S9000 (9%) (s9000-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: S9000 (9%) (s9000-il) Reynolds number: 500,000 Max Cl/Cd: 84.39 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s9000-il-500000-n5.txt Download as CSV file: xf-s9000-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: S9000 (9%)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.4711 0.07338 0.07118 -0.0319 1.0000 0.0051
-8.250 -0.4841 0.06933 0.06719 -0.0329 1.0000 0.0050
-8.000 -0.5016 0.06400 0.06192 -0.0363 1.0000 0.0050
-7.750 -0.5123 0.05700 0.05488 -0.0417 1.0000 0.0049
-7.500 -0.5127 0.04743 0.04510 -0.0486 0.9981 0.0048
-7.250 -0.5018 0.03278 0.02974 -0.0578 0.9920 0.0045
-7.000 -0.4819 0.02434 0.02040 -0.0612 0.9869 0.0043
-6.750 -0.4532 0.02024 0.01563 -0.0632 0.9842 0.0042
-6.500 -0.4261 0.01787 0.01284 -0.0637 0.9803 0.0042
-6.250 -0.3971 0.01623 0.01090 -0.0644 0.9763 0.0042
-6.000 -0.3656 0.01489 0.00933 -0.0655 0.9732 0.0042
-5.750 -0.3327 0.01379 0.00806 -0.0668 0.9709 0.0043
-5.500 -0.3058 0.01293 0.00707 -0.0667 0.9645 0.0045
-5.250 -0.2740 0.01218 0.00620 -0.0676 0.9599 0.0046
-5.000 -0.2423 0.01150 0.00541 -0.0685 0.9549 0.0048
-4.750 -0.2124 0.01098 0.00480 -0.0689 0.9476 0.0051
-4.500 -0.1793 0.01039 0.00414 -0.0700 0.9424 0.0058
-4.250 -0.1482 0.00999 0.00367 -0.0707 0.9345 0.0071
-4.000 -0.1148 0.00957 0.00322 -0.0718 0.9272 0.0102
-3.750 -0.0822 0.00919 0.00286 -0.0728 0.9169 0.0196
-3.500 -0.0508 0.00886 0.00257 -0.0735 0.9040 0.0348
-3.250 -0.0208 0.00852 0.00230 -0.0740 0.8894 0.0627
-3.000 0.0080 0.00825 0.00207 -0.0742 0.8737 0.0937
-2.750 0.0358 0.00799 0.00189 -0.0741 0.8577 0.1334
-2.500 0.0631 0.00775 0.00174 -0.0740 0.8417 0.1801
-2.250 0.0901 0.00754 0.00160 -0.0739 0.8254 0.2300
-2.000 0.1168 0.00731 0.00150 -0.0737 0.8076 0.2931
-1.750 0.1434 0.00712 0.00141 -0.0734 0.7887 0.3544
-1.500 0.1700 0.00696 0.00133 -0.0732 0.7701 0.4119
-1.000 0.2229 0.00661 0.00125 -0.0726 0.7340 0.5507
-0.750 0.2488 0.00646 0.00125 -0.0722 0.7148 0.6261
-0.500 0.2747 0.00639 0.00127 -0.0716 0.6949 0.6860
-0.250 0.3007 0.00642 0.00129 -0.0711 0.6732 0.7248
0.000 0.3267 0.00646 0.00131 -0.0705 0.6506 0.7545
0.250 0.3524 0.00652 0.00134 -0.0699 0.6292 0.7818
0.500 0.3784 0.00659 0.00138 -0.0694 0.6088 0.8040
0.750 0.4042 0.00667 0.00142 -0.0688 0.5887 0.8236
1.250 0.4545 0.00687 0.00153 -0.0673 0.5445 0.8624
1.500 0.4789 0.00699 0.00159 -0.0665 0.5181 0.8811
2.000 0.5263 0.00722 0.00172 -0.0644 0.4726 0.9228
2.250 0.5518 0.00732 0.00178 -0.0637 0.4526 0.9486
2.500 0.5841 0.00747 0.00185 -0.0647 0.4294 0.9802
2.750 0.6135 0.00766 0.00194 -0.0651 0.4060 1.0000
3.000 0.6400 0.00788 0.00207 -0.0649 0.3845 1.0000
3.250 0.6661 0.00814 0.00221 -0.0647 0.3575 1.0000
3.500 0.6921 0.00841 0.00236 -0.0645 0.3305 1.0000
3.750 0.7185 0.00865 0.00252 -0.0643 0.3096 1.0000
4.000 0.7447 0.00892 0.00271 -0.0640 0.2888 1.0000
4.250 0.7708 0.00919 0.00290 -0.0638 0.2677 1.0000
4.500 0.7969 0.00945 0.00310 -0.0636 0.2497 1.0000
4.750 0.8228 0.00975 0.00333 -0.0633 0.2309 1.0000
5.000 0.8479 0.01012 0.00359 -0.0629 0.2042 1.0000
5.250 0.8732 0.01047 0.00386 -0.0626 0.1814 1.0000
5.500 0.8987 0.01080 0.00413 -0.0623 0.1644 1.0000
5.750 0.9241 0.01113 0.00442 -0.0620 0.1497 1.0000
6.000 0.9493 0.01148 0.00473 -0.0616 0.1360 1.0000
6.250 0.9745 0.01182 0.00505 -0.0613 0.1234 1.0000
6.500 0.9993 0.01220 0.00539 -0.0609 0.1097 1.0000
6.750 1.0238 0.01262 0.00576 -0.0604 0.0958 1.0000
7.000 1.0482 0.01302 0.00617 -0.0600 0.0848 1.0000
7.250 1.0721 0.01348 0.00659 -0.0595 0.0729 1.0000
7.500 1.0959 0.01395 0.00703 -0.0589 0.0620 1.0000
7.750 1.1193 0.01443 0.00750 -0.0584 0.0526 1.0000
8.000 1.1424 0.01495 0.00800 -0.0577 0.0446 1.0000
8.250 1.1656 0.01544 0.00852 -0.0571 0.0389 1.0000
8.500 1.1884 0.01595 0.00906 -0.0565 0.0343 1.0000
8.750 1.2111 0.01646 0.00960 -0.0558 0.0300 1.0000
9.000 1.2328 0.01705 0.01022 -0.0550 0.0255 1.0000
9.250 1.2547 0.01760 0.01081 -0.0542 0.0217 1.0000
9.500 1.2752 0.01827 0.01151 -0.0533 0.0180 1.0000
9.750 1.2955 0.01894 0.01224 -0.0523 0.0149 1.0000
10.000 1.3146 0.01970 0.01303 -0.0512 0.0123 1.0000
10.250 1.3334 0.02044 0.01382 -0.0501 0.0102 1.0000
10.500 1.3508 0.02128 0.01472 -0.0488 0.0087 1.0000
10.750 1.3688 0.02200 0.01552 -0.0476 0.0074 1.0000
11.000 1.3844 0.02288 0.01647 -0.0461 0.0064 1.0000
11.250 1.3990 0.02379 0.01747 -0.0444 0.0058 1.0000
11.500 1.4120 0.02461 0.01841 -0.0425 0.0052 1.0000
11.750 1.4228 0.02551 0.01943 -0.0403 0.0048 1.0000
12.000 1.4316 0.02653 0.02054 -0.0380 0.0043 1.0000
12.250 1.4376 0.02777 0.02188 -0.0355 0.0039 1.0000
12.500 1.4445 0.02896 0.02319 -0.0333 0.0035 1.0000
12.750 1.4496 0.03033 0.02470 -0.0311 0.0033 1.0000
13.000 1.4542 0.03181 0.02630 -0.0292 0.0029 1.0000
13.250 1.4567 0.03353 0.02815 -0.0275 0.0027 1.0000
13.500 1.4571 0.03558 0.03032 -0.0260 0.0025 1.0000
13.750 1.4536 0.03815 0.03303 -0.0247 0.0023 1.0000
14.000 1.4513 0.04079 0.03582 -0.0240 0.0022 1.0000
14.250 1.4473 0.04386 0.03905 -0.0238 0.0020 1.0000
14.500 1.4419 0.04733 0.04268 -0.0241 0.0020 1.0000
14.750 1.4343 0.05137 0.04688 -0.0249 0.0018 1.0000
15.000 1.4249 0.05599 0.05166 -0.0264 0.0018 1.0000
15.250 1.4133 0.06128 0.05712 -0.0286 0.0017 1.0000
15.500 1.4002 0.06715 0.06316 -0.0313 0.0017 1.0000
15.750 1.3848 0.07376 0.06994 -0.0347 0.0016 1.0000
16.000 1.3647 0.08164 0.07800 -0.0389 0.0017 1.0000
16.250 1.3438 0.09004 0.08657 -0.0435 0.0017 1.0000
16.500 1.3206 0.09925 0.09595 -0.0487 0.0018 1.0000
16.750 1.2967 0.10892 0.10578 -0.0541 0.0018 1.0000
17.000 1.2721 0.11905 0.11606 -0.0598 0.0019 1.0000
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Polar data table (+)
Polar graphs
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