NREL's S822 Airfoil (s822-nr) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: NREL's S822 Airfoil (s822-nr) Reynolds number: 50,000 Max Cl/Cd: 23.67 at α=9.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s822-nr-50000-n5.txt Download as CSV file: xf-s822-nr-50000-n5.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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.000 -0.5165 0.11025 0.10291 -0.0670 1.0000 0.0670
-13.750 -0.5523 0.09910 0.09180 -0.0722 1.0000 0.0667
-13.500 -0.5868 0.08963 0.08231 -0.0766 1.0000 0.0658
-13.250 -0.6220 0.08142 0.07401 -0.0801 1.0000 0.0651
-13.000 -0.6532 0.07499 0.06746 -0.0821 1.0000 0.0647
-12.750 -0.6814 0.06996 0.06234 -0.0827 1.0000 0.0648
-12.500 -0.7064 0.06601 0.05827 -0.0820 1.0000 0.0651
-12.250 -0.7309 0.06280 0.05491 -0.0802 1.0000 0.0657
-12.000 -0.7537 0.06011 0.05206 -0.0775 1.0000 0.0663
-11.750 -0.7775 0.05785 0.04960 -0.0740 1.0000 0.0672
-11.500 -0.7936 0.05604 0.04774 -0.0704 1.0000 0.0686
-11.250 -0.8033 0.05471 0.04645 -0.0670 1.0000 0.0704
-11.000 -0.8170 0.05333 0.04498 -0.0631 1.0000 0.0720
-10.750 -0.8314 0.05194 0.04349 -0.0588 1.0000 0.0737
-10.500 -0.8469 0.05060 0.04201 -0.0542 1.0000 0.0758
-10.250 -0.8606 0.04920 0.04041 -0.0495 1.0000 0.0782
-10.000 -0.8679 0.04768 0.03874 -0.0455 1.0000 0.0817
-9.750 -0.8710 0.04652 0.03761 -0.0421 1.0000 0.0853
-9.500 -0.8728 0.04515 0.03608 -0.0387 1.0000 0.0900
-9.250 -0.8585 0.04351 0.03432 -0.0382 0.9965 0.0973
-9.000 -0.8416 0.04200 0.03254 -0.0381 0.9921 0.1074
-8.750 -0.8253 0.04070 0.03126 -0.0378 0.9875 0.1172
-8.500 -0.8074 0.03946 0.02996 -0.0378 0.9832 0.1296
-8.250 -0.7911 0.03830 0.02869 -0.0371 0.9788 0.1426
-8.000 -0.7744 0.03723 0.02757 -0.0366 0.9740 0.1581
-7.750 -0.7540 0.03624 0.02648 -0.0367 0.9699 0.1768
-7.500 -0.7390 0.03534 0.02558 -0.0356 0.9652 0.1948
-7.250 -0.7215 0.03452 0.02478 -0.0350 0.9604 0.2146
-7.000 -0.6998 0.03377 0.02399 -0.0350 0.9564 0.2389
-6.750 -0.6838 0.03310 0.02334 -0.0339 0.9518 0.2613
-6.500 -0.6661 0.03249 0.02271 -0.0330 0.9470 0.2862
-6.250 -0.6438 0.03196 0.02218 -0.0329 0.9429 0.3145
-6.000 -0.6242 0.03150 0.02172 -0.0322 0.9388 0.3427
-5.750 -0.6074 0.03108 0.02134 -0.0308 0.9338 0.3702
-5.500 -0.5850 0.03076 0.02104 -0.0303 0.9297 0.4012
-5.250 -0.5585 0.03057 0.02086 -0.0305 0.9264 0.4338
-5.000 -0.5446 0.03036 0.02068 -0.0283 0.9212 0.4618
-4.750 -0.5231 0.03030 0.02066 -0.0273 0.9167 0.4927
-4.500 -0.4970 0.03039 0.02078 -0.0269 0.9132 0.5236
-4.250 -0.4769 0.03052 0.02087 -0.0255 0.9090 0.5520
-4.000 -0.4583 0.03072 0.02107 -0.0236 0.9042 0.5780
-3.750 -0.4338 0.03099 0.02129 -0.0228 0.9002 0.6045
-3.500 -0.4058 0.03131 0.02152 -0.0227 0.8970 0.6309
-3.250 -0.3927 0.03154 0.02168 -0.0199 0.8917 0.6519
-3.000 -0.3719 0.03180 0.02186 -0.0186 0.8872 0.6742
-2.750 -0.3450 0.03224 0.02222 -0.0180 0.8837 0.6940
-2.500 -0.3255 0.03258 0.02247 -0.0163 0.8794 0.7129
-2.250 -0.3094 0.03285 0.02265 -0.0142 0.8744 0.7315
-2.000 -0.2854 0.03321 0.02292 -0.0133 0.8704 0.7493
-1.750 -0.2562 0.03364 0.02326 -0.0133 0.8673 0.7659
-1.500 -0.2456 0.03389 0.02345 -0.0103 0.8616 0.7818
-1.250 -0.2244 0.03420 0.02368 -0.0091 0.8571 0.7977
-1.000 -0.1968 0.03453 0.02393 -0.0090 0.8536 0.8132
-0.750 -0.1791 0.03479 0.02412 -0.0074 0.8488 0.8285
-0.500 -0.1603 0.03503 0.02430 -0.0060 0.8438 0.8435
-0.250 -0.1321 0.03531 0.02451 -0.0063 0.8399 0.8578
0.000 -0.1022 0.03560 0.02474 -0.0070 0.8363 0.8717
0.250 -0.0853 0.03583 0.02493 -0.0057 0.8304 0.8859
0.500 -0.0538 0.03611 0.02517 -0.0068 0.8260 0.8990
0.750 -0.0124 0.03647 0.02547 -0.0098 0.8230 0.9102
1.000 0.0144 0.03681 0.02580 -0.0107 0.8168 0.9219
1.250 0.0534 0.03716 0.02614 -0.0137 0.8121 0.9322
1.500 0.0978 0.03749 0.02645 -0.0175 0.8087 0.9421
1.750 0.1341 0.03792 0.02690 -0.0205 0.8025 0.9512
2.000 0.1774 0.03828 0.02728 -0.0245 0.7973 0.9595
2.250 0.2261 0.03856 0.02758 -0.0292 0.7936 0.9676
2.500 0.2582 0.03898 0.02805 -0.0317 0.7856 0.9770
2.750 0.3035 0.03921 0.02836 -0.0359 0.7806 0.9852
3.000 0.3391 0.03956 0.02877 -0.0388 0.7733 0.9950
3.250 0.3677 0.03970 0.02897 -0.0400 0.7664 1.0000
3.500 0.3672 0.03978 0.02907 -0.0362 0.7566 1.0000
3.750 0.3879 0.03968 0.02901 -0.0353 0.7500 1.0000
4.000 0.3833 0.03978 0.02912 -0.0308 0.7388 1.0000
4.250 0.3916 0.03980 0.02916 -0.0281 0.7295 1.0000
4.500 0.4109 0.03970 0.02912 -0.0268 0.7215 1.0000
4.750 0.4154 0.03984 0.02929 -0.0237 0.7100 1.0000
5.000 0.4311 0.03992 0.02941 -0.0220 0.6998 1.0000
5.250 0.4611 0.03972 0.02931 -0.0222 0.6919 1.0000
5.500 0.4750 0.03990 0.02955 -0.0204 0.6795 1.0000
5.750 0.4931 0.04003 0.02976 -0.0192 0.6675 1.0000
6.000 0.5166 0.03998 0.02982 -0.0185 0.6561 1.0000
6.250 0.5526 0.03937 0.02936 -0.0189 0.6475 1.0000
6.500 0.5727 0.03932 0.02943 -0.0177 0.6337 1.0000
6.750 0.5944 0.03915 0.02939 -0.0166 0.6196 1.0000
7.000 0.6176 0.03884 0.02922 -0.0154 0.6051 1.0000
7.250 0.6417 0.03839 0.02894 -0.0143 0.5902 1.0000
7.500 0.6669 0.03776 0.02847 -0.0130 0.5744 1.0000
7.750 0.6846 0.03760 0.02845 -0.0113 0.5545 1.0000
8.000 0.7049 0.03726 0.02826 -0.0096 0.5335 1.0000
8.250 0.7288 0.03666 0.02781 -0.0082 0.5107 1.0000
8.500 0.7566 0.03578 0.02703 -0.0068 0.4837 1.0000
8.750 0.7828 0.03512 0.02639 -0.0053 0.4497 1.0000
9.000 0.8105 0.03450 0.02561 -0.0039 0.4097 1.0000
9.250 0.8267 0.03492 0.02585 -0.0021 0.3689 1.0000
9.500 0.8379 0.03583 0.02659 -0.0001 0.3312 1.0000
9.750 0.8455 0.03709 0.02766 0.0018 0.2966 1.0000
10.000 0.8521 0.03851 0.02892 0.0036 0.2662 1.0000
10.250 0.8584 0.04007 0.03034 0.0052 0.2389 1.0000
10.500 0.8645 0.04171 0.03184 0.0067 0.2151 1.0000
10.750 0.8717 0.04338 0.03345 0.0080 0.1934 1.0000
11.000 0.8786 0.04513 0.03508 0.0093 0.1748 1.0000
11.250 0.8873 0.04685 0.03677 0.0103 0.1585 1.0000
11.500 0.8964 0.04861 0.03852 0.0113 0.1436 1.0000
11.750 0.9060 0.05037 0.04023 0.0121 0.1310 1.0000
12.000 0.9165 0.05218 0.04212 0.0129 0.1191 1.0000
12.250 0.9286 0.05399 0.04405 0.0136 0.1088 1.0000
12.500 0.9418 0.05579 0.04589 0.0143 0.1003 1.0000
12.750 0.9527 0.05770 0.04788 0.0149 0.0925 1.0000
13.000 0.9650 0.05980 0.05016 0.0155 0.0857 1.0000
13.250 0.9752 0.06194 0.05240 0.0160 0.0800 1.0000
13.500 0.9837 0.06433 0.05494 0.0164 0.0751 1.0000
13.750 0.9881 0.06725 0.05816 0.0169 0.0709 1.0000
14.000 0.9939 0.06993 0.06097 0.0172 0.0676 1.0000
14.250 1.0022 0.07251 0.06354 0.0174 0.0644 1.0000
14.500 0.9928 0.07682 0.06826 0.0173 0.0623 1.0000
14.750 0.9819 0.08146 0.07323 0.0168 0.0606 1.0000
15.000 0.9685 0.08646 0.07851 0.0157 0.0591 1.0000
15.250 0.9534 0.09200 0.08430 0.0141 0.0580 1.0000
15.500 0.9342 0.09848 0.09101 0.0116 0.0574 1.0000
15.750 0.9069 0.10685 0.09963 0.0076 0.0574 1.0000
16.000 0.8634 0.11970 0.11273 0.0002 0.0587 1.0000
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