GOE 617 AIRFOIL (goe617-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 617 AIRFOIL (goe617-il) Reynolds number: 100,000 Max Cl/Cd: 48.8 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe617-il-100000-n5.txt Download as CSV file: xf-goe617-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 617 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
------ -------- --------- --------- -------- -------- --------
-11.750 -0.5072 0.09077 0.08521 -0.0503 1.0000 0.0506
-11.500 -0.6103 0.06664 0.06101 -0.0668 1.0000 0.0491
-11.250 -0.6853 0.05755 0.05161 -0.0680 1.0000 0.0479
-11.000 -0.7140 0.05456 0.04848 -0.0643 1.0000 0.0480
-10.750 -0.7380 0.05252 0.04634 -0.0591 1.0000 0.0483
-10.500 -0.7547 0.05083 0.04455 -0.0541 1.0000 0.0488
-10.250 -0.7710 0.04878 0.04235 -0.0491 1.0000 0.0494
-10.000 -0.7850 0.04684 0.04021 -0.0441 1.0000 0.0500
-9.750 -0.7976 0.04483 0.03797 -0.0390 1.0000 0.0507
-9.500 -0.8079 0.04277 0.03563 -0.0340 1.0000 0.0514
-9.250 -0.8155 0.04075 0.03327 -0.0292 1.0000 0.0524
-9.000 -0.8223 0.03872 0.03078 -0.0243 1.0000 0.0537
-8.750 -0.8138 0.03758 0.02960 -0.0218 0.9996 0.0546
-8.500 -0.7847 0.03634 0.02826 -0.0232 0.9946 0.0564
-8.250 -0.7585 0.03470 0.02637 -0.0240 0.9890 0.0581
-8.000 -0.7302 0.03307 0.02439 -0.0249 0.9839 0.0605
-7.750 -0.7048 0.03156 0.02245 -0.0251 0.9775 0.0629
-7.500 -0.6734 0.03030 0.02120 -0.0266 0.9729 0.0649
-7.250 -0.6453 0.02920 0.01996 -0.0271 0.9669 0.0671
-7.000 -0.6145 0.02809 0.01867 -0.0281 0.9615 0.0699
-6.750 -0.5828 0.02718 0.01744 -0.0290 0.9563 0.0733
-6.500 -0.5547 0.02605 0.01641 -0.0296 0.9498 0.0764
-6.250 -0.5204 0.02512 0.01543 -0.0311 0.9453 0.0801
-6.000 -0.4917 0.02433 0.01450 -0.0314 0.9388 0.0841
-5.750 -0.4613 0.02344 0.01363 -0.0322 0.9328 0.0887
-5.500 -0.4257 0.02267 0.01285 -0.0340 0.9287 0.0946
-5.250 -0.4009 0.02206 0.01218 -0.0335 0.9205 0.0997
-5.000 -0.3687 0.02137 0.01155 -0.0346 0.9151 0.1066
-4.750 -0.3331 0.02074 0.01091 -0.0362 0.9108 0.1150
-4.500 -0.3099 0.02029 0.01049 -0.0354 0.9015 0.1236
-4.250 -0.2756 0.01972 0.00997 -0.0367 0.8964 0.1362
-4.000 -0.2515 0.01929 0.00961 -0.0360 0.8874 0.1501
-3.750 -0.2198 0.01876 0.00917 -0.0368 0.8810 0.1750
-3.500 -0.1938 0.01828 0.00877 -0.0364 0.8725 0.2068
-3.250 -0.1660 0.01765 0.00834 -0.0364 0.8648 0.2483
-3.000 -0.1434 0.01693 0.00808 -0.0355 0.8559 0.3308
-2.750 -0.1180 0.01630 0.00783 -0.0350 0.8476 0.4370
-2.500 -0.0947 0.01583 0.00769 -0.0338 0.8380 0.5192
-2.250 -0.0631 0.01535 0.00755 -0.0340 0.8303 0.6103
-2.000 -0.0173 0.01509 0.00773 -0.0366 0.8225 0.7233
-1.750 0.0454 0.01522 0.00798 -0.0423 0.8155 0.8008
-1.500 0.0880 0.01538 0.00810 -0.0443 0.8059 0.8403
-1.250 0.1326 0.01555 0.00816 -0.0466 0.7960 0.8694
-1.000 0.1682 0.01576 0.00828 -0.0475 0.7833 0.8914
-0.750 0.2111 0.01593 0.00833 -0.0498 0.7711 0.9063
-0.500 0.2539 0.01601 0.00829 -0.0523 0.7592 0.9177
-0.250 0.2914 0.01608 0.00825 -0.0539 0.7460 0.9297
0.000 0.3290 0.01618 0.00826 -0.0556 0.7323 0.9415
0.250 0.3726 0.01620 0.00819 -0.0586 0.7186 0.9502
0.500 0.4095 0.01623 0.00812 -0.0603 0.7053 0.9597
0.750 0.4481 0.01620 0.00800 -0.0625 0.6924 0.9667
1.000 0.4850 0.01618 0.00788 -0.0644 0.6797 0.9737
1.250 0.5232 0.01617 0.00781 -0.0666 0.6661 0.9815
1.500 0.5651 0.01610 0.00768 -0.0697 0.6526 0.9889
1.750 0.6062 0.01603 0.00754 -0.0726 0.6394 0.9963
2.000 0.6379 0.01602 0.00746 -0.0735 0.6260 1.0000
2.250 0.6579 0.01610 0.00745 -0.0721 0.6133 1.0000
2.750 0.6957 0.01633 0.00761 -0.0689 0.5861 1.0000
3.000 0.7150 0.01645 0.00770 -0.0673 0.5733 1.0000
3.250 0.7344 0.01659 0.00778 -0.0657 0.5612 1.0000
3.500 0.7533 0.01674 0.00792 -0.0640 0.5489 1.0000
3.750 0.7718 0.01690 0.00808 -0.0623 0.5365 1.0000
4.000 0.7903 0.01707 0.00823 -0.0606 0.5237 1.0000
4.250 0.8085 0.01725 0.00837 -0.0587 0.5108 1.0000
4.500 0.8262 0.01743 0.00855 -0.0568 0.4977 1.0000
4.750 0.8434 0.01763 0.00876 -0.0548 0.4842 1.0000
5.000 0.8604 0.01784 0.00899 -0.0528 0.4709 1.0000
5.250 0.8764 0.01807 0.00920 -0.0506 0.4561 1.0000
5.500 0.8914 0.01830 0.00942 -0.0482 0.4397 1.0000
5.750 0.9057 0.01856 0.00966 -0.0457 0.4226 1.0000
6.000 0.9193 0.01884 0.00992 -0.0430 0.4051 1.0000
6.250 0.9327 0.01915 0.01021 -0.0404 0.3884 1.0000
6.500 0.9452 0.01949 0.01051 -0.0376 0.3709 1.0000
6.750 0.9568 0.01986 0.01085 -0.0346 0.3530 1.0000
7.000 0.9669 0.02028 0.01122 -0.0315 0.3341 1.0000
7.250 0.9765 0.02072 0.01164 -0.0283 0.3136 1.0000
7.500 0.9846 0.02122 0.01209 -0.0248 0.2921 1.0000
7.750 0.9907 0.02179 0.01257 -0.0211 0.2702 1.0000
8.000 0.9961 0.02239 0.01310 -0.0174 0.2469 1.0000
8.250 0.9981 0.02306 0.01366 -0.0131 0.2269 1.0000
8.500 0.9984 0.02374 0.01425 -0.0086 0.2112 1.0000
8.750 0.9998 0.02448 0.01491 -0.0044 0.1983 1.0000
9.000 1.0029 0.02526 0.01565 -0.0007 0.1880 1.0000
9.250 1.0054 0.02616 0.01648 0.0029 0.1793 1.0000
9.500 1.0105 0.02704 0.01737 0.0059 0.1711 1.0000
9.750 1.0140 0.02807 0.01835 0.0090 0.1643 1.0000
10.000 1.0215 0.02899 0.01935 0.0115 0.1572 1.0000
10.250 1.0264 0.03009 0.02041 0.0141 0.1515 1.0000
10.500 1.0348 0.03110 0.02147 0.0162 0.1462 1.0000
10.750 1.0436 0.03212 0.02257 0.0182 0.1410 1.0000
11.000 1.0510 0.03326 0.02371 0.0201 0.1365 1.0000
11.250 1.0606 0.03437 0.02486 0.0218 0.1326 1.0000
11.500 1.0703 0.03547 0.02608 0.0234 0.1281 1.0000
11.750 1.0794 0.03662 0.02729 0.0250 0.1243 1.0000
12.000 1.0887 0.03783 0.02849 0.0264 0.1212 1.0000
12.250 1.0997 0.03902 0.02977 0.0277 0.1182 1.0000
12.500 1.1104 0.04026 0.03116 0.0289 0.1152 1.0000
12.750 1.1204 0.04154 0.03254 0.0301 0.1125 1.0000
13.000 1.1296 0.04285 0.03391 0.0313 0.1099 1.0000
13.250 1.1398 0.04416 0.03522 0.0323 0.1075 1.0000
13.500 1.1478 0.04570 0.03691 0.0333 0.1051 1.0000
13.750 1.1535 0.04740 0.03881 0.0343 0.1025 1.0000
14.000 1.1581 0.04914 0.04068 0.0352 0.0999 1.0000
14.250 1.1617 0.05089 0.04250 0.0360 0.0973 1.0000
14.500 1.1668 0.05254 0.04410 0.0366 0.0945 1.0000
14.750 1.1626 0.05518 0.04701 0.0371 0.0917 1.0000
15.000 1.1581 0.05786 0.04987 0.0373 0.0885 1.0000
15.250 1.1565 0.06035 0.05245 0.0373 0.0859 1.0000
15.500 1.1563 0.06271 0.05481 0.0372 0.0833 1.0000
15.750 1.1512 0.06591 0.05820 0.0369 0.0808 1.0000
16.000 1.1430 0.06965 0.06218 0.0361 0.0782 1.0000
16.250 1.1370 0.07323 0.06592 0.0352 0.0759 1.0000
16.500 1.1327 0.07664 0.06943 0.0344 0.0739 1.0000
16.750 1.1306 0.07974 0.07254 0.0335 0.0718 1.0000
17.000 1.1199 0.08442 0.07742 0.0319 0.0700 1.0000
17.250 1.1031 0.09026 0.08353 0.0295 0.0681 1.0000
17.500 1.0877 0.09606 0.08954 0.0270 0.0665 1.0000
17.750 1.0717 0.10215 0.09579 0.0242 0.0646 1.0000
18.000 1.0600 0.10762 0.10136 0.0216 0.0629 1.0000
18.250 1.0542 0.11201 0.10575 0.0194 0.0607 1.0000
18.500 1.0190 0.12254 0.11655 0.0139 0.0600 1.0000
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