NREL's S806A Airfoil (modified line 35) (s806a-nr) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: NREL's S806A Airfoil (modified line 35) (s806a-nr) Reynolds number: 50,000 Max Cl/Cd: 34.4 at α=7.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s806a-nr-50000.txt Download as CSV file: xf-s806a-nr-50000.csv |
XFOIL Version 6.96
Calculated polar for: NREL's S806A Airfoil
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.3913 0.11167 0.10514 -0.0268 1.0000 0.2400
-8.750 -0.4246 0.11528 0.10894 -0.0298 1.0000 0.2474
-8.500 -0.4605 0.11736 0.11119 -0.0274 1.0000 0.2486
-8.250 -0.3781 0.10152 0.09520 -0.0263 1.0000 0.2718
-8.000 -0.3870 0.10054 0.09431 -0.0241 1.0000 0.2841
-7.750 -0.4193 0.10176 0.09567 -0.0202 1.0000 0.2914
-7.500 -0.4618 0.10378 0.09784 -0.0154 1.0000 0.2949
-7.250 -0.5077 0.10602 0.10022 -0.0121 1.0000 0.2975
-7.000 -0.4334 0.09486 0.08898 -0.0102 1.0000 0.3293
-6.750 -0.4654 0.09536 0.08960 -0.0056 1.0000 0.3391
-6.500 -0.5164 0.09753 0.09192 -0.0021 1.0000 0.3459
-5.750 -0.4760 0.08690 0.08142 0.0104 1.0000 0.4344
-5.500 -0.4574 0.08411 0.07866 0.0144 1.0000 0.4819
-5.250 -0.4233 0.08388 0.07844 0.0169 1.0000 0.5343
-4.000 -0.3976 0.06941 0.06424 0.0312 1.0000 0.6753
-3.750 -0.4423 0.05351 0.04612 -0.0252 1.0000 0.1942
-3.500 -0.4070 0.04967 0.04149 -0.0273 1.0000 0.1459
-3.250 -0.3747 0.04618 0.03693 -0.0285 1.0000 0.1205
-3.000 -0.3501 0.04187 0.03241 -0.0293 1.0000 0.1126
-2.750 -0.3243 0.03957 0.02965 -0.0293 1.0000 0.1063
-1.250 -0.1870 0.03391 0.02268 -0.0256 1.0000 0.1066
-1.000 -0.1587 0.03300 0.02161 -0.0248 1.0000 0.1086
-0.750 -0.1299 0.03235 0.02078 -0.0244 1.0000 0.1153
-0.500 -0.0979 0.03142 0.01975 -0.0249 1.0000 0.1377
-0.250 -0.0831 0.02774 0.01894 -0.0186 1.0000 1.0000
0.000 -0.0600 0.02823 0.01879 -0.0183 1.0000 1.0000
0.250 -0.0373 0.02876 0.01893 -0.0184 1.0000 1.0000
0.500 -0.0148 0.02933 0.01922 -0.0186 1.0000 1.0000
0.750 0.0077 0.02994 0.01958 -0.0189 1.0000 1.0000
1.000 0.0304 0.03060 0.01999 -0.0193 1.0000 1.0000
1.250 0.0525 0.03129 0.02053 -0.0196 1.0000 1.0000
1.500 0.0746 0.03203 0.02112 -0.0200 1.0000 1.0000
1.750 0.0964 0.03282 0.02178 -0.0205 1.0000 1.0000
2.000 0.1181 0.03365 0.02252 -0.0209 1.0000 1.0000
2.250 0.1395 0.03454 0.02331 -0.0214 1.0000 1.0000
2.500 0.1606 0.03547 0.02419 -0.0219 1.0000 1.0000
3.000 0.2010 0.03749 0.02611 -0.0228 1.0000 1.0000
3.250 0.2195 0.03856 0.02717 -0.0230 1.0000 1.0000
3.500 0.2376 0.03970 0.02830 -0.0233 1.0000 1.0000
3.750 0.2551 0.04088 0.02950 -0.0235 1.0000 1.0000
4.000 0.2722 0.04213 0.03079 -0.0238 1.0000 1.0000
4.250 0.2886 0.04344 0.03214 -0.0240 1.0000 1.0000
4.500 0.3046 0.04484 0.03359 -0.0243 1.0000 1.0000
4.750 0.3200 0.04631 0.03513 -0.0246 1.0000 1.0000
5.000 0.3348 0.04788 0.03677 -0.0250 1.0000 1.0000
5.250 0.3488 0.04952 0.03852 -0.0253 1.0000 1.0000
5.500 0.5407 0.05328 0.04279 -0.0499 0.8374 1.0000
5.750 0.5838 0.05412 0.04387 -0.0520 0.8096 1.0000
6.000 0.7736 0.02775 0.01606 -0.0305 0.2491 1.0000
6.250 0.7480 0.03154 0.01829 -0.0252 0.0779 1.0000
6.500 0.7430 0.03432 0.02066 -0.0209 0.0469 1.0000
6.750 0.7855 0.05333 0.04414 -0.0606 0.6943 1.0000
7.000 0.8148 0.05157 0.04265 -0.0583 0.6605 1.0000
7.250 0.8467 0.04964 0.04102 -0.0556 0.6266 1.0000
7.500 0.9279 0.04156 0.03358 -0.0525 0.5893 1.0000
7.750 1.0117 0.02941 0.02126 -0.0434 0.4471 1.0000
8.000 1.0117 0.03130 0.02175 -0.0373 0.3194 1.0000
8.250 1.0181 0.03470 0.02478 -0.0334 0.2298 1.0000
8.500 1.0401 0.03742 0.02723 -0.0320 0.1787 1.0000
8.750 1.0850 0.04202 0.03175 -0.0332 0.1456 1.0000
9.000 1.0972 0.04328 0.03302 -0.0314 0.1301 1.0000
9.250 1.1138 0.04582 0.03543 -0.0306 0.1146 1.0000
9.500 1.1338 0.04814 0.03788 -0.0297 0.1058 1.0000
9.750 1.1598 0.05245 0.04213 -0.0300 0.0992 1.0000
10.000 1.1679 0.05574 0.04599 -0.0278 0.0966 1.0000
10.250 1.1720 0.05948 0.05022 -0.0256 0.0949 1.0000
10.500 1.1708 0.06342 0.05459 -0.0232 0.0940 1.0000
10.750 1.1642 0.06747 0.05903 -0.0207 0.0938 1.0000
11.000 1.1520 0.07153 0.06341 -0.0180 0.0940 1.0000
11.250 1.1346 0.07558 0.06773 -0.0153 0.0945 1.0000
11.500 1.1148 0.08003 0.07242 -0.0135 0.0951 1.0000
11.750 1.0936 0.08493 0.07752 -0.0125 0.0958 1.0000
12.000 1.0710 0.09030 0.08306 -0.0123 0.0966 1.0000
12.250 1.0492 0.09621 0.08911 -0.0129 0.0975 1.0000
12.500 1.0301 0.10262 0.09562 -0.0141 0.0985 1.0000
12.750 1.0223 0.10949 0.10253 -0.0152 0.0997 1.0000
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Polar data table (+)
Polar graphs
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