GOE 703 AIRFOIL (goe703-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 703 AIRFOIL (goe703-il) Reynolds number: 100,000 Max Cl/Cd: 43.02 at α=7.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe703-il-100000-n5.txt Download as CSV file: xf-goe703-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 703 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
------ -------- --------- --------- -------- -------- --------
-15.250 -0.7311 0.07282 0.06538 -0.0846 1.0000 0.0536
-15.000 -0.7553 0.06769 0.06006 -0.0858 1.0000 0.0536
-14.750 -0.7717 0.06382 0.05603 -0.0860 1.0000 0.0538
-14.500 -0.7826 0.06072 0.05281 -0.0855 1.0000 0.0541
-14.250 -0.7930 0.05786 0.04982 -0.0845 1.0000 0.0542
-14.000 -0.7998 0.05551 0.04738 -0.0832 1.0000 0.0546
-13.750 -0.8063 0.05330 0.04507 -0.0815 1.0000 0.0550
-13.500 -0.8121 0.05131 0.04299 -0.0794 1.0000 0.0555
-13.250 -0.8175 0.04945 0.04101 -0.0771 1.0000 0.0560
-13.000 -0.8220 0.04773 0.03917 -0.0745 1.0000 0.0565
-12.750 -0.8270 0.04613 0.03745 -0.0716 1.0000 0.0571
-12.500 -0.8307 0.04469 0.03588 -0.0684 1.0000 0.0577
-12.250 -0.8347 0.04337 0.03443 -0.0650 1.0000 0.0583
-12.000 -0.8390 0.04219 0.03311 -0.0612 1.0000 0.0589
-11.750 -0.8434 0.04122 0.03202 -0.0572 1.0000 0.0593
-11.500 -0.8449 0.04044 0.03129 -0.0534 1.0000 0.0598
-11.250 -0.8217 0.03915 0.03001 -0.0542 0.9957 0.0607
-11.000 -0.7942 0.03778 0.02859 -0.0557 0.9886 0.0618
-10.750 -0.7667 0.03647 0.02720 -0.0572 0.9816 0.0632
-10.500 -0.7410 0.03523 0.02582 -0.0581 0.9733 0.0647
-10.250 -0.7126 0.03403 0.02456 -0.0595 0.9665 0.0665
-10.000 -0.6901 0.03297 0.02352 -0.0597 0.9565 0.0682
-9.750 -0.6632 0.03190 0.02239 -0.0607 0.9489 0.0706
-9.500 -0.6373 0.03087 0.02128 -0.0612 0.9400 0.0732
-9.250 -0.6104 0.02982 0.02025 -0.0621 0.9325 0.0758
-9.000 -0.5838 0.02886 0.01923 -0.0627 0.9234 0.0790
-8.750 -0.5505 0.02779 0.01816 -0.0647 0.9177 0.0834
-8.500 -0.5248 0.02698 0.01731 -0.0650 0.9069 0.0890
-8.250 -0.4916 0.02601 0.01636 -0.0669 0.8998 0.0964
-8.000 -0.4667 0.02526 0.01564 -0.0670 0.8885 0.1052
-7.750 -0.4332 0.02444 0.01482 -0.0687 0.8804 0.1186
-7.500 -0.4084 0.02385 0.01426 -0.0686 0.8687 0.1328
-7.250 -0.3767 0.02319 0.01363 -0.0699 0.8593 0.1498
-7.000 -0.3546 0.02277 0.01321 -0.0691 0.8468 0.1646
-6.750 -0.3246 0.02228 0.01270 -0.0699 0.8374 0.1816
-6.500 -0.3051 0.02197 0.01238 -0.0686 0.8248 0.1954
-6.250 -0.2764 0.02156 0.01193 -0.0690 0.8156 0.2118
-6.000 -0.2591 0.02133 0.01168 -0.0671 0.8028 0.2257
-5.500 -0.2173 0.02070 0.01110 -0.0648 0.7819 0.2578
-5.250 -0.1928 0.02034 0.01075 -0.0643 0.7735 0.2777
-5.000 -0.1764 0.02009 0.01057 -0.0622 0.7622 0.2955
-4.750 -0.1510 0.01973 0.01022 -0.0618 0.7541 0.3153
-4.500 -0.1328 0.01948 0.01004 -0.0600 0.7439 0.3347
-4.250 -0.1098 0.01912 0.00977 -0.0591 0.7360 0.3596
-4.000 -0.0912 0.01881 0.00960 -0.0574 0.7274 0.3918
-3.750 -0.0727 0.01843 0.00946 -0.0556 0.7191 0.4391
-3.500 -0.0482 0.01804 0.00938 -0.0548 0.7122 0.5123
-3.250 -0.0022 0.01813 0.00992 -0.0575 0.7041 0.6068
-3.000 0.0601 0.01881 0.01075 -0.0625 0.6972 0.6744
-2.750 0.1005 0.01938 0.01128 -0.0639 0.6900 0.7077
-2.500 0.1221 0.01965 0.01150 -0.0621 0.6822 0.7339
-2.250 0.1494 0.01995 0.01168 -0.0614 0.6760 0.7541
-2.000 0.1696 0.02025 0.01191 -0.0595 0.6690 0.7723
-1.750 0.2024 0.02076 0.01235 -0.0597 0.6617 0.7842
-1.500 0.2307 0.02109 0.01254 -0.0592 0.6558 0.7970
-1.250 0.2494 0.02137 0.01277 -0.0571 0.6491 0.8114
-1.000 0.2858 0.02182 0.01314 -0.0582 0.6419 0.8197
-0.750 0.3120 0.02209 0.01329 -0.0575 0.6361 0.8316
-0.500 0.3429 0.02251 0.01365 -0.0577 0.6296 0.8429
-0.250 0.3775 0.02292 0.01402 -0.0585 0.6224 0.8525
0.250 0.4465 0.02354 0.01447 -0.0604 0.6104 0.8716
0.500 0.4646 0.02382 0.01476 -0.0585 0.6037 0.8835
0.750 0.5063 0.02394 0.01480 -0.0611 0.5973 0.8880
1.000 0.5380 0.02401 0.01477 -0.0619 0.5921 0.8936
1.250 0.5512 0.02418 0.01498 -0.0593 0.5853 0.9016
1.500 0.5851 0.02421 0.01498 -0.0606 0.5790 0.9050
1.750 0.6166 0.02422 0.01490 -0.0615 0.5737 0.9093
2.000 0.6310 0.02441 0.01512 -0.0591 0.5676 0.9167
2.250 0.6590 0.02446 0.01518 -0.0594 0.5610 0.9206
2.500 0.6911 0.02445 0.01512 -0.0604 0.5553 0.9241
2.750 0.7164 0.02454 0.01519 -0.0602 0.5495 0.9289
3.000 0.7298 0.02476 0.01546 -0.0577 0.5430 0.9353
3.250 0.7619 0.02472 0.01540 -0.0588 0.5369 0.9381
3.500 0.7925 0.02472 0.01534 -0.0595 0.5316 0.9415
3.750 0.8114 0.02492 0.01564 -0.0582 0.5245 0.9466
4.000 0.8293 0.02507 0.01579 -0.0566 0.5185 0.9515
4.250 0.8626 0.02499 0.01565 -0.0578 0.5134 0.9539
4.500 0.8845 0.02517 0.01594 -0.0572 0.5058 0.9579
4.750 0.9066 0.02527 0.01606 -0.0564 0.4994 0.9618
5.000 0.9286 0.02534 0.01606 -0.0555 0.4939 0.9659
5.250 0.9512 0.02547 0.01631 -0.0550 0.4849 0.9692
5.500 0.9768 0.02540 0.01620 -0.0548 0.4770 0.9721
5.750 0.9942 0.02556 0.01644 -0.0533 0.4674 0.9764
6.000 1.0143 0.02559 0.01641 -0.0520 0.4584 0.9802
6.250 1.0344 0.02566 0.01655 -0.0511 0.4475 0.9832
6.500 1.0578 0.02564 0.01648 -0.0506 0.4390 0.9862
6.750 1.0751 0.02591 0.01685 -0.0493 0.4297 0.9902
7.000 1.0969 0.02602 0.01696 -0.0486 0.4224 0.9931
7.250 1.1157 0.02624 0.01724 -0.0476 0.4141 0.9961
7.500 1.1362 0.02641 0.01745 -0.0468 0.4060 0.9991
7.750 1.1464 0.02671 0.01777 -0.0440 0.3990 1.0000
8.000 1.1467 0.02711 0.01823 -0.0395 0.3919 1.0000
8.250 1.1485 0.02739 0.01848 -0.0350 0.3858 1.0000
8.500 1.1417 0.02783 0.01899 -0.0293 0.3795 1.0000
8.750 1.1363 0.02828 0.01948 -0.0239 0.3729 1.0000
9.000 1.1379 0.02862 0.01977 -0.0197 0.3669 1.0000
9.250 1.1285 0.02933 0.02058 -0.0141 0.3599 1.0000
9.500 1.1253 0.02990 0.02117 -0.0096 0.3531 1.0000
9.750 1.1227 0.03054 0.02181 -0.0052 0.3463 1.0000
10.000 1.1150 0.03142 0.02275 -0.0005 0.3388 1.0000
10.250 1.1161 0.03201 0.02329 0.0031 0.3319 1.0000
10.500 1.1058 0.03319 0.02457 0.0076 0.3240 1.0000
10.750 1.1028 0.03408 0.02542 0.0113 0.3163 1.0000
11.000 1.0951 0.03534 0.02674 0.0152 0.3081 1.0000
11.250 1.0902 0.03648 0.02786 0.0187 0.2996 1.0000
11.500 1.0829 0.03792 0.02933 0.0221 0.2912 1.0000
11.750 1.0773 0.03930 0.03070 0.0252 0.2823 1.0000
12.000 1.0696 0.04098 0.03243 0.0282 0.2735 1.0000
12.250 1.0647 0.04251 0.03392 0.0309 0.2647 1.0000
12.500 1.0575 0.04442 0.03589 0.0333 0.2562 1.0000
12.750 1.0546 0.04601 0.03744 0.0355 0.2483 1.0000
13.000 1.0483 0.04806 0.03954 0.0376 0.2402 1.0000
13.250 1.0458 0.04980 0.04124 0.0394 0.2326 1.0000
13.500 1.0425 0.05178 0.04327 0.0410 0.2256 1.0000
13.750 1.0404 0.05370 0.04519 0.0425 0.2190 1.0000
14.000 1.0393 0.05556 0.04703 0.0439 0.2126 1.0000
14.250 1.0360 0.05779 0.04930 0.0451 0.2063 1.0000
14.500 1.0372 0.05950 0.05094 0.0463 0.2005 1.0000
14.750 1.0342 0.06187 0.05339 0.0473 0.1950 1.0000
15.000 1.0327 0.06407 0.05562 0.0481 0.1896 1.0000
15.250 1.0371 0.06558 0.05705 0.0491 0.1851 1.0000
15.500 1.0318 0.06842 0.06002 0.0496 0.1799 1.0000
15.750 1.0312 0.07070 0.06232 0.0502 0.1753 1.0000
16.000 1.0365 0.07220 0.06375 0.0509 0.1710 1.0000
16.250 1.0313 0.07524 0.06692 0.0512 0.1667 1.0000
16.500 1.0289 0.07792 0.06968 0.0514 0.1625 1.0000
16.750 1.0344 0.07953 0.07125 0.0519 0.1587 1.0000
17.000 1.0309 0.08248 0.07428 0.0519 0.1547 1.0000
17.250 1.0250 0.08580 0.07772 0.0517 0.1505 1.0000
17.500 1.0267 0.08803 0.07994 0.0518 0.1465 1.0000
17.750 1.0265 0.09060 0.08254 0.0518 0.1428 1.0000
18.000 1.0148 0.09495 0.08704 0.0510 0.1383 1.0000
18.250 1.0141 0.09764 0.08977 0.0507 0.1343 1.0000
18.500 1.0134 0.10038 0.09252 0.0504 0.1303 1.0000
18.750 0.9980 0.10551 0.09782 0.0491 0.1258 1.0000
19.000 0.9979 0.10822 0.10053 0.0486 0.1217 1.0000
19.250 0.9917 0.11198 0.10436 0.0476 0.1177 1.0000
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