NREL's S822 Airfoil (s822-nr) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: NREL's S822 Airfoil (s822-nr) Reynolds number: 100,000 Max Cl/Cd: 42.69 at α=8.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s822-nr-100000.txt Download as CSV file: xf-s822-nr-100000.csv |
XFOIL Version 6.96
Calculated polar for: NREL's S822 Airfoil
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.500 -0.6989 0.07336 0.06791 -0.0884 1.0000 0.0556
-13.250 -0.7245 0.06903 0.06352 -0.0880 1.0000 0.0552
-13.000 -0.7554 0.06583 0.06023 -0.0862 1.0000 0.0552
-12.750 -0.7839 0.06340 0.05774 -0.0829 1.0000 0.0550
-12.500 -0.8100 0.06137 0.05564 -0.0790 1.0000 0.0546
-12.250 -0.8393 0.05953 0.05371 -0.0745 1.0000 0.0544
-12.000 -0.8699 0.05812 0.05219 -0.0693 1.0000 0.0546
-11.750 -0.8993 0.05676 0.05070 -0.0638 1.0000 0.0546
-11.500 -0.9270 0.05538 0.04920 -0.0578 1.0000 0.0545
-11.250 -0.9516 0.05391 0.04755 -0.0519 1.0000 0.0546
-11.000 -0.9722 0.05226 0.04565 -0.0466 1.0000 0.0551
-10.750 -0.9895 0.05066 0.04372 -0.0415 1.0000 0.0558
-10.500 -0.9905 0.04721 0.04024 -0.0389 1.0000 0.0579
-10.250 -0.9898 0.04545 0.03838 -0.0360 1.0000 0.0598
-10.000 -0.9893 0.04383 0.03660 -0.0328 1.0000 0.0626
-9.750 -0.9904 0.04227 0.03470 -0.0293 1.0000 0.0661
-9.500 -0.9860 0.03998 0.03217 -0.0266 1.0000 0.0694
-9.250 -0.9761 0.03858 0.03077 -0.0245 1.0000 0.0737
-9.000 -0.9690 0.03726 0.02915 -0.0219 1.0000 0.0788
-8.750 -0.9575 0.03556 0.02745 -0.0201 1.0000 0.0846
-8.500 -0.9469 0.03444 0.02616 -0.0179 1.0000 0.0914
-8.250 -0.9343 0.03307 0.02482 -0.0161 1.0000 0.0988
-8.000 -0.9220 0.03198 0.02348 -0.0140 1.0000 0.1078
-7.750 -0.9086 0.03089 0.02250 -0.0124 1.0000 0.1183
-7.500 -0.8951 0.02982 0.02147 -0.0107 1.0000 0.1300
-7.250 -0.8665 0.02901 0.02052 -0.0119 0.9957 0.1493
-7.000 -0.8402 0.02819 0.01990 -0.0128 0.9919 0.1700
-6.750 -0.8177 0.02753 0.01922 -0.0128 0.9884 0.1937
-6.500 -0.7919 0.02698 0.01879 -0.0135 0.9845 0.2207
-6.250 -0.7655 0.02653 0.01844 -0.0143 0.9805 0.2509
-6.000 -0.7438 0.02603 0.01802 -0.0141 0.9762 0.2810
-5.750 -0.7196 0.02567 0.01781 -0.0143 0.9727 0.3137
-5.500 -0.6907 0.02556 0.01785 -0.0153 0.9694 0.3508
-5.250 -0.6720 0.02519 0.01758 -0.0143 0.9652 0.3841
-5.000 -0.6492 0.02498 0.01751 -0.0140 0.9610 0.4201
-4.750 -0.6225 0.02498 0.01762 -0.0144 0.9575 0.4594
-4.500 -0.5965 0.02511 0.01791 -0.0144 0.9544 0.4977
-4.250 -0.5798 0.02503 0.01795 -0.0127 0.9504 0.5315
-4.000 -0.5570 0.02523 0.01822 -0.0120 0.9463 0.5678
-3.750 -0.5299 0.02571 0.01877 -0.0118 0.9429 0.6016
-3.500 -0.5063 0.02620 0.01929 -0.0111 0.9396 0.6320
-3.250 -0.4911 0.02642 0.01950 -0.0088 0.9358 0.6588
-3.000 -0.4704 0.02689 0.02001 -0.0073 0.9319 0.6829
-2.750 -0.4473 0.02750 0.02060 -0.0063 0.9290 0.7066
-2.500 -0.4229 0.02825 0.02134 -0.0053 0.9252 0.7280
-2.250 -0.4113 0.02852 0.02158 -0.0024 0.9213 0.7484
-2.000 -0.3955 0.02907 0.02212 0.0001 0.9182 0.7658
-1.750 -0.3733 0.02977 0.02278 0.0016 0.9143 0.7836
-1.500 -0.3519 0.03044 0.02341 0.0031 0.9101 0.8011
-1.250 -0.3433 0.03070 0.02365 0.0065 0.9066 0.8181
-1.000 -0.3279 0.03108 0.02400 0.0089 0.9025 0.8358
-0.750 -0.3001 0.03175 0.02459 0.0091 0.8978 0.8533
-0.500 -0.2914 0.03192 0.02474 0.0126 0.8926 0.8693
-0.250 -0.2756 0.03221 0.02501 0.0148 0.8881 0.8853
0.000 -0.2369 0.03300 0.02572 0.0131 0.8825 0.9007
0.250 -0.2212 0.03312 0.02582 0.0147 0.8760 0.9159
0.500 -0.1788 0.03377 0.02642 0.0117 0.8699 0.9291
0.750 -0.1374 0.03439 0.02699 0.0084 0.8626 0.9414
1.000 -0.0755 0.03526 0.02781 0.0013 0.8561 0.9482
1.250 -0.0188 0.03602 0.02852 -0.0050 0.8493 0.9566
1.500 0.0400 0.03669 0.02918 -0.0120 0.8421 0.9626
1.750 0.1095 0.03737 0.02983 -0.0200 0.8373 0.9693
2.000 0.1497 0.03775 0.03024 -0.0243 0.8278 0.9768
2.250 0.2183 0.03815 0.03065 -0.0322 0.8229 0.9827
2.500 0.2576 0.03851 0.03106 -0.0362 0.8129 0.9906
2.750 0.3271 0.03864 0.03123 -0.0441 0.8082 0.9955
3.000 0.3452 0.03885 0.03148 -0.0442 0.7971 1.0000
3.250 0.3536 0.03883 0.03147 -0.0419 0.7872 1.0000
3.500 0.3829 0.03860 0.03127 -0.0425 0.7798 1.0000
3.750 0.3783 0.03858 0.03125 -0.0380 0.7679 1.0000
4.000 0.3867 0.03844 0.03113 -0.0353 0.7575 1.0000
4.250 0.4195 0.03805 0.03079 -0.0359 0.7503 1.0000
4.500 0.4166 0.03791 0.03066 -0.0314 0.7380 1.0000
4.750 0.4237 0.03772 0.03049 -0.0282 0.7265 1.0000
5.000 0.4706 0.03698 0.02982 -0.0304 0.7208 1.0000
5.250 0.4790 0.03681 0.02968 -0.0274 0.7081 1.0000
5.500 0.4992 0.03655 0.02948 -0.0260 0.6962 1.0000
5.750 0.5557 0.03517 0.02822 -0.0288 0.6916 1.0000
6.000 0.5778 0.03473 0.02787 -0.0275 0.6788 1.0000
6.250 0.6063 0.03403 0.02726 -0.0268 0.6667 1.0000
6.500 0.6690 0.03156 0.02497 -0.0295 0.6629 1.0000
6.750 0.6989 0.03039 0.02394 -0.0285 0.6504 1.0000
7.000 0.7750 0.02664 0.02042 -0.0319 0.6473 1.0000
7.250 0.8172 0.02471 0.01863 -0.0321 0.6328 1.0000
7.500 0.8336 0.02405 0.01807 -0.0293 0.6118 1.0000
7.750 0.8758 0.02232 0.01643 -0.0295 0.5873 1.0000
8.000 0.8869 0.02210 0.01623 -0.0263 0.5533 1.0000
8.250 0.9073 0.02167 0.01569 -0.0242 0.5068 1.0000
8.500 0.9256 0.02168 0.01534 -0.0218 0.4449 1.0000
8.750 0.9316 0.02255 0.01579 -0.0185 0.3870 1.0000
9.000 0.9329 0.02379 0.01663 -0.0150 0.3369 1.0000
9.250 0.9339 0.02517 0.01768 -0.0118 0.2932 1.0000
9.500 0.9359 0.02664 0.01887 -0.0089 0.2546 1.0000
9.750 0.9397 0.02815 0.02010 -0.0064 0.2219 1.0000
10.000 0.9466 0.02963 0.02137 -0.0043 0.1945 1.0000
10.250 0.9558 0.03112 0.02263 -0.0026 0.1719 1.0000
10.500 0.9669 0.03255 0.02401 -0.0011 0.1521 1.0000
10.750 0.9797 0.03399 0.02534 0.0002 0.1358 1.0000
11.000 0.9942 0.03546 0.02674 0.0013 0.1215 1.0000
11.250 1.0107 0.03697 0.02823 0.0023 0.1092 1.0000
11.500 1.0312 0.03859 0.02983 0.0028 0.0988 1.0000
11.750 1.0565 0.04031 0.03143 0.0027 0.0892 1.0000
12.000 1.0692 0.04196 0.03331 0.0040 0.0825 1.0000
12.250 1.1026 0.04429 0.03563 0.0032 0.0759 1.0000
12.500 1.1116 0.04623 0.03787 0.0048 0.0715 1.0000
12.750 1.1264 0.04808 0.03974 0.0055 0.0670 1.0000
13.000 1.1469 0.05157 0.04345 0.0056 0.0638 1.0000
13.250 1.1435 0.05420 0.04646 0.0080 0.0621 1.0000
13.500 1.1384 0.05687 0.04944 0.0102 0.0600 1.0000
13.750 1.1365 0.05948 0.05226 0.0118 0.0579 1.0000
14.000 1.1370 0.06209 0.05500 0.0129 0.0559 1.0000
14.250 1.1366 0.06547 0.05853 0.0139 0.0546 1.0000
14.500 1.1314 0.07008 0.06333 0.0147 0.0536 1.0000
14.750 1.1132 0.07514 0.06864 0.0157 0.0532 1.0000
15.000 1.0908 0.07956 0.07334 0.0165 0.0531 1.0000
15.250 1.0661 0.08447 0.07852 0.0166 0.0530 1.0000
15.500 1.0419 0.08998 0.08426 0.0159 0.0531 1.0000
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