GOE 393 AIRFOIL (goe393-il) Xfoil prediction polar at RE=100,000 Ncrit=5
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Airfoil: GOE 393 AIRFOIL (goe393-il) Reynolds number: 100,000 Max Cl/Cd: 57.29 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe393-il-100000-n5.txt Download as CSV file: xf-goe393-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 393 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.4488 0.10560 0.10083 0.0116 1.0000 0.0501
-8.000 -0.4432 0.10258 0.09785 0.0093 1.0000 0.0522
-7.750 -0.4405 0.10027 0.09562 0.0046 1.0000 0.0538
-7.500 -0.4322 0.09733 0.09271 -0.0023 1.0000 0.0543
-7.250 -0.4179 0.09382 0.08918 -0.0105 1.0000 0.0546
-7.000 -0.4122 0.08876 0.08420 -0.0026 1.0000 0.0564
-6.750 -0.4001 0.08548 0.08094 -0.0035 1.0000 0.0585
-6.500 -0.3862 0.08199 0.07745 -0.0067 1.0000 0.0602
-6.250 -0.3697 0.07840 0.07386 -0.0112 1.0000 0.0625
-6.000 -0.3373 0.07486 0.07016 -0.0242 1.0000 0.0654
-5.750 -0.3118 0.07065 0.06582 -0.0304 1.0000 0.0659
-5.250 -0.2785 0.06002 0.05512 -0.0331 1.0000 0.0541
-5.000 -0.2626 0.05678 0.05190 -0.0332 1.0000 0.0527
-4.750 -0.2323 0.05229 0.04721 -0.0384 1.0000 0.0539
-4.500 -0.2083 0.04865 0.04347 -0.0407 1.0000 0.0537
-4.250 -0.1838 0.04533 0.04006 -0.0426 0.9954 0.0529
-4.000 -0.1423 0.04110 0.03555 -0.0481 0.9587 0.0523
-3.750 -0.1000 0.03660 0.03062 -0.0530 0.9181 0.0535
-3.250 -0.0316 0.02952 0.02258 -0.0572 0.8349 0.0541
-3.000 -0.0034 0.02670 0.01920 -0.0575 0.8040 0.0542
-2.750 0.0241 0.02409 0.01600 -0.0574 0.7788 0.0547
-2.500 0.0502 0.02280 0.01437 -0.0570 0.7565 0.0556
-2.250 0.0766 0.02196 0.01326 -0.0566 0.7370 0.0570
-2.000 0.1034 0.02138 0.01243 -0.0562 0.7197 0.0602
-1.750 0.1314 0.02013 0.01077 -0.0559 0.7049 0.0631
-1.500 0.1594 0.01883 0.00904 -0.0555 0.6918 0.0650
-1.250 0.1867 0.01808 0.00812 -0.0551 0.6791 0.0672
-1.000 0.2139 0.01766 0.00761 -0.0548 0.6668 0.0705
-0.750 0.2416 0.01706 0.00681 -0.0544 0.6555 0.0767
-0.500 0.2688 0.01674 0.00644 -0.0540 0.6449 0.0842
-0.250 0.2961 0.01648 0.00606 -0.0536 0.6343 0.0962
0.000 0.3234 0.01641 0.00594 -0.0534 0.6235 0.1104
0.250 0.3505 0.01637 0.00585 -0.0531 0.6136 0.1252
0.500 0.3775 0.01628 0.00574 -0.0528 0.6038 0.1398
0.750 0.4046 0.01615 0.00555 -0.0525 0.5937 0.1493
1.000 0.4311 0.01595 0.00535 -0.0520 0.5845 0.1540
1.250 0.4584 0.01585 0.00520 -0.0516 0.5746 0.1590
1.500 0.4858 0.01580 0.00512 -0.0513 0.5651 0.1647
1.750 0.5128 0.01577 0.00506 -0.0510 0.5568 0.1736
2.000 0.5402 0.01575 0.00509 -0.0508 0.5467 0.1835
2.250 0.5674 0.01576 0.00511 -0.0505 0.5379 0.1966
2.500 0.5947 0.01572 0.00519 -0.0503 0.5286 0.2276
3.000 0.6521 0.01450 0.00537 -0.0503 0.5117 1.0000
3.250 0.6792 0.01473 0.00557 -0.0500 0.5025 1.0000
3.500 0.7059 0.01497 0.00574 -0.0496 0.4948 1.0000
3.750 0.7329 0.01522 0.00600 -0.0493 0.4857 1.0000
4.000 0.7596 0.01548 0.00624 -0.0490 0.4783 1.0000
4.250 0.7863 0.01575 0.00655 -0.0487 0.4697 1.0000
4.500 0.8128 0.01598 0.00680 -0.0483 0.4592 1.0000
4.750 0.8388 0.01614 0.00696 -0.0478 0.4451 1.0000
5.000 0.8646 0.01629 0.00714 -0.0473 0.4291 1.0000
5.250 0.8906 0.01650 0.00738 -0.0469 0.4155 1.0000
5.500 0.9165 0.01674 0.00766 -0.0464 0.4032 1.0000
5.750 0.9422 0.01699 0.00795 -0.0460 0.3899 1.0000
6.000 0.9678 0.01727 0.00831 -0.0455 0.3769 1.0000
6.250 0.9933 0.01757 0.00871 -0.0451 0.3632 1.0000
6.500 1.0187 0.01791 0.00915 -0.0446 0.3490 1.0000
6.750 1.0437 0.01826 0.00963 -0.0441 0.3330 1.0000
7.000 1.0684 0.01865 0.01016 -0.0436 0.3123 1.0000
7.250 1.0922 0.01911 0.01069 -0.0431 0.2839 1.0000
7.500 1.1146 0.01976 0.01128 -0.0425 0.2342 1.0000
7.750 1.1330 0.02104 0.01215 -0.0418 0.1775 1.0000
8.000 1.1510 0.02245 0.01341 -0.0411 0.1479 1.0000
8.250 1.1700 0.02368 0.01463 -0.0404 0.1252 1.0000
8.500 1.1883 0.02494 0.01586 -0.0397 0.1059 1.0000
8.750 1.2064 0.02617 0.01712 -0.0390 0.0888 1.0000
9.000 1.2236 0.02748 0.01851 -0.0381 0.0711 1.0000
9.250 1.2387 0.02898 0.02004 -0.0372 0.0547 1.0000
9.500 1.2515 0.03066 0.02174 -0.0360 0.0452 1.0000
9.750 1.2619 0.03249 0.02362 -0.0347 0.0393 1.0000
10.000 1.2703 0.03439 0.02558 -0.0334 0.0351 1.0000
10.250 1.2759 0.03648 0.02778 -0.0319 0.0326 1.0000
10.500 1.2801 0.03850 0.02998 -0.0302 0.0308 1.0000
10.750 1.2824 0.04068 0.03229 -0.0287 0.0292 1.0000
11.000 1.2835 0.04312 0.03484 -0.0279 0.0277 1.0000
11.250 1.2823 0.04601 0.03780 -0.0275 0.0265 1.0000
11.500 1.2832 0.04890 0.04083 -0.0272 0.0254 1.0000
11.750 1.2855 0.05176 0.04396 -0.0270 0.0243 1.0000
12.000 1.2866 0.05485 0.04724 -0.0268 0.0236 1.0000
12.250 1.2865 0.05816 0.05074 -0.0268 0.0229 1.0000
12.500 1.2850 0.06170 0.05448 -0.0271 0.0224 1.0000
12.750 1.2818 0.06553 0.05850 -0.0276 0.0219 1.0000
13.000 1.2770 0.06965 0.06282 -0.0285 0.0215 1.0000
13.250 1.2704 0.07407 0.06743 -0.0297 0.0211 1.0000
13.500 1.2622 0.07882 0.07235 -0.0313 0.0207 1.0000
13.750 1.2526 0.08389 0.07759 -0.0333 0.0204 1.0000
14.000 1.2416 0.08932 0.08319 -0.0355 0.0202 1.0000
14.250 1.2291 0.09516 0.08921 -0.0382 0.0200 1.0000
14.500 1.2147 0.10158 0.09581 -0.0413 0.0199 1.0000
14.750 1.1983 0.10891 0.10334 -0.0453 0.0199 1.0000
15.000 1.1779 0.11770 0.11236 -0.0504 0.0200 1.0000
15.250 1.1442 0.13095 0.12592 -0.0586 0.0208 1.0000
15.500 1.0912 0.15210 0.14727 -0.0715 0.0225 1.0000
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Polar data table (+)
Polar graphs
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