NASA NACA-RM-L52G18-1952 Investigation of the effects of variations in the Reynolds number between 0 4 x 10(exp 6) and 3 0 x 10(exp 6) on the low-speed aerodynamic characteristics ith .pdf

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1、CASE FI LE _,_,o_CrO PY“._!_._! _._.2.:_:_:_:_2.51.0 _3.0_1.5Flaggedsymbolsdenote1 leading-edgeroughness io0 -10 0 0 0 0 0Angle of attack,_, deg(a) Wing of aspect ratio i.Figure 2.- Lift and pitching-moment characteristics of three low-aspect- _oratio wings of rectangular plan form and NACA 0012 air

2、foil section.Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-io _ACA_L52GI8Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-“ / i / i z -/2 501.0 _ _-*_-_ _-v7_ - %-16 -8 0 8 16 24 32 _-_ NACA /0 0 0 0

3、 0 0Angle of attack, m, deg(c) Wing of aspect ratio 3.Figure 2.- Concluded. wProvided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-.I0 roOO, OA= 1E3A=2d.Og _A = 3Flagged symbols denote. leadlng-edge roughnessO .06!“_ 011. _ 02.2 .4 -7 1.0 2.0 3.0 x 106 Rey

4、nolds number, R k_roFigure 3.- Variation with Reynolds number of the lift-curve slopes oat a = 0 of three low.aspect-ratiowings, coProvided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-1.6|,o N k._CO& o OA=3_- -Flagged symbols denote_leading-edge roughness

5、Q)oo_ 1.0.2 .4 .7 l.O 2.0 3.0 lO6Reynolds number, RFigure 4.- Variation with Reynolds number of maximum lift coefficientof two low-aspect-ratio wings with smooth and. rough leading edges.Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-NACA RM L52G18

6、1. Wings, Complete- NACA RM L52G18 1. Wings, Complete-National Advisory Committee for Aeronautics. Aspect Ratio , National Advisory Committee for Aeronautics. Aspect RatioINVESTIGATION OF THE EFFECTS OF VARIATIONS (1.2.2.2.2) INVESTIGATION OF THE EFFECTS OF VARIATIONS (1.2.2.2.2)IN THE REYNOLDS NUMB

7、ER BETWEEN 0.4 X 106 2. Reynolds Number IN THE REYNOLDS NUMBER BETWEEN 0.4 X 106 2. Reynolds NumberAND 3.0 X 106 ON THE LOW-SPEED AERODY- Effects - Complete AND 3.0 X 106 ON THE LOW-SPEED AERODY- Effects - CompleteNAMIC CHARACTERISTICS OF THREE LOW- Wi,lgs (1.2.2.5) NAMIC CHARACTERISTICS OF THREE LO

8、W- . Wi,zgs (1.2.2.5)ASPECT:RATIO SYMMETRICAL WINGS WITH 3. Boundary Layer - ASPECT-RATIO SYMMETRICAL WINGS WITH 3. Bounaary Layer -RECTANGULAR PLAN FORMS. George W. Jones, Complete Wings RECTANGULAR PLAN FORMS. George W. Jones, Complete WingsJr. September 1952. 13p. diagrs. (NACA (1.2.2.8) Jr. Sept

9、ember 1952. 13p. diagrs. (NACA (1.2.2.8)RM L52G18) I. Jones, George W., Jr. RM L52G18) I. Jones, George W., Jr.II. NACA RM L52G18 II. NACA RM L52G18The effects of Reynolds number on the aerodynamic The effects of Reynolds number on the aerodynamiccharacteristics of three symmetrical wings of aspect

10、characteristics of three symmetrical wings of aspectratio 1, 2, and 3 each having a rectangular plan ratio 1, 2, and 3 each having a rectangular planform and an NACA 0012 airfoil section is given for a form and an NACA 0012 airfoil section is given for arange Of seven Reynolds numbers between 0.4 x

11、106 range of seven Reynolds numbers between 014 x 106and 3.0x 10 . The data show the effects of and 3.0x 10v. The data show the effects ofReynolds number on the lift, the lift-curve slope, Reynolds number on the lift, the lift-curve slope,maximum lift coefficient, and the pitching moment maximum lif

12、t coefficient, and the pitching momentabout the quarter-chord point, about the quarter-chord point.Copies obtainable from NACA, Washington. _ Copies obtainable from NACA, WashingtonNACA RM L52G18 1. Wings, Complete - NACA RM L52G18 1. Wings, Complete-National Advisory Committee for Aeronautics. Aspe

13、ct Ratio National Advisory Committee for Aeronautics. Aspect RatioINVESTIGATION OF THE EFFECTS OF VARIATIONS (1.2.2.2.2) INVESTIGATION OF THE EFFECTS OF VARIATIONS (1.2.2.2.2)IN THE REYNOLDS NUMBER BETWEEN 0.4 X 106 2. Reynolds Number IN THE REYNOLDS NUMBER BETWEEN 0.4 X 106 2. Reynolds NumberAND 3.

14、0 X 106 ON THE LOW-SPEED AERODY- Effects - Complete AND 3.0 X 106 ON THE LOW-SPEED AERODY- Effects - CompleteNAMIC CHARACTERISTICS OF THREE LOW- Wings (1.2.2.5) NAMIC CHARACTERISTICS OF THREE LOW- .Wings (1.2.2.5)ASPECT-RATIO SYMMETRICAL WINGS WITH 3. Boundary Layer - ASPECT-RATIO SYMMETRICAL WINGS

15、WITH 3. Bounaary Layer -RECTANGULAR PLAN FORMS. George W. Jones, Complete Wings RECTANGULAR PLAN FORMS. George W. Jones, Complete WingsJr. September 1952. 13p. diagrs. (NACA (1.2.2.8) Jr. September 1952. 13p. diagrs. (NACA (1.2.2.8)RM L52G18) I. Jones, George W., Jr. RM L52G18) I. Jones, George W.,

16、Jr.II. NACA RM L52G18 II. NACA RM L52G18The effects of Reynolds number on the aerodynamic The effects of Reynolds number on the aerodynamiccharacteristics of three symmetrical wings of aspect characteristics of three symmetrical wings of aspectratio 1, 2, and 3 each having a rectangular plan ratio 1

17、, 2, and 3 each having a rectangular planform and an NACA 0012 airfoil section is given for a form and an NACA 0012 airfoil section is given for arange of seven Reynolds numbers between 01 4 x 106 range of seven Reynolds numbers between 014 x 106and 3.0 x 10v. The data show the effects of and 3.0x 1

18、0v. The data show the effects ofReynolds number on the lift, the lift-curve slope, Reynolds number on the lift, the lift-curve slope,maximum lift coefficient, and the pitching moment maximum lift coefficient, and the pitching momentabout the quarter-chord point, about the quarter-chord point.Copies

19、obtainable from NACA, Washington. _ Copies obtainable from NACA, W_shington.Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-NACA RM L52G18 1. Wings, Complete- NACA RM L52G18 1. Wings, Complete-National Advisory Committee for Aeronautics. Aspect Ratio

20、 National Advisory Committee for Aeronautics. Aspect RatioINVESTIGATION OF THE EFFECTS OF VARIATIONS (1.2.2.2.2) INVESTIGATION OF THE EFFECTS OF VARIATIONS (1.2.2.2.2)IN THE REYNOLDS NUMBER BETWEEN 0.4 X 106 2. Reynolds Number IN THE REYNOLDS NUMBER BETWEEN 0.4 X 106 2. Reynolds NumberAND 3.0 X 106

21、ON THE LOW-SPEED AERODY- Effects- Complete AND 3.0 X 106 ON THE LOW-SPEED AERODY Effects - CompleteNAMIC CHARACTERISTICS OF THREE LOW- Wings (1.2.2.5) NAMIC CHARACTERISTICS OF THREE LOW- . Wings (1.2.2.5)ASPECT-RATIO SYMMETRICAL WINGS WITH 3. Boundary Layer -_ ASPECT-RATIO SYMMETRICAL WINGS WITH 3.

22、Boundary Layer -RECTANGULAR PLAN FORMS. George W. Jones, Complete Wings RECTANGULAR PLAN FORMS. George W. Jones, Complete WingsJr. September 1952. 13p. diagrs. (NACA (1.2.2.8) Jr. September 1952. 13p. diagrs. (NACA (1.2.2.8)RM L52G18) I. Jones, George W., Jr. RM L52G18) I. Jones, George W., Jr.II. N

23、ACA RM L52G18 II. NACA RM L52G18The effects of Reynolds number on the aerodynamic The effects of Reynolds number on the aerodynamiccharacteristics of three symmetrical wings of aspect characteristics of three symmetrical wings of aspectratio 1, 2, and 3 each having a rectangular plan ratio 1, 2, and

24、 3 each having a rectangular planform and an NACA 0012 airfoil section is given for a form and an NACA 0012 airfoil section is given for arange of seven Reynolds numbers between 0.4 x 106 range of seven Reynolds numbers between 0.4 x 106 and3.0x 10 . The data show the effects of and 3.0x10 “. The da

25、ta show the effects ofReynolds number on the lift, the lift-curve slope, Reynolds number on the lift, the lift-curve slope,maximum lift coefficient, and the pitching moment maximuin lift coefficient, and the pitching momentabout the quarter-chord point, about the quarter-chord point.Copies obtainabl

26、e from NACA, Washington _ Copies obtainable from NACA,WashingtonNACA RM L52G18 1. Wings, Complete- NACA RM L52G18 1. Wings, Complete -National Advisory Committee for Aeronautics. Aspect Ratio National Advisory Committee for Aeronautics. Aspect RatioINVESTIGATION OF THE EFFECTS OF VARIATIONS (1.2.2.2

27、.2) INVESTIGATION OF THE EFFECTS OF VARIATIONS (1.2.2.2.2)IN THE REYNOLDS NUMBER BETWEEN 0.4 X 106 2. Reynolds Number IN THE REYNOLDS NUMBER BETWEEN 0.4 X 106 2. Reynolds NumberAND 3.0 X 106 ON THE LOW-SPEED AERODY- Effects - Complete AND 3.0 X 106 ON THE LOW-SPEED AERODY- Effects - CompleteNAMIC CH

28、ARACTERISTICS OF THREE LOW- . Wings (1.2.2.5) NAMIC CHARACTERISTICS OF THREE LOW- Wiugs (1.2.2.5)ASPECT-RATIO SYMMETRICAL WINGS WITH 3. Boundary Layer - ASPECT-RATIO SYMMETRICAL WINGS WITH 3. Boundary Layer -RECTANGULAR PLAN FORMS. George W. Jones, Complete Wings RECTANGULAR PLAN FORMS. George W. Jo

29、nes, Complete WingsJr. September 1952. 13p. diagrs. (NACA (1.2.2.8) Jr. September 1952. 13p. diagrs. (NACA (1.2.2.8)RM L52G18) I. Jones, George W., Jr. RM L52G18) I. Jones, George W., Jr.II. NACA RM L52G18 II. NACA RM L52G18The effects of Reynolds number on the aerodynamic The effects of Reynolds nu

30、mber on the aerodynamiccharacteristics of three symmetrical wings of aspect characteristics of three symmetrical wings of aspectratio 1, 2, ann 3 each having a rectangular plan ratio 1, 2, and 3 each having a rectangular planform and an NACA 0012 airfoil section is given for a form and an NACA 0012

31、airfoil section is given for arange of seven Reynolds numbers between 0.4 x 106 range of seven Reynolds numbers between 0.4 x 106and 3.0x10 _. The data show the effects of and 3.0x10 . The data show the effects ofReynolds number on the lift, the lift-curve slope, Reynolds number on the lift, the lif

32、t-curve slope,maximum lift coefficient, ann the pitching moment maximum lift coefficient, and the pitching momentabout the quarter-chord point, about the quarter-chord point.Copies obtainable from NACA,Washington. _ Copies obtainable from NACA,WashingtonProvided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-