NASA NACA-RM-L8E24-1948 Aerodynamic characteristics of a two-blade NACA 10-(3)(08)-03R propeller《双叶片NACA10-(3)(08)-03R螺旋桨的空气动力特性》.pdf

《NASA NACA-RM-L8E24-1948 Aerodynamic characteristics of a two-blade NACA 10-(3)(08)-03R propeller《双叶片NACA10-(3)(08)-03R螺旋桨的空气动力特性》.pdf》由会员分享，可在线阅读，更多相关《NASA NACA-RM-L8E24-1948 Aerodynamic characteristics of a two-blade NACA 10-(3)(08)-03R propeller《双叶片NACA10-(3)(08)-03R螺旋桨的空气动力特性》.pdf（31页珍藏版）》请在麦多课文档分享上搜索。

1、Copy No. RM Na. ME24 s AERODYNAMIC CKARACTERJSTICS OF A TWO-BLADE NACA 10-(3)(08) -03R PROPELLER BY Albert J. Evans and Leland 6. Salters, Jr. Langley Aeronautical Laboratory Langley Field, Va. NATIONAL ADVISORY COMMITTEE Provided by IHSNot for ResaleNo reproduction or networking permitted without l

2、icense from IHS-,-,-Albert J. $vans and Leland B. Salters, Jr . Fulldcale tests have been made in the Langley l torque, and rotational aped were measured at each 5 increment of blade angle from 20 to 55O, inclueive, memured at- the 75percent (45inch) radiua statim. A conrrtant rotational speed. wa8

3、used for each test and a range of advance ratio = 9 waB cowred by changing the tunnel airspeed which wae varied fram about 60 to 464 miles per hour. At hlgher blade angles the dynamometer could not deliver sufficient torque to cover the complete range of advance rat30 at the higher rotational speeds

4、 and for thls reason the lower rotational epeeds were used for the higher blade angles. Additional tests were made at constant high value of tunnel airspeed anhvariable rotational speeds in order to extend %he tip Mach number range of the tests at a blade angle of 45. All bet8 were run over a range

5、of advance ratio to determine propeller performance from maxFmum efficiency to zero torque. A chart- of the testing proam is presented in table I. The test results corrected for tunneld interference and spinner force are presented in the form of the usual thrust and power coeff icjsnt8 Provided by I

6、HSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-mAcA RM no. -24 3 aad propeller efficiency. A complete descri:+lon of the methods used to determine the propeller coefficients is given in reference 1. The Bymbols and definitione ueed throughout this report are aa

7、follm: 5 b blade chord, feet CT D h J M % 11 B * P r R T V B 9 P design lift coefficient mer coefficient thrust coefficient (si) propeller d5ameter, feet blade-section nux3m.m thichese, feet helicalrtip Mach Iumiber M l + (I 02) popeller rotational speed, revolutions per second propeller rotational

8、speed, revolutions per mlIurte radius to a blade element, feet propellez-tip radiw, feet propeller thrust, pounds free-stream velocity, feet per second blade angle, deejrees mass density of afr in free stream, slugs per cubic foot I Faired curves of thrust coefficient, per coefficient, and. propelle

9、r efficiency platted against advance ratio are presented in figures 3 to 10. Test points are shown on the figures giving thrust and power coefficient. Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-4 XACA RM No. IsE24 I Sham 012 the propeller-effici

10、ency cmes are plots of the akr-stream Mach number together uith the helical-tip Mach nmder. The discorcbinuities in the %ch number cmee, when plotted agafnst advance -ratio at constant rotational speed, are caused changes in the air ternperatwe in the tunnel between tests. The values of Mach number

11、and helical-tip Msch number ehnm for the propeller data in thfs report me the true Mach nrnnbers at which the data were obtained. # krvelope+fficiency curves plotted against advance ratio are presenf;ed in figure 11 for five rotational speede. The induced efficiency of a frictionlees propeller with

12、a Betz loading operating at the same values of power coefficient as the LBACA 10-(3)(08)-03R propeller at 13% revolu- tions per mlnute is ale0 Shawn on figure U. The duference between the emelope curve for the WACA 1 in reference 3. Figure 12 presents the values of maximum efficiency attainable in t

13、he tests for several blade angles plotted against propeller tip Mach nwnber. Langley Aeronautical Laboratory National Adviscqy Conmlttee for Aeronautics Lar?.?.ey Field, Va. REFERENCES 3 Crier, John L., and Talkin, Herbert W. : Charts for DetemTning Propeller Efficiency. PIACA Am No. L4129, 1944. Pr

14、ovided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-.NACA RM No. Lm4 5 . Tunnel speed Variable Variable Variable Variable Variable Variable M = 0.56 M = 0.60 M = 0.65 M = 0.65 T 40 45 50 40 45 50 40 45 45 43 45 45 50 Provided by IHSNot for ResaleNo reprodu

15、ction or networking permitted without license from IHS-,-,-. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . x= - R X Figure 1. - Comparison of design loading of NACA lo-( 3)(08) -03R propeller blade with Bet2 loading. . . . . . . Provided by IHSNot for ResaleNo reproduction or

16、 networking permitted without license from IHS-,-,-NclCA RV No. LI8 0“ 116 + a c 6 -14 E c W 0 .I2 L W 3 2 .IC .oa 06 a4 -0 2 0 Advance ratio, J (b) Power coefflcient. Figure 5.- Continued. 1600 revolutions per minute. . . - Provided by IHSNot for ResaleNo reproduction or networking permitted withou

17、t license from IHS-,-,-. 7 .6 F 6 a E W 5 .5 c .3 .2 .I F C Advme mli,J (c) Efficiency. Figure 5.- Concluded. la0 revolutions per minute. .I . Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-.I2 .I 0 F. 0 a2 0 A .6 .a , LO 12 I .4 1.6 2.0 2.2 2.4 26

18、28 Advance rotio, J V (a) Thrust coefficient. Figure 6. - Characteristics of: NACA 10-(3)(08) -03R propeller at 2000 revolutions per minute. Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-. . . . . . . Advance ratio, J (b) Power coefficient. Figure

19、6.- Continued. 2000 revolutions per minute. .“. . Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-Advw ratlo, J (c) Efflciencg. Figure 6.- Concluded, 2000 revolutions per minute. Provided by IHSNot for ResaleNo reproduction or networking permitted wi

20、thout license from IHS-,-,-Iu 0 -0 .2 .4 .8 Figure 7. - Characteristics 1.0 12 I .4 Advance ratio, (a) Thrust 1.6 1.8 2.0 2.2 2.4 J coefficient. of NACA 10 -( 3) (08) -03R propeller at 2160 revolutions 2.6 - 2. per minute. 3 Provided by IHSNot for ResaleNo reproduction or networking permitted withou

21、t license from IHS-,-,-E .F (b) Power coefficient. Figure 7.- Continued. 2180 revolutions per minute. Iu r Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-. . . . . . . . - . . . . . . . . . . . . . 1.c 9 .8 .7 .6 6 .- T ,s 0 ;t W .- .4 .3 .2 .I C .

22、. . . . . . . AvLI,C rollo, d (c) Efficiency, Figure 7.- Concluded. 2i60 revolutions per minute. . . . . . Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-NACA RM No. -4 22 20 .I 8 .I 6 .I 4 . t2 .IO .O 8 .O 6 -0 4 .o 2 0 I .o 9 .8 7 5 -4 3 2 .I n- -

23、 I .4 1.6 I .8 2.0 . 2.2 2.4 2 6 Advanee ratio, J Figure 8. - Characteristics of NACA 10 -( 3) (08) 43Rgropeller at 1500 revolutions per minute. = 45 . Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-24 NACA HM No. L8E24 t .4 1.6 , 1.8 2.0 2.2 2.4 2

24、-6 Advance ratio, J (a) Air-stream Mach number, 0.56. .4 .2 .o 3 Figure 9. - Characteristics of NACA 10 -(3)(08) -03R Propeller at high forward speeds. = 450. Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-. L I -2 2 .20 .I 8 a .I6 c c- Q) .- . 5 -1

25、4 0. 0 0 L a 1 “p .t2 z c .IO 0 0 a j 5 , . .08 0 0 (II c .06 .a4 .o 2 0 (c Air-stream Mach number, 0.65. 1.4 1.6 1.8 2.0. 2.2 2.4 2.6 2.8w Advance ratio, J Figure 9.- Concluded. Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-26 mACA I(M No. Lz W 0

26、y .4 3 2 .I 0- Figure 9. - Continued. Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-22 .20 .I 8 .I 6 .I 4 .I2 .I 0 .O 8 .O 6 .O 4 -0 2 0 1.6 2.0 2.2 2.4 2.6 2:8 30 Advance ratio, J Figure 10. - Characteristics of NACA 10 -(3) (08) -033 propeller. 0

27、.75R = 50; air-stream Mach number, 0.65. Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-.O .9 .8 .7 .6 o .4 .0 1.2 Figure 11.- Envelope “ . . 1.6 2 .o 2.4 2.8 . 3.2 Advance rotio, J efficiency of NACA 10 -( 3) (08) -0 3R propeller. . Provided by IHS

28、Not for ResaleNo reproduction or networking permitted without license from IHS-,-,-F r 8 E .- z x 1.0 .9 .0 .7 .6 .5 -4 ;5 .6 .7 .8 .9 I .o I .I 1.2 I .3 Helical tip Mach number, M+ Mgure 12.- Effect of helical-tip Mach number on maximum efficiency. Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-