NATIONAL AERONAUTICS AND SPACE ADMIN LANGLEY RESEARCH CENTER HAMPTON VA

The primary purpose of this conference was to convey to the military services, their contractors, and others concerned with the design of helicopters the results of NACA research on helicopters and to provide those attending an opportunity to discuss the results.

MEASUREMENTS OF NORMAL-FORCE-COEFFICIENT FLUCTUATION ON FOUR 9-PERCENT-THICK AIRFOILS HAVING DIFFERENT LOCATIONS OF MAXIMUM THICKNESS

27 Apr 1954

31 pages

Authors: Milton D Humphreys; NATIONAL AERONAUTICS AND SPACE ADMIN LANGLEY RESEARCH CENTER HAMPTON VA

ROCKET-POWERED-MODEL INVESTIGATION OF THE HINGE-MOMENT AND NORMAL-FORCE CHARACTERISTICS OF A HALF-DIAMOND TIP CONTROL ON A 60 deg SWEPTBACK DIAMOND WING BETWEEN MACH NUMBERS OF 0.5 AND 1.3

26 Apr 1954

35 pages

Authors: JAMES D CHURCH; NATIONAL AERONAUTICS AND SPACE ADMIN LANGLEY RESEARCH CENTER HAMPTON VA

AN EXPERIMENTAL INVESTIGATION OF THE TRANSONIC-FLOW-GENERATION AND SHOCK-WAVE-REFLECTION CHARACTERISTICS OF A TWO-DIMENSIONAL WIND TUNNEL WITH 17-PERCENT-OPEN PERFORATED WALLS

26 Apr 1954

50 pages

Authors: Davis; Don D Jr; Thomas B Sellers; George M Stokes; NATIONAL AERONAUTICS AND SPACE ADMIN LANGLEY RESEARCH CENTER HAMPTON VA

LATERAL CONTROL CHARACTERISTICS OF TWO STRUCTURALLY SIMILAR FLEXIBLE WINGS WITH 45 deg SWEEP: A SWEPTBACK WING AND A WING WITH M PLAN FORM

26 Apr 1954

53 pages

Authors: RODGER L NAESETH; DELWIN R CROOM; John W McKee; NATIONAL AERONAUTICS AND SPACE ADMIN LANGLEY RESEARCH CENTER HAMPTON VA

EXPERIMENTAL EFFECTS OF PROPULSIVE JETS AND AFTERBODY CONFIGURATIONS ON THE ZERO-LIFT DRAG OF BODIES OF REVOLUTION AT A MACH NUMBER OF 1.59

22 Apr 1954

38 pages

Authors: De; Carlos A Moraes; Albin M Nowitzky; NATIONAL AERONAUTICS AND SPACE ADMIN LANGLEY RESEARCH CENTER HAMPTON VA

DYNAMIC STABILITY AND CONTROL CHARACTERISTICS OF A DUCTED-FAN MODEL IN HOVERING FLIGHT

22 Apr 1954

22 pages

Authors: ROBERT H KIRBY; NATIONAL AERONAUTICS AND SPACE ADMIN LANGLEY RESEARCH CENTER HAMPTON VA

THE EFFECTS OF WING-MOUNTED EXTERNAL STORES ON THE TRIM, BUFFET, AND DRAG CHARACTERISTICS OF A ROCKET-PROPELLED MODEL HAVING A 45 deg SWEPTBACK WING

22 Apr 1954

32 pages

Authors: Allen B Henning; NATIONAL AERONAUTICS AND SPACE ADMIN LANGLEY RESEARCH CENTER HAMPTON VA

Experimental Influence Coefficients for the Deflection of the Wing of a Full-Scale, Swept-Wing Bomber

22 Apr 1954

29 pages

Authors: Alton P Mayo; John F Ward; NATIONAL AERONAUTICS AND SPACE ADMIN LANGLEY RESEARCH CENTER HAMPTON VA

AN ANALYSIS OF PRESSURE STUDIES AND EXPERIMENTAL AND THEORETICAL DOWNWASH AND SIDEWASH BEHIND FIVE POINTED-TIP WINGS AT SUPERSONIC SPEEDS

21 Apr 1954

127 pages

Authors: WILLIAM B BOATRIGHT; NATIONAL AERONAUTICS AND SPACE ADMIN LANGLEY RESEARCH CENTER HAMPTON VA

COMPARISON OF EXPERIMENTAL WITH CALCULATED RESULTS FOR THE LIFTING EFFECTIVENESS OF A FLEXIBLE 45 DEG SWEPTBACK WING OF ASPECT RATIO 6.0 AT MACH NUMBERS FROM 0.8 TO 1.3

15 Apr 1954

40 pages

Authors: RICHARD E WALTERS; NATIONAL AERONAUTICS AND SPACE ADMIN LANGLEY RESEARCH CENTER HAMPTON VA

PRESSURE RECOVERY AND DRAG CHARACTERISTICS OF A FORWARD LOCATED CIRCULAR SCOOP INLET AS DETERMINED FROM FLIGHT TESTS FOR MACH NUMBERS FROM 0.8 TO 1.6

08 Apr 1954

29 pages

Authors: Charles F Merlet; NATIONAL AERONAUTICS AND SPACE ADMIN LANGLEY RESEARCH CENTER HAMPTON VA

SUBSONIC INVESTIGATION OF EFFECTS OF BODY IDENTATION ON ZERO-LIFT DRAG CHARACTERISTICS OF A 45 deg SWEPTBACK WING-BODY COMBINATION WITH NATURAL AND FIXED BOUNDARY LAYER TRANSITION THROUGH A RANGE OF REYNOLDS NUMBER FROM 1 X 10 6 TO 8 X 10 6

05 Apr 1954

17 pages

Authors: GENE J BINGHAM; Albert L Braslow; NATIONAL AERONAUTICS AND SPACE ADMIN LANGLEY RESEARCH CENTER HAMPTON VA

A TRANSONIC WIND-TUNNEL INVESTIGATION OF THE EFFECTS OF TWIST AN CAMBER WITH AND WITHOUT THE INCIDENCE, TWIST, AND BODY INDENTATION OF THE AERODYNAMIC CHARACTERISTICS OF A 45 deg SWEPTBACK WING-BODY CONFIGURATION

01 Apr 1954

41 pages

Authors: J L COOPER; NATIONAL AERONAUTICS AND SPACE ADMIN LANGLEY RESEARCH CENTER HAMPTON VA

LIFT AND MOMENT COEFFICIENTS EXPANDED TO THE SEVENTH POWER OF FREQUENCY FOR OSCILLATING RECTANGULAR WINGS IN SUPERSONIC FLOW AND APPLIED TO A SPECIFIC FLUTTER PROBLEM

Apr 1954

58 pages

Authors: Herbert C Nelson; Ruby A Rainey; Charles E Watkins; NATIONAL AERONAUTICS AND SPACE ADMIN LANGLEY RESEARCH CENTER HAMPTON VA

AN EXTENSION OF THE EFFECTS OF HEAT TRANSFER ON BOUNDARY-LAYER TRANSITION ON A PARABOLIC BODY OF REVOLUTION (NACA RM-10) AT A MACH NUMBER OF 1.61

Apr 1954

25 pages

Authors: K R Czarnecki; ARCHIBALD R SINCLAIR; NATIONAL AERONAUTICS AND SPACE ADMIN LANGLEY RESEARCH CENTER HAMPTON VA

A METHOD FOR MEASURING THE PRODUCT OF INERTIA AND THE INCLINATION OF THE PRINCIPAL LONGITUDINAL AXIS OF INERTIA OF AN AIRPLANE

Apr 1954

43 pages

Authors: Robert W Boucher; Drexel A Rich; Harold L Crane; Cloyce E Matheny; NATIONAL AERONAUTICS AND SPACE ADMIN LANGLEY RESEARCH CENTER HAMPTON VA

PRELIMINARY INVESTIGATION OF THE EFFECTS OF HEAT TRANSFER ON BOUNDARY-LAYER TRANSITION ON A PARABOLIC BODY OF REVOLUTION (NACA RM-10) AT MACH NUMBER OF 1.61

Apr 1954

27 pages

Authors: K R Czarnecki; ARCHIBALD R SINCLAIR; NATIONAL AERONAUTICS AND SPACE ADMIN LANGLEY RESEARCH CENTER HAMPTON VA

A CALCULATION STUDY OF WING-AILERON FLUTTER IN TWO DEGREES OF FREEDOM FOR TWO-DIMENSIONAL SUPERSONIC FLOW

Apr 1954

30 pages

Authors: Donald S Woolston; Vera Huckel; NATIONAL AERONAUTICS AND SPACE ADMIN LANGLEY RESEARCH CENTER HAMPTON VA

Results are presented of some sample calculations made for the bending-aileron and torsion-aileron flutter of an idealized wing-aileron system (infinite aspect ratio, full-span aileron hinged at its leading edge) for several values of Mach number in supersonic flow and also for some subsonic Mach numbers. It is emphasized that the results are subject to various limitations and are not intended to be applicable to particular configurations. They may serve, however, ...

MANEUVER ACCELERATIONS EXPERIENCED BY FIVE TYPES OF COMMERCIAL TRANSPORT AIRPLANES DURING ROUTINE OPERATIONS

Apr 1954

30 pages

Authors: Thomas L Coleman; Martin R Copp; NATIONAL AERONAUTICS AND SPACE ADMIN LANGLEY RESEARCH CENTER HAMPTON VA

The magnitude and frequency of occurrence of maneuver accelerations experienced by five types of commercial transport airplanes during routine operations have been obtained from time-history (VGH) records and are presented herein. The results are compared with available gust acceleration data for the operations considered. It is indicated that maneuver accelerations may contribute substantially to the total load histories of transport airplanes, particularly in the case of medium altitude operations.

AN EXPERIMENTAL STUDY OF POROSITY CHARACTERISTICS OF PERFORATED MATERIALS IN NORMAL AND PARALLEL FLOW

Apr 1954

28 pages

Authors: George M Stokes; Davis; Don D Jr; Thomas E Sellers; NATIONAL AERONAUTICS AND SPACE ADMIN LANGLEY RESEARCH CENTER HAMPTON VA

ROLLING EFFECTIVENESS AND AILERON REVERSAL OF RECTANGULAR WINGS AT SUPERSONIC SPEEDS

Apr 1954

83 pages

Authors: John M Hedgepeth; Robert J Kell; NATIONAL AERONAUTICS AND SPACE ADMIN LANGLEY RESEARCH CENTER HAMPTON VA

Linearized supersonic lifting-surface theory is used in conjunction with structural influence coefficients to formulate a method for analyzing the aeroelastic behavior in roll at supersonic speeds of a rectangular wing mounted on a cylindrical body. Rolling effectiveness and aileron-reversal speed are computed by using a numerical solution which incorporates matrices. Results obtained for an example configuration by using this method are compared with the results obtained by using simplified methods ...

THE EFFECT OF NACELLE LOCATION ON THE ZERO-LIFT DRAGS OF 45 DEGREE SWEPTBACK WING-BODY CONFIGURATIONS HAVING BOATTAIL AND CYLINDRICAL AFTERBODIES AS DETERMINED BY FLIGHT TESTS AT TRANSONICS SPEEDS

25 Mar 1954

36 pages

Authors: SHERWOOD HOFFMAN; AUSTIN L WOLFF; NATIONAL AERONAUTICS AND SPACE ADMIN LANGLEY RESEARCH CENTER HAMPTON VA

ROCKET-MODEL INVESTIGATION OF THE LONGITUDINAL STABILITY, DRAG, AND DUCT PERFORMANCE OF A 60 DEGREE DELTA-WING CANARD AIRCRAFT WITH TWIN SIDE INLETS AT MACH NUMBERS FROM 0.80 TO 1.70

Mar 1954

55 pages

Authors: Aleck C Bond; Andrew G Swanson; NATIONAL AERONAUTICS AND SPACE ADMIN LANGLEY RESEARCH CENTER HAMPTON VA

INVESTIGATIONS TOWARD SIMPLIFICATION OF MISSILE CONTROL SYSTEMS

12 Nov 1953

18 pages

Authors: Curfman; Howard J Jr; H K Strass; Harold L Crane; NATIONAL AERONAUTICS AND SPACE ADMIN LANGLEY RESEARCH CENTER HAMPTON VA

SOME FLUTTER EXPERIMENTS AT A MACH NUMBER OF 1.3 ON CANTILEVER WINGS WITH TUBULAR AND CLOSED BODIES AT THE TIPS

07 Oct 1953

21 pages

Authors: John L McCarty; W J Tuovila; NATIONAL AERONAUTICS AND SPACE ADMIN LANGLEY RESEARCH CENTER HAMPTON VA

Flutters tests of 39 cantilever wings with tubular bodies or closed bodies at the tips have been made in a small intermittent-flow supersonic wind tunnel where the testing technique involved changing the structural parameters so that the combinations would flutter at the tunnel Mach number of 1.3. The experimental results are compared with an analysis that uses two-dimensional supersonic air forces on the wing and tube forces derived form a ...

SOME EXPERIMENTAL EFFECTS OF AFTERBODY SHAPE ON THE ZERO-LIFT DRAG OF BODIES FOR MACH NUMBERS BBETWEEN 0.8 AND 1.3

01 Oct 1953

28 pages

Authors: Stoney; William E Jr; NATIONAL AERONAUTICS AND SPACE ADMIN LANGLEY RESEARCH CENTER HAMPTON VA

Zero-lift drag data were obtained on a series of fin-stabilized bodies differing only in afterbody shape. Three series of afterbodies (fineness ratios 1.78, 3.00, and 5) with varying ratios of base radius to maximum radius (0, 0.458, 0.700, and 1) were combined with a fineness-ratio-7.13 parabolic nose. Both conical and parabolic afterbodies were tested. The models were launched from the Langley helium gun, and data were obtained for Mach numbers ...

AXIAL-LOAD FATIGUE TESTS ON NOTCHED AND UNNOTCHED SHEET SPECIMENS OF 61S-T6 ALUMINUM ALLOY, ANNEALED 347 STAINLESS STEEL, AND HEAT-TREATED 403 STAINLESS STEEL

Oct 1953

35 pages

Authors: Herbert F Hardrath; Charles B Landers; Utley; Elmer C Jr; NATIONAL AERONAUTICS AND SPACE ADMIN LANGLEY RESEARCH CENTER HAMPTON VA

Axial-load fatigue tests a stress ratio of zero were performed on notched and unnotched sheet specimens of 61S-T6 aluminum alloy and 347 and 403 stainless steels. Special emphasis was placed on tests at high stress levels producing failures in small numbers of cycles. It was found that the stress- concentration factors effective in fatigue of notched specimens were somewhat less than theoretical elastic values at low stresses and were approximately ...

A SUMMARY OF DATA ON THE DIVISION OF LOADS FOR VARIOUS WING-FUSELAGE COMBINATIONS

08-Jun-1953

17 pages

Authors: CLARENCE L GILLIS; NATIONAL AERONAUTICS AND SPACE ADMIN LANGLEY RESEARCH CENTER HAMPTON VA

A summary has been made of the available experimental data on division of normal-force loads between the wing and fuselage of aircraft. Comparison of the experimental values with theoretical calculations which include interference effects show good agreement in general with the greatest differences occurring near a Mach number of 1.0. At high angles of attack, above the range of linear lift curves, the proportion of the total wing-fuselage load carried ...

LOADS EXPERIENCED IN FLIGHTS OF TWO SWEPT-WING RESEARCH AIRPLANES IN THE ANGLE-OF-ATTACK RANGE OF REDUCED STABILITY

05 Jun 1953

14 pages

Authors: HUBERT M DRAKE; GLENN H ROBINSON; ALBERT E KUHL; NATIONAL AERONAUTICS AND SPACE ADMIN LANGLEY RESEARCH CENTER HAMPTON VA

LOW-SPEED, LARGE-SCALE INVESTIGATION OF AERODYNAMIC CHARACTERISTICS OF A SEMISPAN 49 DEGREE SWEPTBACK WING WITH A FLOWLER FLAP IN COMBINATION WITH A PLAIN FLAP, SLATS, AND FENCES

05 Jun 1953

46 pages

Authors: Whittle; Edward F Jr; Stanley Lipson; NATIONAL AERONAUTICS AND SPACE ADMIN LANGLEY RESEARCH CENTER HAMPTON VA

AERODYNAMIC CHARACTERISTICS AT HIGH AND LOW SUBSONIC MACH NUMBERS OF FOUR NACA 6-SERIES AIRFOIL SECTIONS AT ANGLES OF ATTACK FROM -2 TO 31

05 Jun 1953

52 pages

Authors: Homer B Wilson; Elmer A Horton; NATIONAL AERONAUTICS AND SPACE ADMIN LANGLEY RESEARCH CENTER HAMPTON VA