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Measurement of Static Forces on Externally Carried Bombs of Fineness Ratios 7.1 and 10.5 in the Flow Field of a Swept-Wing Fighter- Bomber Configuration at a Mach Number of 1.6

Description: Memorandum presenting forces and moments measured at Mach number 1.6 in the 4- by 4-foot supersonic pressure tunnel on bombs of fineness ratios 7.0 and 10.5 in the presence of a swept-wing fighter-bomber airplane configuration for a large number of positions under the fuselage. The results can be used to calculate bomb-drop paths.
Date: January 31, 1957
Creator: Geier, Douglas J. & Carlson, Harry W.
open access

Flutter Investigation on the High Subsonic and Transonic Speed Range on Cantilever Delta-Wing Plan Forms With Leading-Edge Sweepback of 60 Degrees, 53 Degrees 8', and 45 Degrees

Description: Report presenting results of flutter testing on three cantilever delta-wing plan forms at a range of Mach numbers. The time and location of flutter and results of the flutter calculations are provided for each of the wings.
Date: January 31, 1957
Creator: Lauten, William T., Jr. & Burgess, Marvin F.
open access

Supersonic Free-Flight Measurement of Heat Transfer and Transition on a 10 Degree Cone Having a Low Temperature Ratio

Description: Report presenting an investigation of the heat-transfer coefficients (Stanton number and boundary-layer transition) obtained from a free-flight test of a 10 degree total-angle cone with a 1/16-inch tip radius. Testing occurred over a range of Mach numbers from 1.8 to 3.5 and a range of wall-to-local-stream temperature ratios. Results regarding skin temperatures, heat-transfer coefficient, and boundary-layer transition are presented.
Date: January 31, 1957
Creator: Merlet, Charles F. & Rumsey, Charles B.
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