SA7026 (sa7026-il)
SA7026 - Selig / Ashok Gopalarathnam SA7026 low Reynolds number airfoil
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(sa7026-il) SA7026 Selig / Ashok Gopalarathnam SA7026 low Reynolds number airfoil Max thickness 9% at 32.9% chord. Max camber 3.8% at 47.1% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Selig format |
SA7026
1.00000 .00000
.99812 .00025
.99257 .00112
.98355 .00270
.97128 .00505
.95598 .00814
.93789 .01194
.91722 .01639
.89423 .02143
.86923 .02689
.84236 .03256
.81374 .03834
.78363 .04413
.75217 .04973
.71943 .05507
.68567 .06013
.65104 .06475
.61567 .06887
.57976 .07253
.54351 .07560
.50708 .07805
.47064 .07993
.43443 .08118
.39861 .08178
.36340 .08176
.32899 .08108
.29556 .07972
.26324 .07774
.23227 .07512
.20276 .07186
.17482 .06802
.14864 .06364
.12432 .05872
.10192 .05333
.08158 .04758
.06339 .04150
.04737 .03517
.03359 .02875
.02214 .02233
.01305 .01603
.00632 .01000
.00197 .00446
0.0 0.0
.00127 -.00358
.00625 -.00623
.01442 -.00876
.02556 -.01092
.03965 -.01261
.05671 -.01386
.07661 -.01470
.09927 -.01511
.12456 -.01513
.15235 -.01480
.18248 -.01415
.21478 -.01322
.24905 -.01205
.28508 -.01068
.32266 -.00916
.36155 -.00755
.40149 -.00589
.44222 -.00424
.48346 -.00264
.52494 -.00113
.56635 .00024
.60740 .00144
.64779 .00244
.68722 .00324
.72541 .00382
.76207 .00418
.79694 .00434
.82975 .00429
.86025 .00407
.88823 .00369
.91346 .00318
.93575 .00259
.95493 .00196
.97085 .00134
.98337 .00081
.99248 .00043
.99809 .00014
1.00000 0.00000
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Polars for SA7026 (sa7026-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| sa7026-il | 50,000 | 9 | 38.4 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sa7026-il | 50,000 | 5 | 40.6 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sa7026-il | 100,000 | 9 | 61.8 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sa7026-il | 100,000 | 5 | 61.9 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sa7026-il | 200,000 | 9 | 87.5 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sa7026-il | 200,000 | 5 | 82.8 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sa7026-il | 500,000 | 9 | 121.1 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sa7026-il | 500,000 | 5 | 106.4 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sa7026-il | 1,000,000 | 9 | 143.1 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sa7026-il | 1,000,000 | 5 | 120.7 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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