NASA NACA-RM-L54I13-1954 Comparison of low-speed rotor and cascade performance for medium-camber NACA 65-(C(sub lo)A(sub 10) 10 compressor-blade sections over a wide range of rotord 0 .pdf

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1、l.J J ” cc :;z 2 ,g 2 s COPY 6 RM L54Ilf RESEARCH MEMORANDUM COMPARISON OF LOW-SPEED ROTOR AND CASCADE PERFORMANCE FOR :-: II MEDIUM-CAMBER NACA 65- (C20Al$ 10 COMPRESSOR-BLADE 5 :i- SECTIONS OVER A WIDE RANGE OF ROTOR tJ BLADE -SETTING ANGLES AT SOLIDITIES ., OF 1.0 AND 0.5 . Ot (a) u =I.0 0 Ed + 1

2、7.5O 0 Ed + 7.5O * td * e- 7.5” -2; .2 .3 .4 .5 .6 .7 .s .S 1.0 1.1 1.2 Quantity flow coefficient, + b)u=0.5 Figure 2.- Variation in mass flow as measured upstream and downstream of rotor. Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-NACA RM L5411

3、3 13 E 8100 ,” I6 ; 20 I6 20 24 28 32 36 Angle ai attack:=, deg (a) Inboard section; NACA 65(15.8Alo)10 section; radius, 11.26 inches. Figure lO.- Variation of measured and estimated turning angles with angle of attack at three radii for several blade-setting angles and u = 1.0. Vertical lines acros

4、s curves indicate design angle of attack. Flagged symbols indicate audible partial-span rotating stall. Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-401 IllI Ill II II lllllll Illlllllrl a.? rr 6 CT 20 .s E t- I z? 73 25 c Measured zz;g: - - NACA

5、65(mlo)o section; radius, 12.41 inches. Figure lo.- Continued. Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-25- 20- !i! -0 a? a- 5 15- El c” 2 E .$ In- 9 Measured Estimated - i radius, 13.56 inches. Figure lo.- Concluded. Provided by IHSNot for Re

6、saleNo reproduction or networking permitted without license from IHS-,-,-30 /- 25 2?- F 1 m I5 C .- E z IO 5 0 II II I II II I II I II II I I IIll 1 I III .- 4 8 12 Iti 00 4 8 I2 I6 00 4 8 :20 16 20 A 0 4 8 12 16 20 24 28 32 Angle of attack, a, deg (a) Inboard section; NACA 65(15.81)10 section; radi

7、us, 26 inches. Figure ll.- Variation of measured and estimated turning angles with angle of attack at three radii for several blade-setting angles and (I = 0.5. Vertical lines across curves indicate design angle of attack. Flagged symbols indicate audible partial-span rotating stall. Provided by IHS

8、Not for ResaleNo reproduction or networking permitted without license from IHS-,-,-25 I I I I I I I I I I I I I I I I I I I I I I I I I I I I nL r / 0 I - l radius, 12.41 inches. Figure 11.- Continued. Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-

9、25. , , I I I I I 1 I I I I I I I I I I I I l l I I I I I I I 20 1 Measured Estimated - NACA 6g(g.jn,)lO section; radius, 13.56 inches. Figure 11.- Concluded. Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-d- E ;s 24 4 c” O 20 P C 5 + 16 II 12 13 I4

10、 la Ed + 7*5* i - - Estimated cYm=13.140 q I- 2 I I I2 I3 I4 Radius, inches (b) Ed cc) Ed - 7*5* Figure 12.- Radial variation of measured and estimated turning angles at several angles of attack for three blade-setting angles. u = 1.0; ad, = 12.5. Provided by IHSNot for ResaleNo reproduction or netw

11、orking permitted without license from IHS-,-,-I - NACA RM 54113 c I I I -I 16 am = 7.25” 8 I ir -0 uT I 4 ii? 0 6 I F - l-T71 U.m = 5.37” : 8 4 ILL-J-. I I 12 13 - Estimated c inb. a m = 4.59 I I l bl I I I2 I3 I4 Radius, inches 27 I. radius, 11.26 inches. Figure.15.- Variation of efficiency and sta

12、tic- and total-pressure-rise coefficients with quantity flow coefficient at three radial stations for several blade-setting-angles and ts = 1.0. Vertical lines across curves indicate design angle of attack. Flagged synibols indicate audible partial-span rotating stall. Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-