1、Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-REPORT 1336 AN INVESTIGATION OF SINGLE- AND DUAL-ROTATION PROPELLERS AT POSITIVE AND NEGATIVE THRUST, AND IN COMBINATION WITH AN NACA 1-SERIES D-TYPE COWLING AT MACH NUMBERS UP TO 0.84 By ROBERT M. REYN
2、OLDS, ROBERT I. SAMMONDS, and JOHN H. WALKER Ames Aeronautical Laboratory Moffett Field, Calif. Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-National Advisory Committee for Aeronautics Headquarters, 1611 H Street NW., Washington 66, D. C, Created
3、by Act of Congress approved March 3, 1915, for the supervision and direction of the scientific study Its membership was increased from 12 to 15 by act The members are appointed by the President of the problems of flight (U. S. Code, title 50, sec. 151). approved March 2, 1929, and to 17 by act appro
4、ved May 25, 1948. and serve as such without compensation. JAMES H. DOOLrTTLE, Sc. D., Vice President, Shell Oil Company, Chairman LEONARD CARMICHAEL, Ph. D., Secretary, Smithsonian Institution, Vice Chairman ALLEN V. ASTIN, Ph. D., Director, National Bureau of Standards. PRESTON R. BASSETT, D. 8c. D
5、ETLEV W. BRONK, Ph. D., President, Rockefeller Institute for FREDERICK C. CRAWFORD, So. D., Chairman of the Board, WILLIAM V. DAVIS, JR., Vice Admiral, United States Navy, PAUL D. FOOTE, Ph. D., Assistant Secretary of Defense, Re- (Appointed member of Committee WELLINGTON T. HINES, Rear Admiral, Uni
6、ted States Navy, JEaoMn C. HUNSAEER, Sc. D., Massachusetts Institute of Medical Research. Thompson Products, Inc. Deputy Chief of Naval Operations (Air). search and Engineering. Oct. 22, 1957.) Assistant Chief for Procurement, Bureau of Aeronautics. Technology. CHARLES 5. MCCARTHY, S. B., Chairman o
7、f the Board, Chance DONALD L. PUTT, Lieutenant General, United States Air Force, JAMES T. PYLE, A. B., Administrator of Civil Aeronautics. FRANCIS W. REICHELDERFER, Sc. D., Chief, United States EDWARD V. RICKENBACKER, Sc. D., Chairman of the Board, LOUIS S. ROTHSCHILD, Ph. B., Under Secretary of Com
8、merce for THOMAS D. WHITE, General, United States Air Force, Chief of Yought Aircraft, Inc. Deputy Chief of Staff, Development. Weather Bureau. Eastern Air Lines, Inc. Transportation. Staff. HUGH L. DRYDEN, PH. D., Director JOHN W. CROWLEY, JR., B. S., Associate Director for Research JOHN F. VICTORY
9、, LL. D., Executive Secretary EDWARD H. CHARIBERLIN, Executive O$cer HENRY J. E. REID, D. Eng., Director, Langley Aeronautical Laboratory, Langley Field, Va. SMITX J. DEFRANCE, D. Eng., Director, Ames Aeronautical Laboratory, Moffett Field, Calif. EDWARD R. SHARP, So. D., Director, Lewis Flight Prop
10、ulsion Laboratory, Cleveland, Ohio WALTER 6. WILLIAMS, B. S., Chief, High-speed Flight Station, Edwards, Calif. n Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-, REPORT 1336 AN INVESTIGATION OF SINGLE- AND DUAL-ROTATION PROPELLERS AT POSITIVE AND N
11、EGATIVE THRUST, AND IN COMBINATION WITH AN NACA 1-SERIES D-TYPE COWLING AT MACH NUMBERS UP TO 0.84 By ROBERT M. REYNOLDS, ROBERT I. SAMMONDS, and JOHN H. WALRR SUMMARY An investigation has been made to determine the aerod?/namic characteristics of the NACA 4-(5) (O6)44l four-blade, single- rotation
12、propeller and the NACA 4-(6)(06)-US7 six- and eight-blade, dual-rotation propellers in combination with various spinners and NACA D-type spinner-cowling combina- tions at Mach numbers up to 0.84. Propeller force characteris- tics, local velocity distributions in the propeller planes, inlet pressure
13、recoveries, and static-pressure distributions on the cowling surfaces were measured for a wide range of blade angles, advance ratios, and inlet-velocity ratios. Included are data showing: (a) the effect of extended cylindrical spinners on the characteristics of the single-rotation propeller, (b) the
14、 effect of variation of the differcnnce in blade angle setting between the front and rear components of the dd-rotation propellers, (e) the negative- and static-thrust characteristics of the propellers with I-series spinners, and (d) the effects of ideal- andplatform- type propeller-spinner juncture
15、s on the pressure-recovery characteristics of the single-rotation propeller-spinner-cowling combination. All tests were made at an angle of attack of Oo, and, except for the static-thrust data, were made at Reynolds numbers of 1.5 and 1.0 million per foot, respectively, for the single- and dual-rota
16、tion propeller-spinner-cowling eombina- tions, A description of the 1000-horsepower propeller dyna- mometer used to obtain the data is also included in the report. The highest Mach number at which the propellers with the NACA I-series spinners operated without marked compres- ability losses was abou
17、t 0.7. The maximum escieneies of the propellers at this Mach number were Y9, 85, and 88 percent, respectively, for the four-, six-, and eight-blade propellers at a blade angle of 65“. The results indicate that for operation of thc propellers at Mach numbers greater than about 0.8, highest eficiencie
18、s would be obtained at lower advance ratios and lower blade angles. Substantially higher eficiencies were obtained for the NACA 446) (05-041 propeller with extencled cylindrical spinners as compared to those obtained for the propeller with an NACA 1-series spinner, amounting to as much as 15 percent
19、 at the highest Mach number and blade angle of the tests. Due to the apparent increase in propeller thrust associated with favorable interference ejects of the cowling on the$ow$eld at the propeller, marimum eficiencies obtained with the single- and dual-rota- tion propellers operating in the presen
20、ce of the cowlings were higher at all Mach numbers and blade angles than those for the isolated propeller-spinner combinations. Addition of the propellers, with platform-type propeller- spinner junctures, to the spinner-cowling combinations resulted in a considerable decrease an pressure recovery at
21、 the inlet. At a Mach number of 0.8 and at the design inlet-velocity ratios, ram-recovery ratios of about 0.8Y were obtained for the various propeller-spinner-cowling combinations, as compared to re- covery ratios of about 0.96 with the propeller removed. IWTRODUCTION Possible application of the tur
22、bine-propeller type of power plant for moderately high-speed long-range airplanes has led to a need for data concerning the characteristics of propellers and propeller-spinner-cowling combinations suit- able for use with large turbine engines in this speed regime. Two general problems are involved,
23、that of obtaining satis- factory propeller performance, and that of providing efficient air induction to the turbine engines. Propellers driven by modern high-power gas-turbine engines must perform satisfactorily throughout a wide speed range, from static and near static conditions to high subsonic
24、speeds, at either positive or negative thrust. The large thrust at Iow speed, resulting in a reduction in take-off run, constitutes one of the greatest advantages of the turbine- propeller combination over other means of aircraft propulsion. Interest in propeller performance in the negative-thrust r
25、ange stems from the desire to utilize the negative thrust for landing and maneuvering, and to cal- culate and provide controls for the alleviation of the large drag forces which result in the event of an engine failure. Many investigations have been conducted in recent years, such as those reported
26、in references 1 to 5, to determine the effects of compressibility, blade thickness ratio, and camber on the high-speed performance of two-blade, single-rotation propeilers with cylindrical spinners. However, the data from these tests do not permit the assessment of the effects on pefformance of eith
27、er practical spinner installations or the high solidities required to absorb large horsepowers. High-solidity, dual-rotation propellers, in spite of the ad- vantages of smaller diameter, absence of reaction torque, 1 Summarims the resultsot NACA RMs A94322 by Robert 1. Sammonds and Robert M. Reynold
28、s, 1955; A54Q13 by John I. Walker and Robert M. Regnolds, 1954; A53B06 by Robert M. Reynolds, Robert I. Sammonds, and Qearge 0. Kenyon, 1053; A52DOla by Robert I. Sammonds, and Ashley 3. Malk, 1952; A52IlQa by Robert M. Reynolds, Donald A. Ruell, and John H. Walker, 1952. 1 Provided by IHSNot for Re
29、saleNo reproduction or networking permitted without license from IHS-,-,-2 REPORT 1336-NATIONAL ADVISORY COMMITTEE FOR AERONAUTICS less noise, and theoretically greater efficiency over single- rotation propellers capable of absorbing equal power, have received only limited research effort, such as t
30、he investiga- tion reported in reference 6 for a high advance-ratio design. Data on the static- and negative-thrust characteristics of propellers are also somewhat limited. The most recent data on the static characteristics of a two-blade, single-rotation propeller are reported in reference 7, and t
31、he results of previous investigations of numerous single- and dual-rotation propellers are correlated in reference 8. A number of reports relating to the performance of propellers operating at negative thrust are available, but most of the data, such as those reported in reference 9, are for propell
32、ers of older design and were obtained only at low speeds. The efficiency of the air-induction system has a large effect on the power and fuel economy of a gas-turbine engine, as analyzed in reference 10. In the case of the propeller- spinner-cowling combination, the induction efficiency can be quite
33、 low as a result of interference effects of the propeller blade shanks and pressure losses in the spinner boundary layer. Reference 11 presents a procedure, from the results of tests at low speed, for the selection of D-type spinner- cowling Combinations for specific high-speed requirements, the val
34、idity of which has been subsequently shown for high speeds in reference 12. The only data available showing the effects of propeller operation and propeller-spinner- juncture configuration on the internal-flow characteristics of spinner-cowling combinations of this type have been reported in referen
35、ces 13 and 14. An investigation has been made in the Ames 12-foot pressure wind tunnel to provide additional data useful in the design and development of propellers and propeller- spinner-cowling combinations for application at high sub- sonic speeds. Presented herein are force-test results for the
36、following configurations: (a) the NACA 4-(5) (05)-041 four-blade, single-rotation propeller and the NACA 4-(5) (05)-037 six-, and eight-blade, dual-rotation pIopellers operating at positive thrust with NACA 1-series spinners and with NACA D-type spinner-cowling combinations, (b) the NACA 4-(5)(05)-0
37、41 propeller at positive thrust with extended cylindrical spinners, and (c) the NACA 445) (05)-041 and 4-(5)(05)-037 propellers with NACA 1-series spinners operating at negative thrust and at near static conditions. Included are results of measurements of the internal pressure-recovery characteristi
38、cs of the propeller- spinner-cowling combinations, surface pressure distributions on the cowlings, and local velocity distributions in the propeller plabes of the combinations. The tests were conducted at Mach numbers up to 0.84, for a wide range of blade angles and inlet-velocity ratios. All tests
39、were made at an angle of attack of 0 and, except for the static-thrust data, were made at Reynolds numbers of 1.5 and 1.0 million per foot, respectively, for the single- and dual-rotation propeller-spinner-cowling combinations. SYMBOLS a speed of sound,2 ft/sec b blade width, ft B number of blades c
40、zd blade-section design lift coefficient 7, pressure coefficient, 9 P P power coefficient, - pn3D5 ?* T CT thrust coefficient, - pnZD4 cl spinner diameter, in. D propeller diameter, ft h HP horsepower maximum thickness of blade section, ft 17, J advance ratio, - nD T7 A4 Mach number, - M, tip Mach n
41、umber, Md1+$ n propeller rotational speed, rps p static pressure,2 lb/sq ft p, total pressure,2 lbjsq ft p,-P ram-recovery ratio Pt-P _ P P r R s T TC 17 T7e VI T7 - X X P AP Pd 11 P 1 cr F i c power, Et-lb/sec dynamic pressure, -1 lb/sq ft radius from center of rotation propeller tip radius, ft pro
42、peller disc area, sq ft thrust, lb thrust coefficient, - pV2Dz air-stream velocity: ft/sec equivalent free-air velocity (air-stream velocity eor- rected for tunnel-wall constraint on the propeller slipstream) , f t/sec PVZ 2 T inlet-velocity ratio distance along the longitudinal axis from any refer-
43、 ence, such as the leading edge of the spinner or cowl, in. total length along the longitudinal axis of any com- ponent of the model, such as the spinner or cowl, in. propeller blade angle at 0.75 R design propeller section blade angle difference in blade angle between the front and rear components
44、of the dual-rotation propellers, PF-2 3 0 10 20 30 40 50 60 70 80 Front blade angle, 0=60“. Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-22 REPORT 1336-NATIONAL ADVISORY COMMITTEE FOR AERONAUTICS 2$ 8: 8 4p o( L1 r 0 .8 6; !? y 45 2 0 .2 5 a L1 5
45、.8 ; 2 .4 10 8 c 6s p 9 .4 E 2 80 Advance ratio. J (a) M=0.60 and 0.70 FIGURE 13.-Positive-thrust characteristics of the NACA 445) (05)-037 dual-rotation propellers (design &3=0.8“) with NACA 1-series spinners Provided by IHSNot for ResaleNo reproduction or networking permitted without license from
46、IHS-,-,-SINGLE- AND DUAL-ROTATION PROPELLERS AT POSITIVE AND NEGATIVE THRUST AT MACH NUMBERS UP TO 0.84 23 (b) M=0.75 and 0.80 PIGURI? 13.-Continued 439740-58-4 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-24 REPORT 1336-NATIONAL ADVISORY COMMITTE
47、E FOR AERONAUTICS Advance ratio, J (e) M=0.84 FIGURE 13.-Concluded. Moch number.44 Advance ratio, J (a) NACA 445) (05)-037 six-blade, dual-rotation propeller. (b) NACA 445) (05)-037 eight-blade, dual-rotatlon propeller. FIGURE 14.-The effect of Mach number and advance ratlo on the maximum efficiency
48、 of the dual-rotation propellers, at design A (OX), with NACA 1-series spinners. It was demonstrated by the results of surveys of the local Mach numbers in the vicinity of the Propeller plane (dis- cussed in the appendix) that with the short 1-series spinner used with the single-rotation propeller,
49、the local velocities on the inner portions of the propeller blades were consider- ably higher than the free-stream velocities. Calculations, using the method of reference 20, of the thrust and torque loadings on the blades in combination with the 1-series and cylindrical spinners of equal diameter indicated that the lower efficiencies for the propeller with the 1-series spinner are
