{"copyright":{"thirdPartyPermissionsProduced":false,"disclosedToPublic":false,"containsIndication":false,"publisherPermissionOrRightsToDistribute":false,"belongsToUsGov":false,"determinationType":"GOV_PUBLIC_USE_PERMITTED","thirdPartyContentCondition":"NOT_SET","belongsToContractor":false,"disclosedInvention":false,"submissionId":19930092838,"containsThirdPartyMaterial":false,"belongsToPublisher":false,"id":"a0ab9e7e06014d2fa0ff494e840f4a83","belongsToAuthors":false},"subjectCategories":["Aerodynamics"],"keywords":["WINGS-REPUBLIC P-47B-3 WIND TUNNEL TESTS(NACA-HIGH-SPEED-8')","AILERONS - BRISTOL FRISE SLOTTED","WIND TUNNEL TESTS-NACA-HIGH-SPEED (8') LMAL","AILERONS - DEFLECTION","AILERONS - HINGE MOMENTS","PRESSURE DISTRIBUTION-AIRFOILS EFFECT OF COMPRESSIBILITY"],"exportControl":{"isExportControl":"NO","submissionId":19930092838,"ear":"NO","id":"d0f9cc2fa485430e9be47fce25a3a383","itar":"NO"},"distributionDate":"2019-06-26T00:00:00.0000000+00:00","otherReportNumbers":["NACA-ACR-L4G12","NACA-WR-L-266","Report Number: NACA-ACR-L4G12","Report Number: NACA-WR-L-266"],"title":"Effect of Compressibility on Pressure Distribution over an Airfoil with a Slotted Frise Aileron","stiType":"OTHER","distribution":"PUBLIC","submittedDate":"2013-09-06T19:13:00.0000000+00:00","authorAffiliations":[{"sequence":0,"submissionId":19930092838,"meta":{"author":{"name":"Luoma, Avro A"},"organization":{"name":"National Advisory Committee for Aeronautics. Langley Aeronautical Lab.","location":"Langley Field, VA, United States"}},"id":"f8432b2ea1ce490ba482d86647163370"}],"stiTypeDetails":"Other - NACA Wartime Report","technicalReviewType":"TECHNICAL_REVIEW_TYPE_NONE","modified":"2025-08-31T18:39:21.7150190+00:00","id":19930092838,"legacyMeta":{"__type":"LegacyMetaIndex, StrivesApi.ServiceModel","accessionNumber":"93R22128"},"created":"2013-09-06T19:13:00.0000000+00:00","center":{"code":"CDMS","name":"Legacy CDMS","id":"092d6e0881874968859b972d39a888dc"},"onlyAbstract":false,"sensitiveInformation":2,"abstract":"Pressure distribution measurements were made over an airfoil with slotted Frise aileron up to 0.76 Mach at various angles of attack and aileron defections. Section characteristics were determined from these pressure data. Results indicated loss of aileron rolling power for deflections ranging from -12 Degrees to -19 Degrees. High stick forces for non-differential deflections incurred at high speed, which were due to overbalancing tendency of up-moving aileron, may precipitate serious control difficulties. Detailed results are presented graphically.","isLessonsLearned":false,"disseminated":"DOCUMENT_AND_METADATA","publications":[{"submissionId":19930092838,"id":"779791b1268f42a88603c1ab04c94155","publicationDate":"1944-07-01T00:00:00.0000000+00:00"}],"status":"CURATED","related":[],"downloads":[{"draft":false,"mimetype":"application/pdf","name":"19930092838.pdf","type":"STI","links":{"original":"/api/citations/19930092838/downloads/19930092838.pdf","pdf":"/api/citations/19930092838/downloads/19930092838.pdf","fulltext":"/api/citations/19930092838/downloads/19930092838.txt"}}],"downloadsAvailable":true,"index":"submissions-2026-04-16-04-50"}