing for negative. The eective deection angle, as determined by the method of reference 12, is about 1:45 + :92 for this conguration. The pitching-moment data show similar trends for all deection angles, but the curves are displaced above and below the zero-deection data. The positive deection angle, producing a more positive normal force, results in a higher pitching moment; whereas the negative deection-angle data show a negative increment in pitching moment. A noticeable break occurs in the curve for =15 at 8, which is probably due to canard stall as reected in the C N loss (with the eective canard angle being about 25 ). This break is also seen in the rollingmoment data in which one canard may stall rst, but with the exception of this break, very little eect of canard deection is seen in the rolling-moment data. The pitching-moment data in gure 12 also show that this conguration is almost neutrally stable at both test Mach numbers throughout the expected ight angle-of-attack range ( <1 ), and therefore the small canards on this conguration should be sucient to provide controllability. Eect of Tail Shaping The most interesting aspect of this conguration is the shaping of the tail ns for producing the rolling moments that are needed for control of this conguration. These shaping eects are examined in this section by comparing body-tail data from the two tail designs, termed shaved and beveled. Also, body-alone data are shown to illustrate the individual dierences caused by the two tail designs. These comparisons, which are shown in gure 13 at =, are the only comparisons in this study that include data at M =2:16. (The peak Mach number of this conguration is about 2..) Very little eect of n shaping is seen in the normal-force and pitchingmoment data. The beveled ns show higher axial force than the shaved ns throughout the angle-ofattack range. These trends are similar at all the test Mach numbers. The rolling-moment data show a strong eect of n shaping, and the eect changes with Mach number. As noted in reference 2, the largest pressure 5

9 dierences between the concave and convex surfaces of wraparound ns occurred near the leading edge, and geometry changes in this leading-edge region could possibly alter the n loading. Changes in rolling moment were obtained in the present study as a result of the n shaping in both the leading- and trailing-edge regions. In order to see this eect more clearly, the rollingmoment data for the two n-shaping designs at all three test Mach numbers have been combined in gure 14, with two primary eects being apparent from this gure. One eect is that the shaved ns produce much larger rolling moments than are produced by the beveled ns. In fact, the rolling moments for the beveled ns at the lowest test Mach number are in the opposite direction from that desired. This \roll-reversal" eect with decreasing Mach number was also reported in reference 2 with beveled leading edges, and it was explained by the variation of measured pressures in the leading-edge region. The second eect is that the shaved ns produce rolling moments that are virtually constant with Mach number at angles of attack up to about 1, whereas the beveled ns produce large variations with both parameters. The variations with Mach number for beveled wraparound ns are similar to those reported in reference 2, which used the traditional cruciform arrangement. Because producing adequate rolling moments that do not vary with speed or attitude is highly desirable for a rolling missile such as the present con- guration, the conclusion can be made that the present conguration would be much simpler to control with the shaved ns than with the beveled ns that were tested in this investigation. By using the roll-damping calculation method described in reference 13, the rolling moments produced in this study by the shaved ns were estimated to be sucient to generate the roll rates necessary for this conguration to be controllable in ight. A signicant feature is that the favorable rollingmoment characteristics needed for the control of this conguration were produced on the tail ns by n shaping and not by the opposing-pair, wraparound tail-n arrangement. Thus, no conclusion can be drawn in this study regarding the aerodynamics of the tail-n arrangement. Concluding Remarks An experimental investigation has been performed at low supersonic speeds (at Mach numbers of 1.6, 1.9, and 2.16) to evaluate the aerodynamic characteristics of a missile concept capable of being tube launched and controlled with a simple oneaxis canard controller. The concept features an axisymmetric body with two planar canards and four wraparound tail ns arranged in opposing pairs. The small canards on this conguration should be sucient to provide controllability because this con- guration was found to be almost neutrally stable. Also, the small vertical plate attached to the trailing edge of each canard, which was intended to simulate a free-oscillation suppression device in ight, increased the axial force slightly, but otherwise it had a negligible eect on the static aerodynamics measured in this study. This concept must be in rolling motion in ight to be controllable in any radical plane with the planar canards. Thus, producing a constant rolling moment that is invariant with speed and attitude to provide this motion is desirable. Two tail-n shaping designs, one shaved and one beveled, were evaluated for their eciency in producing the needed rolling moments. The results showed that the shaved ns were much more desirable for this task than the beveled ns and that the shaved ns produced sucient rolling moments needed for controllability. No conclusion can be drawn regarding the aerodynamics of the opposing-pair arrangement of the wraparound tail ns of the present conguration. NASA Langley Research Center Hampton, VA August 31, 1994 References 1. The World's Missile Systems. Seventh ed., Edward L. Korb, ed., Pomona Division, General Dynamics Corp., Apr Holmes, John E.: Wrap-Around Fin (WAF) Aerodynamics. Proceedings of 9th Navy Symposium on Aeroballistics, Volume 1, Appl. Phys. Lab., Johns Hopkins Univ., May 1972, pp. 13{ Dahlke, C. W.: The Aerodynamic Characteristics of Wrap-Around Fins at Mach Numbers of.3 to 3.. Rep. RD-77-4, U.S. Army Missile Command, Oct. 15, (Available from DTIC as AD A ) 4. Washington, William D.: Experimental Investigation of Rolling Moment for a Body-Wing-Tail Missile Conguration With Wrap Around Wings and Straight Tails at Supersonic Speeds. AIAA , Aug Fournier, Roger H.: Supersonic Aerodynamic Characteristics of a Series of Wrap-Around-Fin Missile Congurations. NASA TM X-3461,

10 6. Sawyer, W. C.; Monta, W. J.; Carter, W. V.; and Alexander, W. K.: Control Characteristics for Wrap- Around Fins on Cruise Missile Congurations. J. Spacecr. &Rockets, vol. 19, no. 2, Mar.{Apr. 1982, pp. 15{ Lucero, E. F.: Subsonic Stability and Control Characteristics of Congurations Incorporating Wrap-Around Surfaces. J. Spacecr. & Rockets, vol. 13, no. 12, Dec. 1976, pp. 74{ Catani, Umberto; Bertin, John J.; De Amicis, Roberto; Masullo, Sergio; and Bouslog, Stanley A.: Aerodynamic Characteristics for a Slender Missile With Wrap-Around Fins. J. Spacecr. & Rockets, vol. 2, no. 2, Mar.{ Apr. 1983, pp. 122{ Eastman, Donald W.; and Wenndt, Donna L.: Aerodynamics of Maneuvering Missiles With Wrap-Around Fins. AIAA , Oct Jackson, Charlie M., Jr.; Corlett, William A.; and Monta, William J.: Description and Calibration of the Langley Unitary Plan Wind Tunnel. NASA TP-195, Stallings, Robert L., Jr.; and Lamb, Milton: Eects of Roughness Size on the Position of Boundary-Layer Transition and on the Aerodynamic Characteristics of a 55 Swept Delta Wing at Supersonic Speeds. NASA TP-127, Hemsch, Michael J.: Component Build-Up Method for Engineering Analysis of Missiles at Low-to-High Angles of Attack. Tactical Missile Aerodynamics: Prediction Methodology, Michael R. Mendenhall, ed., AIAA, 1992, pp. 115{ Mikhail, Ameer G.: Roll Damping for Finned Projectiles Including: Wraparound, Oset, and Arbitrary Number of Fins. AIAA , Aug

11 Table 1. Summary of Data Locations Table for of M Conguration, deg 22: : BC1T1 2(a) 2(b) 2(c) 2(d) 2(e) 5 3(a) 3(b) 3(c) 5 4(a) 4(b) 4(c) 1 5(a) 5(b) 5(c) 1 6(a) 6(b) 6(c)? 15 7(a) 7(b) 7(c) 7(d) 7(e) y 15 8(a) 8(b) 8(c) 8(d) 8(e) BC1 9(a) 9(b) 9(c) BC2 1(a) 1(b) 1(c) BT1 11(a) 11(b) 11(c) BT2 12(a) 12(b) 12(c) B 13(a) 13(b) 13(c) 1.9 BC1T1 14(a) 14(b) 14(c) 5 15(a) 15(b) 15(c) 5 16(a) 16(b) 16(c) 1 17(a) 17(b) 17(c) 1 18(a) 18(b) 18(c)? 15 19(a) 19(b) 19(c) y 15 2(a) 2(b) 2(c) BC1 21(a) 21(b) 21(c) BC2 22(a) 22(b) 22(c) BT1 23(a) 23(b) 23(c) BT2 24(a) 24(b) 24(c) B 25(a) 25(b) 25(c) 2.16 BT1 26(a) 26(b) 26(c) BT2 27(a) 27(b) 27(c) B 28(a) 28(b) 28(c) 8

12 Table 2. Data for Conguration BC1T1 at M =1:6 and = (a) = 4:32 :8516 :5987 :2581 :836 :258 :135 :1553 :31 :67 :5838 :39 :884 :53 :95 :1495 3:69 :7285 :628 :1961 :826 :699 :136 :1552 8:69 1:851 :6465 :355 :786 :822 :2 :1734 9:68 2:778 :6387 :4968 :824 :164 :33 : :72 2:6223 :6351 :528 :94 :1345 :298 : :71 3:8651 :6321 :134 :849 :218 :562 : :68 5:4482 :6285 :241 :784 :2769 :964 :2148 (b) =22:5 4:28 :8299 :6289 :4678 :76 :3569 :531 :1332 :32 :359 :694 :265 :896 :454 :51 :1235 3:73 :7499 :6314 :3835 :732 :267 :45 :133 7:78 1:699 :6577 :7599 :417 :383 :1476 :1554 9:7 2:169 :663 1:1184 :163 :4416 :1831 :166 11:77 2:6723 :6631 1:3932 :458 :596 :2555 : :73 3:8153 :6643 1:133 :185 1:182 :239 : :77 5:1757 :6388 :2625 :3995 2:12 :465 :2169 (c) =45 4:15 :7627 :6238 :9148 :661 :5861 :172 :131 :2 :18 :657 :225 :886 :56 :122 :1261 3:81 :7534 :6318 :81 :719 :4497 :598 :1325 7:86 1:6272 :669 1:7696 :386 :6314 :1555 :1556 9:82 2:1193 :6661 2:2819 :362 :6335 :218 : :85 2:6425 :6726 2:6357 :424 :6921 :2499 : :86 3:8136 :6881 2:9333 :574 :8919 :268 :236 19:79 5:1797 :651 2:6512 :1135 1:725 :1497 :23 9

13 Table 2. Concluded (d) =67:5 4:12 :756 :6322 1:375 :761 :4988 :237 :1286 :4 :217 :695 :3 :91 :516 :248 :1241 3:98 :7812 :6352 1:2952 :777 :3765 :418 :136 7:94 1:5987 :6826 2:4984 :857 :4669 :797 :1518 9:96 2:724 :6844 3:991 :12 :378 :1252 :176 11:93 2:5588 :6854 3:52 :1477 :337 :178 : :92 3:6619 :6764 3:5196 :1919 :24 :38 :286 19:94 5:25 :6613 2:9984 :1853 :475 :6764 :2333 (e) =9 3:99 :7247 :6278 1:5136 :936 :1374 :532 :1266 :11 :458 :6114 :513 :915 :736 :417 :1232 4:7 :876 :642 1:5722 :949 :27 :236 :1352 8:8 1:637 :6826 2:9469 :18 :54 :378 :1685 1:7 2:19 :6881 3:5425 :151 :711 :385 : :9 2:695 :685 3:9598 :179 :282 :347 : :1 3:7491 :673 3:889 :1211 :531 :524 :1998 2:8 5:1294 :6543 3:4656 :1371 :2365 :424 :2148 1

14 Table 3. Data for Conguration BC1T1 at M =1:6 and =5 (a) = 4:26 :7176 :6137 1:412 :823 :338 :28 :1565 :24 :826 :6312 :7632 :93 :79 :13 :1575 3:77 :863 :649 :647 :856 :655 :2 :1679 7:77 1:614 :6755 :8834 :635 :12 :228 :189 9:71 2:174 :6915 :2533 :793 :849 :34 :1995 9:79 2:237 :6895 :2279 :812 :971 :369 :226 11:74 2:7227 :695 :551 :94 :1616 :463 :27 15:75 3:9193 :6914 :32 :852 :2138 :515 : :72 5:54 :6889 :5772 :622 :315 :955 :2257 (b) =45 4:5 :684 :6226 1:4146 :629 :926 :7 :1454 :8 :84 :625 :5216 :879 :4337 :1191 :1472 3:96 :8519 :6459 :2839 :597 :9664 :1615 :1612 7:97 1:713 :6759 1:164 :285 1:253 :2982 :1782 9:93 2:2152 :6884 1:8273 :139 1:77 :3421 : :96 2:7418 :6995 2:237 :135 1:116 :4192 :236 15:91 3:8728 :722 2:5492 :16 1:1867 :436 : :91 5:2285 :6818 2:1451 :1689 1:8165 :418 :2548 (c) =9 4:3 :7465 :6466 1:5282 :924 :5895 :1445 :1297 : :198 :6259 :16 :96 :6554 :1515 :13 4:6 :7929 :6498 1:5461 :952 :7 :1126 :1388 8:1 1:6174 :6961 2:9416 :1112 :6689 :847 :1658 1:7 2:953 :724 3:5447 :1213 :5756 :154 : :97 2:5656 :6964 3:9655 :1292 :5743 :1199 : :96 3:6791 :6824 3:9447 :1279 :5863 :1958 :216 2:3 5:844 :654 3:5393 :1355 :5388 :3415 :

15 Table 4. Data for Conguration BC1T1 at M =1:6 and = 5 (a) = 4:28 :9293 :632 :3584 :884 :82 :222 :153 :26 :155 :619 :4856 :927 :47 :1 :1494 3:73 :6345 :5993 :7495 :86 :736 :198 :1524 7:69 1:4733 :633 :8893 :832 :92 :292 :1666 9:74 2:11 :63 1:785 :89 :19 :375 : :73 2:5293 :6161 1:518 :945 :1395 :364 : :65 3:7854 :6119 :5363 :924 :29 :597 : :74 5:3896 :597 :855 :698 :3511 :19 :2156 (b) =45 4:28 :8783 :6365 :545 :613 :9578 :1136 :1546 :25 :95 :6117 :3365 :912 :457 :738 :1489 3:77 :6648 :6135 1:185 :712 :741 :119 :1532 7:69 1:514 :6449 2:1551 :374 :333 :59 :1729 9:79 2:167 :659 2:6537 :287 :4244 :859 :185 11:73 2:4922 :6492 2:938 :364 :4421 :1212 : :74 3:6763 :645 3:2285 :874 :734 :748 : :75 5:615 :6145 2:691 :1361 1:3941 :113 :2464 (c) =9 4:23 :791 :657 1:5995 :943 :611 :691 :138 :28 :276 :6289 :834 :931 :5932 :132 :1287 3:72 :7194 :6439 1:494 :941 :5281 :143 :1415 7:7 1:5498 :6947 2:8546 :943 :474 :69 :1643 9:78 2:35 :754 3:4599 :874 :4753 :733 : :71 2:4943 :736 3:933 :817 :4848 :711 : :68 3:5868 :6892 3:9745 :11 :3385 :116 : :75 4:9795 :66 3:4997 :138 :99 :2284 :

16 Table 5. Data for Conguration BC1T1 at M =1:6 and =1 (a) = 4:33 :6468 :6285 1:723 :855 :669 :48 :161 :31 :22 :6538 1:3834 :91 :24 :81 :1576 3:74 :9962 :6858 1:212 :932 :1124 :378 :1588 7:75 1:6541 :7115 1:5939 :525 :2 :146 : :71 2:836 :7453 :361 :97 :2199 :626 : :7 3:9198 :7366 :4432 :92 :292 :556 :218 19:75 5:5245 :7289 :7247 :795 :3767 :1176 :2187 (b) =45 4:28 :6825 :6299 2:84 :471 :2546 :1621 :1553 :25 :138 :6432 1:156 :885 :8435 :214 :1555 3:73 :8891 :6667 :2665 :577 1:3225 :2734 :162 7:72 1:6895 :717 :577 :114 1:3556 :3769 : :73 2:728 :7354 1:838 :81 1:14 :5773 : :7 3:8666 :7392 2:2929 :294 1:3574 :5634 : :77 5:1643 :7176 1:9257 :2227 1:5392 :6457 :2524 (c) =9 4:29 :799 :6785 1:6397 :116 1:1767 :2848 :142 :32 :311 :6631 :897 :94 1:2456 :2953 :1385 3:71 :7285 :6746 1:4185 :788 1:2429 :2794 :1444 7:76 1:5697 :7197 2:932 :11 1:1634 :215 : :71 2:5156 :7333 3:938 :1438 :9554 :27 : :71 3:614 :7145 3:9451 :1336 :9964 :3679 :251 19:74 5:537 :6913 3:6596 :1412 :8294 :6587 :

17 Table 6. Data for Conguration BC1T1 at M =1:6 and = 1 (a) = 4:3 1:53 :6893 :9658 :916 :797 :129 :1534 :29 :259 :6591 1:1193 :944 :65 :41 :1543 3:72 :5592 :6358 1:4276 :891 :1395 :391 :1625 7:75 1:489 :631 1:625 :899 :1324 :483 : :73 2:4378 :667 1:6798 :868 :957 :34 :19 15:76 3:7247 :5979 1:126 :897 :2424 :784 :228 19:76 5:347 :5745 :5115 :761 :3315 :131 :219 (b) =45 4:28 :9696 :6736 :719 :534 1:3759 :2144 :1574 :28 :192 :6425 :7742 :92 :872 :1661 :1578 3:73 :625 :6298 1:6754 :564 :3184 :192 :1626 7:69 1:4479 :6563 2:6268 :118 :364 :183 : :68 2:423 :6414 3:3172 :72 :1115 :546 :298 15:71 3:5768 :6194 3:4788 :164 :4889 :477 : :74 5:627 :5932 2:9595 :944 1:161 :333 :2569 (c) =9 4:26 :7923 :6742 1:635 :831 1:2149 :269 :1374 :31 :352 :666 :1175 :954 1:2331 :2313 :1375 3:76 :7485 :6788 1:4637 :1 1:1611 :278 :1412 7:68 1:5647 :7133 2:8811 :883 1:612 :1781 : :77 2:5294 :723 3:8989 :666 :9432 :1942 :196 15:72 3:6238 :787 3:9151 :116 :7716 :2865 :27 19:76 5:323 :6913 3:624 :1433 :3251 :5161 :225 14

18 Table 7. Data for Conguration BC1T1 at M =1:6 and =15 (a) = 4:28 :5919 :6481 2:5531 :89 :88 :67 :1673 :34 :2776 :6824 1:9997 :93 :62 :111 :164 3:75 1:985 :7223 1:651 :931 :1128 :421 :1654 7:77 1:7278 :7552 2:238 :439 :37 :325 :178 9:75 2:3188 :7624 1:164 :73 :641 :393 : :71 2:8355 :788 :7166 :895 :1752 :63 :198 15:73 3:9637 :7781 :5425 :832 :1713 :664 :255 19:78 5:5995 :7753 :9682 :791 :2492 :693 :2294 (b) =22:5 4:31 :618 :681 2:6236 :297 :2277 :1438 :1358 :23 :2736 :712 1:8591 :912 :6493 :185 :1344 3:67 1:471 :7477 1:4132 :696 :8886 :2352 :1364 7:66 1:7691 :7846 1:1995 :771 :759 :345 :1558 9:68 2:3366 :7927 :3847 :36 :934 :354 : :69 2:8619 :827 :651 :829 :9381 :485 : :71 3:8968 :7978 :1499 :3518 1:257 :5458 : :69 5:2715 :7931 :4922 :451 1:418 :6225 :283 (c) =45 4:27 :6432 :6752 2:587 :35 :6277 :2585 :1551 :3 :1972 :6913 1:4679 :99 1:275 :2959 :1539 3:78 :9728 :7251 :6239 :459 1:6835 :3676 :1572 7:74 1:7388 :7696 :1837 :1 1:616 :48 :1687 9:68 2:2363 :7743 :9576 :541 1:5215 :5656 :182 11:71 2:7691 :7875 1:5558 :121 1:3142 :769 : :77 3:9124 :85 2:681 :1151 1:337 :7896 : :72 5:1838 :7797 1:7766 :2186 1:1812 :8339 :

19 Table 7. Concluded (d) =67:5 4:28 :7122 :7133 2:3139 :742 1:2317 :3528 :148 :26 :194 :7128 :8269 :913 1:7165 :3925 :1341 3:74 :8369 :7445 :4388 :415 2:46 :4213 :1379 7:76 1:6569 :789 1:7722 :389 1:8271 :4687 :1547 9:67 2:754 :776 2:2795 :94 1:7248 :497 : :72 2:628 :7996 2:9937 :1465 1:4118 :5625 : :68 3:6579 :798 3:2812 :159 1:894 :8824 : :72 5:22 :7549 2:926 :1774 :183 1:4948 :2392 (e) =9 4:24 :7965 :7321 1:6121 :1189 1:7275 :4112 :1411 :3 :396 :778 :866 :915 1:875 :415 :1372 3:66 :7232 :7224 1:4343 :634 1:7457 :42 :1434 7:75 1:5662 :7637 2:945 :911 1:6973 :3497 :1611 9:71 2:483 :7779 3:6137 :1324 1:3515 :3875 : :69 2:5311 :7792 4:48 :1572 1:3365 :4181 : :73 3:6166 :7669 3:9872 :1269 1:215 :6381 : :78 5:176 :7355 3:8783 :1583 1:1779 :9531 :

20 Table 8. Data for Conguration BC1T1 at M =1:6 and = 15 (a) = 4:28 1:178 :731 1:432 :925 :884 :26 :1478 :3 :3638 :6928 1:7852 :956 :692 :211 :1532 3:72 :54 :6611 2:35 :971 :173 :433 :1582 7:74 1:2968 :6493 2:1944 :926 :1533 :443 :1668 9:73 1:7867 :629 2:2363 :966 :1674 :549 :176 11:75 2:3252 :6165 2:216 :917 :1268 :355 : :74 3:586 :5966 1:7549 :911 :2329 :625 : :65 5:953 :5659 1:58 :84 :3388 :1118 :2141 (b) =22:5 4:24 1:1165 :7435 1:1575 :68 :9327 :1959 :131 :24 :328 :789 1:6313 :955 :7664 :1158 :1367 3:66 :58 :6779 2:3139 :431 :3727 :844 :1455 7:77 1:3573 :6784 2:5977 :139 :317 :318 :1561 9:69 1:8291 :6656 2:7418 :15 :785 :9 : :69 2:3387 :6545 2:7886 :581 :2348 :168 : :72 3:588 :625 2:4918 :1293 :9668 :742 :281 19:68 4:9454 :5841 1:6323 :2787 1:9727 :3765 :2166 (c) =45 4:35 1:392 :7226 :3352 :419 1:7246 :345 :154 :27 :2424 :695 1:2427 :954 1:3299 :2347 :154 3:72 :5626 :6727 2:2667 :451 :7167 :186 :1572 7:76 1:43 :6918 3:6 :59 :4168 :592 :178 9:73 1:88 :6786 3:3947 :397 :314 :15 : :69 2:3685 :6658 3:6443 :569 :2766 :64 :27 15:67 3:532 :644 3:6473 :225 :1 :154 : :69 4:9388 :629 3:494 :1159 :7419 :151 :

21 Table 8. Concluded (d) =67:5 4:31 :912 :748 :754 :429 1:9949 :3624 :1368 :31 :1599 :791 :612 :968 1:7452 :3137 :1362 3:76 :653 :763 2:559 :758 1:2371 :273 :1432 7:72 1:4811 :7411 3:259 :472 :8982 :187 :1544 9:7 1:9397 :746 3:764 :171 :798 :145 : :72 2:421 :7375 4:774 :161 :8333 :418 : :67 3:4892 :7152 3:9137 :145 :8944 :31 :23 19:68 4:8512 :6965 3:435 :1986 :5642 :732 :2235 (e) =9 4:31 :865 :7214 1:6648 :725 1:7581 :3358 :1387 :28 :295 :778 :1191 :972 1:8668 :3418 :1358 3:68 :7371 :738 1:42 :1214 1:6861 :3535 :1417 7:68 1:5749 :7596 2:924 :1144 1:5359 :342 :1667 9:73 2:724 :7738 3:5759 :799 1:2761 :3289 :181 11:68 2:5226 :7695 3:969 :627 1:279 :3429 :192 15:74 3:6491 :7585 3:992 :1183 :9826 :5414 :29 19:76 5:1591 :7442 3:8414 :1291 :6549 :8165 :

22 Table 9. Data for Conguration BC1 at M =1:6 and = (a) = 4:33 :4188 :4625 1:5332 :7 :81 :3 :1325 :33 :321 :4414 :84 :25 :137 :48 :1218 3:72 :3535 :4696 1:5574 :41 :275 :5 :138 7:69 :8272 :4862 3:781 :63 :536 :81 :1822 9:77 1:145 :4826 3:8111 :66 :443 :88 : :74 1:51 :4879 4:5862 :71 :1138 :12 :235 15:68 2:4289 :4979 6:5136 :83 :819 :126 : :72 3:6217 :4963 8:5793 :67 :94 :481 :2593 (b) =45 4:32 :3186 :478 1:2159 :13 :4144 :815 :133 :34 :111 :4376 :21 :22 :88 :116 :1233 3:75 :2916 :4594 1:1746 :28 :3913 :585 :1463 7:69 :6825 :488 2:33 :16 :8461 :958 :1792 9:73 :947 :4978 2:8142 :16 1:187 :641 : :75 1:2651 :559 3:3916 :1 1:556 :264 : :74 2:822 :521 4:6641 :37 2:3593 :1119 : :75 3:1968 :551 6:2833 :1 2:115 :392 :2525 (c) =9 4:28 :2368 :4598 :8118 :6 :87 :32 :1275 :31 :134 :4345 :61 :42 :3 :1 :1225 3:76 :2188 :4522 :8588 :22 :287 :77 :1481 7:74 :5536 :597 1:5914 :18 :77 :54 :1685 9:71 :784 :525 2:253 :11 :159 :116 : :71 1:438 :552 2:5282 :4 :59 :157 :293 15:73 1:822 :5179 4:118 :21 :43 :474 : :73 2:978 :5292 5:3133 :6 :213 :711 :

23 Table 1. Data for Conguration BC2 at M =1:6 and = (a) = 4:25 :3857 :4484 1:4689 :38 :8 :14 :1315 :32 :187 :4199 :191 :53 :171 :47 :1254 3:75 :3637 :448 1:5615 :79 :445 :4 :1449 7:68 :821 :473 2:9969 :81 :543 :54 :181 9:69 1:1281 :47 3:757 :75 :631 :92 : :68 1:4666 :4746 4:4226 :76 :661 :8 : :7 2:3854 :4871 6:3376 :84 :117 :94 : :68 3:5826 :4733 8:3573 :92 :1281 :199 :2661 (b) =45 4:34 :3146 :4524 1:1719 :56 :363 :516 :1356 :34 :158 :4193 :51 :66 :13 :59 :1243 3:76 :2913 :4486 1:297 :69 :4191 :742 :1454 7:67 :678 :487 2:2957 :53 :8585 :153 :1721 9:69 :9265 :4857 2:8162 :4 1:1613 :745 : :74 1:2499 :56 3:3829 :16 1:5488 :246 :284 15:75 2:554 :562 4:633 :15 2:294 :1293 : :79 3:1824 :4845 6:3552 :67 1:8563 :936 :2564 (c) =9 4:31 :248 :4528 :863 :73 :119 :82 :134 :29 :153 :4234 :92 :6 :39 :132 :1179 3:77 :2178 :444 :8418 :54 :839 :185 :1522 7:68 :549 :494 1:648 :39 :113 :194 :1734 9:73 :7788 :496 2:333 :35 :518 :235 : :73 1:453 :4984 2:557 :24 :219 :352 :237 15:74 1:8245 :5138 4:971 :7 :784 :498 : :78 3:249 :599 5:3962 :24 :15 :112 :2653 2

24 Table 11. Data for Conguration BT1 at M =1:6 (a) = 4:33 :711 :5569 1:2382 :86 :285 :47 :1582 :25 :285 :5482 :1453 :923 :72 :159 :1525 3:71 :6138 :563 :961 :889 :979 :384 :161 7:7 1:3499 :5849 1:92 :91 :119 :455 :187 9:75 1:7859 :5931 2:3654 :946 :145 :469 : :73 2:2545 :5941 2:748 :963 :1464 :383 :197 15:72 3:4262 :688 2:9498 :969 :2584 :537 :24 19:68 4:7241 :5988 2:3843 :867 :3835 :154 :234 (b) =45 4:25 :7372 :5689 1:4147 :658 :1411 :337 :1544 :26 :289 :5481 :91 :921 :259 :15 :1483 3:71 :67 :5727 1:1772 :733 :877 :129 :1566 7:77 1:4963 :625 2:5851 :279 :45 :55 :1714 9:74 1:9363 :617 3:1354 :82 :39 :168 : :72 2:3957 :6223 3:4859 :415 :1182 :56 :287 15:72 3:5222 :615 3:5386 :712 :2996 :145 : :7 4:8588 :6148 3:373 :168 :296 :1143 :2485 (c) =9 4:31 :858 :5857 1:6562 :996 :869 :274 :1519 :28 :367 :5471 :146 :945 :488 :231 :1478 3:74 :7361 :5834 1:441 :984 :85 :124 :1569 7:76 1:5516 :635 2:8237 :187 :78 :99 :1834 9:73 2:184 :642 3:4269 :17 :283 :29 : :73 2:562 :6334 3:857 :156 :415 :298 :252 15:69 3:6356 :616 3:8713 :1225 :31 :465 : :69 4:9928 :5962 3:459 :1335 :215 :351 :

25 Table 12. Data for Conguration BT2 at M =1:6 (a) = 4:23 :7116 :6464 1:2312 :137 :836 :214 :1633 2:25 :379 :659 :774 :132 :648 :152 :151 :17 :346 :659 :843 :139 :86 :25 :144 1:8 :353 :6495 :5258 :143 :429 :81 :1476 3:81 :641 :6462 1:693 :148 :644 :126 :164 5:8 :9978 :6488 1:5962 :124 :371 :38 :1655 7:83 1:42 :6491 2:1561 :157 :483 :17 :18 9:79 1:8229 :6477 2:6182 :222 :921 :174 : :79 2:3129 :6467 3:62 :178 :975 :94 : :81 2:8587 :6517 3:2421 :161 :167 :268 :211 16:77 3:817 :656 3:967 :128 :2432 :45 : :81 4:99 :6393 2:8218 :18 :2646 :397 :2351 (b) =45 4:2 :797 :6537 1:5845 :41 :851 :132 :169 2:2 :451 :6472 :8174 :29 :789 :158 :1481 :22 :425 :6445 :881 :143 :256 :42 :1428 1:81 :3392 :6451 :6681 :233 :278 :88 :1484 3:78 :7168 :654 1:419 :447 :491 :177 :1666 5:82 1:1265 :6658 2:1624 :689 :665 :181 :1876 7:8 1:5419 :673 2:8284 :14 :1666 :54 :222 9:78 1:9959 :6727 3:4178 :1387 :2514 :826 : :79 2:4832 :663 3:8588 :161 :4899 :149 :241 13:78 3:163 :656 4:856 :1746 :7218 :213 :264 16:82 4:444 :6369 4:781 :254 :8717 :2636 : :77 5:861 :6184 3:8754 :2585 :8977 :2867 :2977 (c) =9 4:19 :787 :663 1:5594 :15 :84 :273 :1663 2:2 :496 :6471 :8415 :15 :169 :22 :1478 :18 :465 :6412 :1264 :16 :541 :87 :1449 1:83 :323 :6444 :5953 :17 :1336 :299 :1485 3:82 :6942 :6573 1:2976 :171 :1982 :446 :1667 5:78 1:63 :6769 1:9123 :192 :2846 :763 :1864 7:78 1:4711 :6847 2:4975 :217 :3256 :799 :218 9:79 1:9193 :6815 3:315 :326 :3931 :126 : :8 2:3996 :6722 3:419 :397 :4297 :1199 : :81 2:9591 :6577 3:6781 :55 :464 :151 :23 16:82 3:9439 :6387 3:6579 :625 :4576 :1591 : :82 5:44 :623 3:2651 :68 :45 :156 :266 22

26 Table 13. Data for Conguration B at M =1:6 (a) = 4:32 :2259 :4246 :8834 :11 :3 :25 :1323 :33 :125 :42 :83 :3 :186 :34 :128 3:69 :1995 :4189 :9237 :9 :338 :61 :1447 7:67 :5257 :4674 1:734 :19 :462 :67 :1843 9:71 :7499 :4615 2:1449 :28 :718 :62 : :76 1:199 :4698 2:6954 :32 :632 :1 : :68 1:791 :4796 4:275 :45 :1239 :127 : :67 2:8468 :4796 6:117 :61 :388 :14 :2723 (b) =45 4:34 :2369 :4226 :8997 :5 :28 :67 :1431 :22 :56 :45 :361 :18 :288 :13 :1194 3:71 :1992 :421 :9 :1 :234 :113 :145 7:74 :5281 :4542 1:7211 :38 :113 :267 :1727 9:68 :7496 :4523 2:1258 :56 :62 :243 : :68 1:161 :4496 2:6672 :81 :383 :292 :211 15:66 1:7932 :452 4:1943 :123 :235 :169 :242 19:66 2:982 :4623 5:7854 :163 :2188 :134 :254 (c) =9 4:31 :2399 :4152 :8971 :32 :5 :26 :1345 :28 :136 :3973 :73 :24 :186 :6 :1163 3:75 :245 :4156 :924 :17 :292 :92 :1455 7:76 :5272 :4455 1:7372 :11 :46 :159 :1792 9:68 :7454 :4498 2:1454 :1 :395 :21 : :67 1:217 :4544 2:6493 :8 :115 :249 : :68 1:8183 :4723 4:1344 :31 :539 :485 : :77 3:239 :4984 5:435 :75 :155 :641 :

27 Table 14. Data for Conguration BC1T1 at M =1:9 and = (a) = 4:33 :7342 :5659 :1 :835 :225 :51 :1495 :3 :443 :5498 :177 :881 :324 :96 :1429 3:71 :6278 :5654 :265 :837 :133 :72 :1429 7:66 1:3448 :657 :5521 :825 :46 :31 :155 9:72 1:8621 :677 :4942 :958 :518 :2 : :68 2:3764 :646 :7899 :945 :1283 :45 : :62 3:667 :6117 1:5394 :888 :895 :268 : :71 5:1968 :674 1:895 :872 :645 :135 :1855 (b) =45 4:18 :725 :594 :6993 :73 :6365 :262 :137 :19 :151 :5672 :1348 :879 :37 :256 :1253 3:8 :6528 :5987 :3826 :745 :5386 :373 :1247 7:76 1:422 :6358 :954 :449 :8813 :793 :1379 9:83 1:8997 :6456 1:1934 :441 :9761 :1147 : :85 2:441 :6577 1:3469 :499 1:78 :1583 : :79 3:7285 :673 1:4658 :818 1:2148 :118 : :81 5:1213 :6668 1:1723 :98 1:8178 :783 :1852 (c) =9 3:97 :696 :5963 1:35 :941 :658 :468 :1316 :2 :115 :5738 :135 :91 :521 :42 :128 4:4 :681 :611 1:351 :927 :312 :372 :1253 8:8 1:4869 :6449 2:886 :125 :135 :314 :1513 1:2 1:9194 :6588 2:4372 :157 :345 :384 : :3 2:4248 :6597 2:5564 :152 :248 :319 : :97 3:6175 :656 2:2826 :981 :596 :432 : :99 5:735 :6574 2:2711 :977 :769 :558 :

28 Table 15. Data for Conguration BC1T1 at M =1:9 and =5 (a) = :2 :993 :5837 :6927 :922 :154 :13 :1478 4:32 :6434 :5724 :6271 :865 :473 :36 :159 :26 :397 :5829 :683 :912 :22 :78 :1496 3:66 :6987 :647 :8828 :88 :132 :144 :1486 7:77 1:412 :6444 1:3272 :797 :243 :53 :1562 9:67 1:971 :6546 1:1326 :978 :416 :257 : :69 2:4313 :6552 1:351 :141 :1513 :42 : :7 3:7443 :6621 2:95 :162 :172 :119 : :66 5:216 :6694 2:2637 :114 :757 :24 :1851 (b) =45 4:12 :6574 :5688 1:1311 :692 :2329 :921 :1437 :9 :433 :5561 :548 :92 :3621 :166 :1413 3:91 :7179 :589 :55 :695 :9544 :1233 :1419 7:87 1:4723 :636 :4171 :384 1:269 :1884 :156 9:94 1:9757 :6493 :7715 :267 1:2727 :2352 : :91 2:4895 :6683 :9438 :65 1:2991 :3156 :168 15:9 3:7622 :687 1:82 :347 1:3811 :3197 :181 19:92 5:1725 :6794 :916 :1251 2:423 :197 :1946 (c) =9 4:9 :7221 :691 1:3243 :959 :537 :152 :133 :1 :243 :5835 :1449 :914 :5332 :1244 :1255 4: :6712 :615 1:165 :944 :5827 :97 :1272 8:3 1:4741 :6639 2:1242 :113 :5873 :593 :1422 1:4 1:9226 :669 2:455 :1155 :6112 :638 : :93 2:3991 :6675 2:5551 :193 :5817 :931 : :96 3:6131 :6661 2:2914 :13 :477 :1794 :1678 2: 5:812 :6663 2:3122 :944 :4675 :2583 :

29 Table 16. Data for Conguration BC1T1 at M =1:9 and = 5 (a) = 4:37 :8523 :5836 :4449 :876 :346 :3 :1447 :33 :1722 :5629 :2951 :927 :311 :49 :141 3:68 :4968 :5559 :1669 :89 :127 :122 :141 7:66 1:2467 :5842 :111 :925 :191 :199 :1532 9:65 1:7289 :5823 :39 :981 :538 :239 : :69 2:2569 :5759 :2722 :128 :877 :337 : :7 3:6163 :5739 1:144 :955 :854 :324 :18 19:71 5:11 :5775 1:4475 :862 :387 :159 :1839 (b) =45 4:36 :833 :5957 :4292 :66 :9411 :549 :1452 :29 :129 :5625 :1365 :922 :3112 :599 :1415 3:71 :551 :5717 :6691 :763 :2413 :4 :1438 7:63 1:313 :697 1:2233 :448 :6368 :9 :153 9:64 1:7638 :6191 1:4471 :387 :7771 :199 : :71 2:311 :6169 1:5839 :399 :8275 :547 : :64 3:5553 :6226 1:529 :622 :944 :255 : :68 5:296 :6252 1:4114 :651 1:5922 :138 :21 (c) =9 4:38 :7696 :6169 1:3984 :972 :4721 :659 :1298 :28 :689 :5874 :2141 :927 :4461 :913 :1235 3:66 :677 :6192 :9275 :933 :4257 :775 :1262 7:66 1:3942 :668 2:155 :954 :3887 :497 :1443 9:74 1:8555 :6696 2:4194 :963 :3666 :515 : :7 2:348 :6699 2:573 :11 :3152 :649 :163 15:69 3:5269 :6612 2:2814 :133 :1923 :111 : :69 4:9657 :6647 2:2443 :1154 :565 :1943 :

30 Table 17. Data for Conguration BC1T1 at M =1:9 and =1 (a) = :6 :124 :5967 1:1339 :899 :179 :59 :1479 :32 :1341 :5975 1:1318 :891 :367 :55 :1446 3:66 :8292 :6267 1:3329 :98 :265 :1 :1447 7:69 1:444 :6575 1:9437 :613 :559 :31 :158 11:7 2:4953 :6881 1:636 :12 :1289 :325 : :65 3:7252 :6884 2:2678 :147 :142 :259 : :71 5:289 :711 2:4521 :967 :1182 :221 :1788 (b) =45 4:34 :6462 :5945 1:5393 :57 :367 :1528 :149 :28 :861 :5949 :89 :95 :6512 :1821 :1468 3:66 :7549 :6234 :4258 :671 1:2426 :196 :1471 7:73 1:587 :6664 :48 :317 1:4332 :277 : :67 2:4899 :778 :6259 :378 1:4764 :4255 : :64 3:769 :7214 :6944 :176 1:4873 :478 : :68 5:117 :7196 :6927 :1412 1:9277 :377 :24 (c) =9 4:37 :7661 :6391 1:433 :135 :9726 :2259 :1364 :38 :868 :6163 :2519 :95 :9689 :2648 :1311 3:73 :6165 :6356 :9319 :832 1:156 :228 :1333 7:7 1:492 :6829 2:88 :18 :9768 :1584 : :74 2:3635 :725 2:6394 :1159 :9119 :281 : :71 3:5364 :693 2:321 :848 :737 :3799 : :71 5:97 :69 2:4443 :825 :738 :4942 :

31 Table 18. Data for Conguration BC1T1 at M =1:9 and = 1 (a) = 4:32 :9488 :6181 :9694 :892 :695 :139 :1489 :29 :2656 :599 :7772 :921 :411 :11 :1461 3:73 :4319 :5771 :7172 :96 :696 :19 :1458 5:69 :789 :574 :6117 :983 :442 :11 : :7 2:171 :5724 :2187 :172 :158 :48 : :69 3:5327 :5667 :631 :137 :1472 :483 : :67 5:2 :5575 :9598 :932 :177 :422 :1844 (b) =45 4:38 :964 :6348 :496 :597 1:2848 :144 :1462 :35 :2112 :5977 :4719 :96 :6745 :138 :1425 3:72 :4988 :5952 1:346 :74 :77 :197 :1452 7:66 1:2624 :6199 1:5935 :273 :357 :621 : :7 2:232 :636 1:876 :155 :4986 :49 : :68 3:5131 :627 1:6375 :33 :6997 :167 :199 19:7 4:9821 :6153 1:566 :787 1:3429 :934 :269 (c) =9 4:29 :7645 :6347 1:413 :891 :9556 :1592 :1328 :35 :882 :6137 :2695 :921 :9438 :1985 :1269 3:72 :6112 :6385 :9222 :984 :9321 :1773 :135 7:67 1:3924 :6799 2:627 :922 :881 :1288 :146 11:71 2:3438 :6933 2:644 :948 :7348 :1562 : :67 3:4973 :6849 2:3119 :1176 :4768 :2986 :171 19:7 4:9825 :6876 2:4361 :1223 :4248 :3936 :