11 Matching Results

Search Results

Advanced search parameters have been applied.

in subjects: "RM-10"

open access

Aerodynamic characteristics of NACA RM-10 missile in 8- by 6-foot supersonic wind tunnel at Mach numbers from 1.49 to 1.98 1: presentation and analysis of pressure measurements (stabilizing fins removed)

Experimental investigation of flow about a slender body of revolution (NACA RM-10 missile) aligned and inclined to a supersonic stream was conducted at Mach numbers from 1.49 to 1.98 at a Reynolds number of approximately 30,000,000. Boundary-layer measurements at zero angle of attack are correlated with subsonic formulations for predicting boundary-layer thickness and profile. Comparison of pressure coefficients predicted by theory with experimental values showed close agreement at zero angle o… more

Date: July 20, 1950

Creator: Luidens, Roger W. & Simon, Paul C.

Item Type: Report

Partner: UNT Libraries Government Documents Department

open access

Correlation of Supersonic Convective Heat-Transfer Coefficients From Measurements of the Skin Temperature of a Parabolic Body of Revolution (NACA RM-10)

Report presenting local coefficients of convective heat transfer as measured from skin temperature along the body of an RM-10 NACA research missile, which consisted of a parabolic body of revolution. Results regarding recovery factors, adiabatic wall temperatures, Nusselts, Prandtl, and Reynolds numbers, and boundary-layer transition are provided.

Date: March 7, 1951

Creator: Chauvin, Leo T. & deMoraes, Carlos A.

Item Type: Report

Partner: UNT Libraries Government Documents Department

open access

The zero-lift drag of a slender body of revolution (NACA RM-10 research model) as determined from tests in several wind tunnels and in flight at supersonic speeds

Presents zero-lift drag data of an NACA RM-10 slender body of revolution with and without stabilizing fins attached. The results from several wind tunnels and in flight are compared. The results cover a Reynolds number range from about 1 time 10 to the 6th power to 40 times 10 to the 6th power for the flight models. The Mach numbers covered include 1.5 to 2.4 in the wind tunnels and 0.85 to 2.5 in flight.

Date: April 1953

Creator: Evans, Albert J.

Item Type: Report

Partner: UNT Libraries Government Documents Department

open access

Aerodynamic characteristics of NACA RM-10 missile in 8- by 6-foot supersonic wind tunnel at Mach numbers from 1.49 to 1.98 2: presentation and analysis of force measurements

Experimental investigation of aerodynamic forces acting on body of revolution (NACA RM-10 missile) with and without stabilizing fins was conducted at Mach numbers from 1.49 to 1.98 at angles of attack from 0 to 9 degrees and at Reynolds number of approximately 30,000,000. Comparison of experimental lift, drag, and pitching-moment coefficients and center of pressure location for body alone is made with linearized potential theory and a semiempirical method. Results indicate that aerodynamic char… more

Date: July 21, 1950

Creator: Esenwein, Fred T.; Obery, Leonard J. & Schueller, Carl F.

Item Type: Report

Partner: UNT Libraries Government Documents Department

open access

The zero-lift drag of a slender body of revolution (NACA RM-10 research model) as determined from tests in several wind tunnels and in flight at supersonic speeds

From Summary: "The results of tests of a slender body of revolution designated the NACA rm-10 have been compiled from various NACA test facilities. Zero-lift drag data are presented for a Reynolds number range from about 1 x 10(6) to 40 x 10(6) from several wind tunnels and from about 12 x 10(6) to 140 x 10(6) from free-flight tests. The Mach numbers covered include 1.5 to 2.4 for the wind-tunnel data and 0.85 to 2.5 for the flight results. The wind tunnel models were tested with and without 60… more

Date: April 16, 1953

Creator: Evans, Albert J.

Item Type: Report

Partner: UNT Libraries Government Documents Department

open access

Investigation of the Aerodynamic Characteristics of the NACA RM-10 Missile (With Fins) at a Mach Number of 1.62 in the Langley 9-Inch Supersonic Tunnel

Report presenting an investigation of a fin-stabilized scale model of the NACA RM-10 missile at a Mach number of 1.62. Measurements were made of the lift, drag, and pitching moment of the finned body over a range of angles of attack. Comparisons with the results from other testing facilities are also provided.

Date: December 19, 1952

Creator: Coletti, Donald E.

Item Type: Report

Partner: UNT Libraries Government Documents Department

open access

Drag Measurements on a 1/6-Scale, Finless, Sting-Mounted NACA RM-10 Missile in Flight at Mach Numbers From 1.1 to 4.04 Showing Some Reynolds Number and Heating Effects

Report discussing a finless NACA RM-10 missile string-mounted on a parent body to determine the total drag, base drag, and wall temperature at peak Mach number 4.04. The total- and base-drag measurements were well-correlated with wind tunnel results and calculations made by using Love's method. The existence of considerable regions of laminar flow on the body during the flight were observed.

Date: October 27, 1954

Creator: Piland, Robert O.

Item Type: Report

Partner: UNT Libraries Government Documents Department

open access

Some new drag data on the NACA RM-10 missile and a correlation of the existing drag measurements at M = 1.6 and 3.0

Report presenting the total zero-lift drag of a fin-stabilized parabolic body of revolution designated the RM-10 using scale models launched from a gun through still air at a range of Mach and Reynolds numbers. Results indicated that the location of transition had an important effect on the drag of the configuration.

Date: June 1954

Creator: Carros, Robert J. & James, Carlton S.

Item Type: Report

Partner: UNT Libraries Government Documents Department

open access

Flight measurements of boundary-layer temperature profiles on a body of revolution (NACA RM-10) at Mach numbers from 1.2 to 3.5

Report presenting flight testing of a fin-stabilized parabolic body of revolution (NACA RM-10) as a rocket-propelled model. Boundary-layer static-temperature profiles were determined around the body and from Mach number profiles obtained from a total-pressure rake. Results regarding boundary-layer profiles, skin-friction coefficients, and heat-transfer coefficients are provided.

Date: July 1957

Creator: Swanson, Andrew G.; Buglia, James J. & Chauvin, Leo T.

Item Type: Report

Partner: UNT Libraries Government Documents Department

open access

Free-Flight Tests to Determine the Power-on and Power-Off Pressure Distribution and Drag of the NACA RM-10 Research Vehicle at Large Reynolds Numbers Between Mach Numbers 0.8 and 3.0

Memorandum presenting an investigation of the effect of a propulsive jet on the drag and pressure distribution of the NACA RM-10 missile configuration at large Reynolds numbers that utilized rocket models between Mach numbers 0.8 and 3.0. Pressures were measured along the body, near the fin root, and at the base. Results regarding basic data, body pressures, fin pressures, and drag are provided.

Date: September 20, 1955

Creator: Hoffman, Sherwood

Item Type: Report

Partner: UNT Libraries Government Documents Department

open access

An Investigation of the Characteristics of the NACA RM-10 (With and Without Fins) in the Langley 11-Inch Hypersonic Tunnel at a Mach Number of 6.9

Report presenting an investigation of the aerodynamic characteristics of a model of the NACA RM-10 in the hypersonic tunnel at a Mach number of 6.9. Longitudinal pressure surveys were made on the body without fins at zero lift and at angles of attack. Results regarding the pressure distributions, forebody pressure forces, body forces, fin-body combination forces, pitching moment and center of pressure, variation of the zero-lift drag components with Reynolds number and Mach number, variation of… more

Date: November 26, 1954

Creator: McCauley, William D. & Feller, William V.

Item Type: Report

Partner: UNT Libraries Government Documents Department