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NASA LRN 1015 (NASA TM 102840) (lrn1015-il)

NASA LRN 1015 (NASA TM 102840) - LRN 1015 airfoil used on the Northrop Grumman RQ-4 Global Hawk airfoil


Airfoil lrn1015-il
Details Dat file Parser  
(lrn1015-il) NASA LRN 1015 (NASA TM 102840)
LRN 1015 airfoil used on the Northrop Grumman RQ-4 Global Hawk airfoil
Max thickness 15.2% at 40% chord.
Max camber 4.9% at 44% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Selig format
NASA LRN 1015 (NASA TM 102840)
1.000000 0.000000
0.998379 0.000577
0.993525 0.002244
0.985471 0.004834
0.974268 0.008107
0.959990 0.011820
0.942728 0.015794
0.922595 0.020019
0.899721 0.024801
0.874255 0.030724
0.846362 0.037889
0.816223 0.046102
0.784032 0.055549
0.750000 0.066230
0.714346 0.077492
0.677302 0.088455
0.639109 0.098407
0.600013 0.106947
0.560268 0.113813
0.520133 0.118919
0.479867 0.122351
0.439732 0.124264
0.399987 0.124809
0.360891 0.124114
0.322698 0.122299
0.285654 0.119458
0.250000 0.115663
0.215968 0.110974
0.183777 0.105433
0.153638 0.099088
0.125745 0.092004
0.100279 0.084202
0.077405 0.075746
0.057272 0.066677
0.040010 0.057142
0.025732 0.046990
0.014529 0.036312
0.006475 0.026197
0.001621 0.017070
0.000000 0.000000
0.001621 -0.001976
0.006475 -0.004930
0.014529 -0.007513
0.025732 -0.010010
0.040010 -0.012525
0.057272 -0.014983
0.077405 -0.017226
0.100279 -0.019318
0.125745 -0.021214
0.153638 -0.022877
0.183777 -0.024304
0.215968 -0.025466
0.250000 -0.026357
0.285654 -0.026977
0.322698 -0.027302
0.360891 -0.027330
0.399987 -0.027065
0.439732 -0.026505
0.479867 -0.025652
0.520133 -0.024494
0.560268 -0.023028
0.600013 -0.021274
0.639109 -0.019239
0.677302 -0.016865
0.714346 -0.014081
0.750000 -0.010938
0.784032 -0.007663
0.816223 -0.004646
0.846362 -0.002130
0.874255 -0.000215
0.899721 0.001069
0.922595 0.001761
0.942728 0.001957
0.959990 0.001792
0.974268 0.001378
0.985471 0.000884
0.993525 0.000429
0.998379 0.000113
1.000000 0.000000
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Lednicer format dat file
Selig format dat file

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Polars for NASA LRN 1015 (NASA TM 102840) (lrn1015-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   lrn1015-il50,000921.9 at α=12.75°Mach=0 Ncrit=9Xfoil predictionDetails
   lrn1015-il50,000520.2 at α=11°Mach=0 Ncrit=5Xfoil predictionDetails
   lrn1015-il100,000939.8 at α=9.75°Mach=0 Ncrit=9Xfoil predictionDetails
   lrn1015-il100,000534 at α=9°Mach=0 Ncrit=5Xfoil predictionDetails
   lrn1015-il200,000970.8 at α=7.25°Mach=0 Ncrit=9Xfoil predictionDetails
   lrn1015-il200,000572.6 at α=6.5°Mach=0 Ncrit=5Xfoil predictionDetails
   lrn1015-il500,0009127.7 at α=6°Mach=0 Ncrit=9Xfoil predictionDetails
   lrn1015-il500,0005112.9 at α=4.75°Mach=0 Ncrit=5Xfoil predictionDetails
   lrn1015-il1,000,0009154.8 at α=5°Mach=0 Ncrit=9Xfoil predictionDetails
   lrn1015-il1,000,0005134.4 at α=3.25°Mach=0 Ncrit=5Xfoil predictionDetails
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