S9026 (9.5%) (s9026-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: S9026 (9.5%) (s9026-il) Reynolds number: 100,000 Max Cl/Cd: 33.79 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s9026-il-100000.txt Download as CSV file: xf-s9026-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: S9026 (9.5%)
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
------ -------- --------- --------- -------- -------- --------
-10.750 -0.6652 0.11627 0.11110 0.0110 1.0000 0.1489
-10.500 -0.7754 0.07898 0.07396 -0.0181 1.0000 0.0802
-10.250 -0.7837 0.07339 0.06837 -0.0201 1.0000 0.0790
-10.000 -0.8050 0.06777 0.06269 -0.0221 1.0000 0.0776
-9.750 -0.8318 0.06234 0.05710 -0.0223 1.0000 0.0762
-9.500 -0.8536 0.05637 0.05083 -0.0221 1.0000 0.0746
-9.250 -0.8686 0.05048 0.04447 -0.0211 1.0000 0.0733
-9.000 -0.8721 0.04559 0.03909 -0.0197 1.0000 0.0731
-8.750 -0.8661 0.04183 0.03489 -0.0183 1.0000 0.0742
-8.500 -0.8557 0.03889 0.03152 -0.0169 1.0000 0.0773
-8.250 -0.8441 0.03595 0.02794 -0.0152 1.0000 0.0799
-8.000 -0.8286 0.03276 0.02430 -0.0138 1.0000 0.0822
-7.750 -0.8080 0.03059 0.02207 -0.0130 1.0000 0.0860
-7.500 -0.7874 0.02882 0.02000 -0.0118 1.0000 0.0917
-7.250 -0.7663 0.02698 0.01805 -0.0109 1.0000 0.0987
-7.000 -0.7442 0.02554 0.01632 -0.0098 1.0000 0.1070
-6.750 -0.7217 0.02402 0.01485 -0.0090 1.0000 0.1169
-6.500 -0.6995 0.02279 0.01360 -0.0081 1.0000 0.1292
-6.250 -0.6770 0.02164 0.01245 -0.0071 1.0000 0.1430
-6.000 -0.6548 0.02064 0.01144 -0.0061 1.0000 0.1594
-5.750 -0.6326 0.01969 0.01046 -0.0050 1.0000 0.1788
-5.500 -0.6108 0.01871 0.00965 -0.0040 1.0000 0.1996
-5.250 -0.5891 0.01784 0.00888 -0.0029 1.0000 0.2252
-5.000 -0.5679 0.01703 0.00823 -0.0017 1.0000 0.2553
-4.750 -0.5469 0.01627 0.00764 -0.0004 1.0000 0.2896
-4.500 -0.5262 0.01559 0.00717 0.0010 1.0000 0.3284
-4.250 -0.5058 0.01497 0.00674 0.0024 1.0000 0.3713
-4.000 -0.4855 0.01441 0.00641 0.0039 1.0000 0.4173
-3.750 -0.4653 0.01392 0.00614 0.0056 1.0000 0.4659
-3.500 -0.4452 0.01348 0.00593 0.0073 1.0000 0.5153
-3.250 -0.4254 0.01309 0.00576 0.0092 1.0000 0.5643
-3.000 -0.4056 0.01278 0.00564 0.0113 1.0000 0.6138
-2.750 -0.3863 0.01253 0.00559 0.0135 1.0000 0.6621
-2.500 -0.3673 0.01234 0.00558 0.0159 1.0000 0.7087
-2.250 -0.3490 0.01222 0.00560 0.0186 1.0000 0.7547
-2.000 -0.3305 0.01216 0.00566 0.0213 1.0000 0.7993
-1.750 -0.3100 0.01218 0.00576 0.0238 1.0000 0.8431
-1.500 -0.2816 0.01231 0.00593 0.0247 1.0000 0.8854
-1.250 -0.2363 0.01259 0.00616 0.0223 1.0000 0.9227
-1.000 -0.1724 0.01289 0.00637 0.0160 1.0000 0.9505
-0.750 -0.0994 0.01303 0.00640 0.0075 1.0000 0.9711
-0.500 -0.0264 0.01292 0.00622 -0.0015 1.0000 0.9889
-0.250 0.0188 0.01268 0.00598 -0.0061 1.0000 1.0000
0.000 0.0000 0.01260 0.00592 0.0000 1.0000 1.0000
0.250 -0.0188 0.01268 0.00598 0.0061 1.0000 1.0000
0.500 0.0262 0.01292 0.00622 0.0015 0.9889 1.0000
0.750 0.0993 0.01303 0.00640 -0.0075 0.9711 1.0000
1.000 0.1727 0.01289 0.00637 -0.0161 0.9504 1.0000
1.250 0.2363 0.01259 0.00616 -0.0223 0.9227 1.0000
1.500 0.2817 0.01231 0.00593 -0.0248 0.8852 1.0000
1.750 0.3100 0.01218 0.00576 -0.0238 0.8430 1.0000
2.000 0.3306 0.01216 0.00566 -0.0214 0.7994 1.0000
2.250 0.3491 0.01222 0.00560 -0.0186 0.7547 1.0000
2.500 0.3675 0.01234 0.00559 -0.0160 0.7088 1.0000
2.750 0.3864 0.01253 0.00559 -0.0135 0.6621 1.0000
3.000 0.4057 0.01278 0.00565 -0.0113 0.6137 1.0000
3.250 0.4255 0.01309 0.00576 -0.0093 0.5643 1.0000
3.500 0.4454 0.01348 0.00593 -0.0073 0.5152 1.0000
3.750 0.4655 0.01392 0.00614 -0.0056 0.4659 1.0000
4.000 0.4856 0.01441 0.00641 -0.0040 0.4172 1.0000
4.250 0.5059 0.01497 0.00674 -0.0024 0.3711 1.0000
4.500 0.5263 0.01559 0.00717 -0.0010 0.3283 1.0000
4.750 0.5470 0.01627 0.00764 0.0004 0.2895 1.0000
5.000 0.5680 0.01703 0.00823 0.0016 0.2552 1.0000
5.250 0.5892 0.01784 0.00888 0.0028 0.2252 1.0000
5.500 0.6109 0.01871 0.00965 0.0040 0.1996 1.0000
5.750 0.6327 0.01969 0.01046 0.0050 0.1788 1.0000
6.000 0.6548 0.02064 0.01144 0.0061 0.1594 1.0000
6.250 0.6771 0.02165 0.01245 0.0071 0.1430 1.0000
6.500 0.6994 0.02278 0.01360 0.0080 0.1291 1.0000
6.750 0.7217 0.02402 0.01485 0.0090 0.1168 1.0000
7.000 0.7441 0.02553 0.01632 0.0098 0.1069 1.0000
7.250 0.7662 0.02698 0.01806 0.0109 0.0987 1.0000
7.500 0.7873 0.02884 0.02002 0.0119 0.0917 1.0000
7.750 0.8079 0.03059 0.02206 0.0130 0.0860 1.0000
8.000 0.8285 0.03277 0.02430 0.0138 0.0822 1.0000
8.250 0.8440 0.03594 0.02793 0.0152 0.0799 1.0000
8.500 0.8556 0.03889 0.03152 0.0169 0.0773 1.0000
8.750 0.8658 0.04187 0.03495 0.0184 0.0743 1.0000
9.000 0.8720 0.04556 0.03905 0.0198 0.0731 1.0000
9.250 0.8685 0.05045 0.04445 0.0212 0.0733 1.0000
9.500 0.8534 0.05637 0.05083 0.0221 0.0746 1.0000
9.750 0.8318 0.06232 0.05708 0.0223 0.0762 1.0000
10.000 0.8060 0.06769 0.06260 0.0222 0.0777 1.0000
10.250 0.7826 0.07350 0.06848 0.0200 0.0790 1.0000
10.500 0.7760 0.07892 0.07390 0.0182 0.0802 1.0000
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Polar data table (+)
Polar graphs
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