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FX 60-177 AIRFOIL (fx60177-il)

FX 60-177 AIRFOIL - Wortmann FX 60-177 airfoil


Airfoil fx60177-il
Details Dat file Parser  
(fx60177-il) FX 60-177 AIRFOIL
Wortmann FX 60-177 airfoil
Max thickness 17.7% at 37.1% chord.
Max camber 2.7% at 77.8% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
FX 60-177 AIRFOIL
       49.       49.

 0.0000000 0.0000000
 0.0010200 0.0098000
 0.0042200 0.0178700
 0.0096000 0.0257800
 0.0170200 0.0339800
 0.0265000 0.0417600
 0.0380200 0.0497100
 0.0515800 0.0572900
 0.0669400 0.0646800
 0.0842200 0.0715300
 0.1033000 0.0780000
 0.1240300 0.0837700
 0.1464300 0.0891600
 0.1703700 0.0937800
 0.1955800 0.0980100
 0.2222100 0.1014500
 0.2499800 0.1044900
 0.2780100 0.1067700
 0.3086100 0.1086800
 0.3393300 0.1098400
 0.3705600 0.1105900
 0.4024300 0.1106200
 0.4346900 0.1102300
 0.4673300 0.1091200
 0.4999700 0.1075900
 0.5327400 0.1054700
 0.5652500 0.1029200
 0.5975000 0.0996800
 0.6293800 0.0960200
 0.6607400 0.0917200
 0.6913300 0.0869900
 0.7211500 0.0817500
 0.7499501 0.0761300
 0.7777300 0.0702000
 0.8043500 0.0640000
 0.8297000 0.0576200
 0.8535000 0.0511600
 0.8759000 0.0446900
 0.8964400 0.0383500
 0.9157100 0.0323200
 0.9329900 0.0264700
 0.9484800 0.0210400
 0.9619200 0.0161200
 0.9734400 0.0116700
 0.9829100 0.0077700
 0.9903400 0.0046100
 0.9957100 0.0022100
 0.9989100 0.0006800
 1.0000000 0.0000000

 0.0000000 0.0000000
 0.0010200 -.0015400
 0.0042200 -.0055600
 0.0096000 -.0099700
 0.0170200 -.0145900
 0.0265000 -.0194000
 0.0380200 -.0240800
 0.0515800 -.0288200
 0.0669400 -.0335200
 0.0842200 -.0380600
 0.1033000 -.0423400
 0.1240300 -.0464200
 0.1464300 -.0501500
 0.1703700 -.0536900
 0.1955800 -.0568300
 0.2222100 -.0597100
 0.2499800 -.0620400
 0.2780100 -.0640400
 0.3086100 -.0654400
 0.3393300 -.0663500
 0.3705600 -.0666300
 0.4024300 -.0664700
 0.4346900 -.0656300
 0.4673300 -.0643200
 0.4999700 -.0622700
 0.5327400 -.0596100
 0.5652500 -.0561100
 0.5975000 -.0519700
 0.6293800 -.0469400
 0.6607400 -.0413600
 0.6913300 -.0351700
 0.7211500 -.0287200
 0.7499501 -.0220900
 0.7777300 -.0157500
 0.8043500 -.0098200
 0.8297000 -.0046900
 0.8535000 -.0003200
 0.8759000 0.0030900
 0.8964400 0.0056500
 0.9157100 0.0073700
 0.9329900 0.0082700
 0.9484800 0.0084100
 0.9619200 0.0078600
 0.9734400 0.0067200
 0.9829100 0.0051700
 0.9903400 0.0034800
 0.9957100 0.0018500
 0.9989100 0.0006400
 1.0000000 0.0000000
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Polars for FX 60-177 AIRFOIL (fx60177-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   fx60177-il50,000924.2 at α=9°Mach=0 Ncrit=9Xfoil predictionDetails
   fx60177-il50,000525 at α=10°Mach=0 Ncrit=5Xfoil predictionDetails
   fx60177-il100,000940.4 at α=9°Mach=0 Ncrit=9Xfoil predictionDetails
   fx60177-il100,000537.3 at α=7.25°Mach=0 Ncrit=5Xfoil predictionDetails
   fx60177-il200,000949.3 at α=5.75°Mach=0 Ncrit=9Xfoil predictionDetails
   fx60177-il200,000553.3 at α=4.25°Mach=0 Ncrit=5Xfoil predictionDetails
   fx60177-il500,000981.5 at α=3°Mach=0 Ncrit=9Xfoil predictionDetails
   fx60177-il500,000574.6 at α=1.5°Mach=0 Ncrit=5Xfoil predictionDetails
   fx60177-il1,000,0009105.5 at α=1.5°Mach=0 Ncrit=9Xfoil predictionDetails
   fx60177-il1,000,000585.8 at α=3.75°Mach=0 Ncrit=5Xfoil predictionDetails
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