Drag Measurements on Equivalent Bodies of Revolution of Six Configurations of the Convair MX-1964 (Originally MX-1626) Proposed Supersonic Bomber

Drag Measurements on Equivalent Bodies of Revolution of Six Configurations of the Convair MX-1964 (Originally MX-1626) Proposed Supersonic Bomber

Date: October 29, 1953
Creator: Hall, James Rudyard
Description: Tests on equivalent bodies of revolution of six configurations of the Consolidated Vultee Aircraft Corporation proposed supersonic bomber (Convair MX-1964) have indicated that it is possible to reduce the drag of the configuration by designing it to have a favorable area distribution. The method of NACA RM L53I22c to predict the peak pressure drag of a configuration on the basis of its area distribution gave generally good agreement with the subject models.
Contributing Partner: UNT Libraries Government Documents Department
Free-flight investigation of longitudinal stability and control of a rocket-propelled missile model having cruciform, triangular, inline wings and tails

Free-flight investigation of longitudinal stability and control of a rocket-propelled missile model having cruciform, triangular, inline wings and tails

Date: March 25, 1952
Creator: Hall, James R
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Two experiments on applications of the transonic area rule to asymmetric configurations

Two experiments on applications of the transonic area rule to asymmetric configurations

Date: April 20, 1956
Creator: Hall, James Rudyard
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Effect of wing size and amount of indentation on applicability of transonic area rule to swept-wing configurations

Effect of wing size and amount of indentation on applicability of transonic area rule to swept-wing configurations

Date: July 20, 1956
Creator: Hall, James Rudyard
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Preliminary free-flight study of the drag and stability of a series of short-span missiles at Mach numbers from 0.9 to 1.3

Preliminary free-flight study of the drag and stability of a series of short-span missiles at Mach numbers from 0.9 to 1.3

Date: February 8, 1956
Creator: Hall, James Rudyard
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Effect on transonic and supersonic drag of fuselage gloves designed to give a smooth overall area distribution to a swept-wing--body combination

Effect on transonic and supersonic drag of fuselage gloves designed to give a smooth overall area distribution to a swept-wing--body combination

Date: November 26, 1954
Creator: Hall, James Rudyard
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Abortion: Legal Control

Abortion: Legal Control

Date: August 12, 1976
Creator: Hall, James
Description: The U.S. Supreme Court decisions in Roe v. Wade, 410 U.S. 112 (1973), and Doe v. Bolton, 410 U.S. 179, which held generally that a State could no longer prohibit abortions in the first 6 months of pregnancy, caused several House and Senate members to move for an abortion prohibition effectuated by congressional action. To this end, proposed bills and constitutional amendments have been introduced in both Houses. Rather than having settled the abortion question conclusively, the Supreme Court decisions have kindled a national protest movement.
Contributing Partner: UNT Libraries Government Documents Department
The Zero-Lift Drag of Several Configurations of the XAAM-N-2 Pilotless Aircraft. TED No. NACA DE332

The Zero-Lift Drag of Several Configurations of the XAAM-N-2 Pilotless Aircraft. TED No. NACA DE332

Date: March 16, 1950
Creator: Hall, James R.
Description: Free-flight tests have been made to determine the zero-lift drag of several configurations of the XAAM-N-2 pilotless aircraft. Base-pressure measurements were also obtained for some of the configurations. The results show that increasing the wing-thickness ratio from 4 to 6 percent increased the wing drag by about 100 percent at M = 1.3 and by about 30 percent at M = 1.8. Increasing the nose fineness ratio from 5.00 to 6.25 reduced the drag coefficient of the wingless models a maximum of about 0.030 (10 percent) at M = 2.0. A corresponding change in nose shape for the winged models decreased the drag coefficient by about 0.05 in the Mach number range from 1.1 to 1.4; at Mach numbers greater than 1.6 no measurable reduction in drag coefficient was obtained. The drag of the present Sparrow fuselage is less than that of a parabolic fuselage which could contain the same equipment.
Contributing Partner: UNT Libraries Government Documents Department
Limited heat-transfer, drag, and stability results from an investigation at Mach numbers up to 9 of a large rocket-propelled 10 degree cone

Limited heat-transfer, drag, and stability results from an investigation at Mach numbers up to 9 of a large rocket-propelled 10 degree cone

Date: July 22, 1957
Creator: Hall, James R
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Free-flight investigation of the longitudinal stability and control of a rocket-propelled missile model having cruciform, triangular, interdigitated wings and tails

Free-flight investigation of the longitudinal stability and control of a rocket-propelled missile model having cruciform, triangular, interdigitated wings and tails

Date: July 10, 1951
Creator: Sandahl, Carl A
Description: None
Contributing Partner: UNT Libraries Government Documents Department
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