S8064 (s8064-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: S8064 (s8064-il) Reynolds number: 50,000 Max Cl/Cd: 29.31 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s8064-il-50000-n5.txt Download as CSV file: xf-s8064-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: S8064
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
------ -------- --------- --------- -------- -------- --------
-11.500 -0.5236 0.09577 0.08870 -0.0525 1.0000 0.0392
-11.250 -0.5326 0.08984 0.08281 -0.0557 1.0000 0.0389
-11.000 -0.5443 0.08416 0.07714 -0.0589 1.0000 0.0386
-10.750 -0.5613 0.07860 0.07158 -0.0619 1.0000 0.0382
-10.500 -0.5809 0.07385 0.06680 -0.0637 1.0000 0.0379
-10.250 -0.5999 0.07016 0.06308 -0.0638 1.0000 0.0375
-10.000 -0.6258 0.06710 0.05995 -0.0619 1.0000 0.0375
-9.750 -0.6478 0.06510 0.05793 -0.0583 1.0000 0.0369
-9.500 -0.6748 0.06335 0.05611 -0.0531 1.0000 0.0370
-9.250 -0.6963 0.06115 0.05377 -0.0485 1.0000 0.0370
-9.000 -0.7132 0.05888 0.05133 -0.0442 1.0000 0.0369
-8.750 -0.7285 0.05633 0.04852 -0.0398 1.0000 0.0373
-8.500 -0.7379 0.05374 0.04565 -0.0359 1.0000 0.0374
-8.250 -0.7448 0.05091 0.04243 -0.0320 1.0000 0.0380
-8.000 -0.7460 0.04818 0.03931 -0.0286 1.0000 0.0384
-7.750 -0.7431 0.04542 0.03609 -0.0254 1.0000 0.0390
-7.500 -0.7357 0.04280 0.03317 -0.0228 1.0000 0.0399
-7.250 -0.7258 0.04078 0.03102 -0.0207 1.0000 0.0418
-7.000 -0.7142 0.03904 0.02906 -0.0185 1.0000 0.0448
-6.750 -0.6993 0.03715 0.02672 -0.0164 1.0000 0.0489
-6.500 -0.6835 0.03533 0.02480 -0.0147 1.0000 0.0530
-6.250 -0.6672 0.03393 0.02319 -0.0129 1.0000 0.0600
-6.000 -0.6510 0.03247 0.02171 -0.0111 1.0000 0.0684
-5.750 -0.6344 0.03119 0.02033 -0.0092 1.0000 0.0796
-5.500 -0.6188 0.02998 0.01908 -0.0073 1.0000 0.0952
-5.250 -0.6033 0.02883 0.01784 -0.0054 1.0000 0.1142
-5.000 -0.5892 0.02765 0.01676 -0.0035 1.0000 0.1385
-4.750 -0.5750 0.02649 0.01572 -0.0017 1.0000 0.1731
-4.500 -0.5621 0.02518 0.01479 0.0002 1.0000 0.2274
-4.250 -0.5508 0.02378 0.01401 0.0022 1.0000 0.3245
-4.000 -0.5337 0.02275 0.01386 0.0040 0.9961 0.4848
-3.750 -0.5122 0.02272 0.01431 0.0064 0.9920 0.6117
-3.500 -0.4880 0.02320 0.01482 0.0085 0.9874 0.6935
-3.250 -0.4630 0.02370 0.01514 0.0100 0.9828 0.7501
-3.000 -0.4387 0.02415 0.01541 0.0117 0.9779 0.7925
-2.750 -0.4068 0.02476 0.01580 0.0122 0.9739 0.8283
-2.500 -0.3683 0.02539 0.01619 0.0113 0.9707 0.8600
-2.250 -0.3270 0.02586 0.01639 0.0093 0.9671 0.8859
-2.000 -0.2772 0.02630 0.01656 0.0052 0.9642 0.9048
-1.750 -0.2264 0.02664 0.01664 0.0003 0.9612 0.9195
-1.500 -0.1733 0.02693 0.01668 -0.0053 0.9585 0.9313
-1.250 -0.1291 0.02706 0.01663 -0.0093 0.9541 0.9432
-1.000 -0.0808 0.02721 0.01660 -0.0143 0.9500 0.9531
-0.750 -0.0312 0.02738 0.01663 -0.0195 0.9462 0.9623
-0.500 0.0122 0.02751 0.01666 -0.0237 0.9414 0.9723
-0.250 0.0561 0.02760 0.01666 -0.0280 0.9361 0.9815
0.000 0.1046 0.02773 0.01674 -0.0332 0.9318 0.9896
0.250 0.1472 0.02783 0.01680 -0.0374 0.9262 0.9986
0.500 0.1754 0.02795 0.01690 -0.0387 0.9188 1.0000
0.750 0.1939 0.02807 0.01702 -0.0381 0.9098 1.0000
1.000 0.2232 0.02823 0.01720 -0.0394 0.9028 1.0000
1.250 0.2366 0.02836 0.01734 -0.0377 0.8923 1.0000
1.500 0.2583 0.02853 0.01753 -0.0375 0.8837 1.0000
1.750 0.2814 0.02869 0.01773 -0.0374 0.8749 1.0000
2.000 0.2941 0.02885 0.01792 -0.0354 0.8640 1.0000
2.250 0.3161 0.02901 0.01815 -0.0349 0.8548 1.0000
2.500 0.3394 0.02916 0.01836 -0.0347 0.8454 1.0000
2.750 0.3517 0.02931 0.01856 -0.0324 0.8335 1.0000
3.000 0.3688 0.02945 0.01877 -0.0309 0.8223 1.0000
3.250 0.4052 0.02949 0.01896 -0.0325 0.8143 1.0000
3.500 0.4190 0.02959 0.01912 -0.0303 0.8012 1.0000
3.750 0.4360 0.02964 0.01927 -0.0285 0.7881 1.0000
4.000 0.4555 0.02965 0.01941 -0.0270 0.7747 1.0000
4.250 0.4777 0.02958 0.01947 -0.0258 0.7611 1.0000
4.500 0.5028 0.02937 0.01942 -0.0249 0.7468 1.0000
4.750 0.5311 0.02899 0.01922 -0.0242 0.7318 1.0000
5.000 0.5641 0.02826 0.01874 -0.0237 0.7158 1.0000
5.250 0.5838 0.02777 0.01842 -0.0213 0.6949 1.0000
5.500 0.6183 0.02662 0.01751 -0.0203 0.6723 1.0000
5.750 0.6443 0.02575 0.01684 -0.0181 0.6422 1.0000
6.000 0.6630 0.02524 0.01645 -0.0152 0.6037 1.0000
6.250 0.6893 0.02459 0.01583 -0.0130 0.5503 1.0000
6.500 0.7134 0.02434 0.01537 -0.0107 0.4721 1.0000
6.750 0.7254 0.02489 0.01543 -0.0073 0.3802 1.0000
7.000 0.7274 0.02605 0.01605 -0.0033 0.3050 1.0000
7.250 0.7289 0.02746 0.01703 0.0003 0.2452 1.0000
7.500 0.7336 0.02895 0.01817 0.0031 0.2014 1.0000
7.750 0.7421 0.03041 0.01943 0.0054 0.1697 1.0000
8.000 0.7530 0.03188 0.02073 0.0073 0.1471 1.0000
8.250 0.7679 0.03325 0.02210 0.0087 0.1281 1.0000
8.500 0.7872 0.03466 0.02353 0.0098 0.1136 1.0000
8.750 0.8092 0.03608 0.02501 0.0104 0.1000 1.0000
9.000 0.8388 0.03774 0.02672 0.0103 0.0892 1.0000
9.250 0.8631 0.03943 0.02849 0.0106 0.0791 1.0000
9.500 0.8911 0.04156 0.03100 0.0105 0.0703 1.0000
9.750 0.9127 0.04376 0.03326 0.0108 0.0638 1.0000
10.000 0.9275 0.04607 0.03597 0.0122 0.0581 1.0000
10.250 0.9407 0.04817 0.03810 0.0132 0.0540 1.0000
10.500 0.9488 0.05119 0.04155 0.0151 0.0513 1.0000
10.750 0.9490 0.05412 0.04490 0.0175 0.0489 1.0000
11.000 0.9468 0.05680 0.04787 0.0198 0.0468 1.0000
11.250 0.9437 0.05950 0.05078 0.0218 0.0450 1.0000
11.500 0.9391 0.06245 0.05393 0.0235 0.0440 1.0000
11.750 0.9322 0.06574 0.05741 0.0250 0.0432 1.0000
12.000 0.9223 0.06940 0.06126 0.0261 0.0427 1.0000
12.250 0.9084 0.07344 0.06550 0.0268 0.0425 1.0000
12.750 0.8669 0.08329 0.07580 0.0257 0.0425 1.0000
13.000 0.8333 0.09062 0.08338 0.0224 0.0431 1.0000
13.250 0.7701 0.10621 0.09920 0.0119 0.0463 1.0000
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Polar data table (+)
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