GOE 617 AIRFOIL (goe617-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 617 AIRFOIL (goe617-il) Reynolds number: 200,000 Max Cl/Cd: 67.18 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe617-il-200000.txt Download as CSV file: xf-goe617-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.500 -0.6678 0.06328 0.05899 -0.0697 1.0000 0.0525
-11.250 -0.6951 0.05982 0.05543 -0.0671 1.0000 0.0524
-11.000 -0.7177 0.05693 0.05247 -0.0632 1.0000 0.0522
-10.750 -0.7458 0.05480 0.05026 -0.0570 1.0000 0.0521
-10.500 -0.7710 0.05229 0.04762 -0.0512 1.0000 0.0521
-10.250 -0.7988 0.05006 0.04518 -0.0444 1.0000 0.0522
-10.000 -0.8222 0.04793 0.04282 -0.0378 1.0000 0.0524
-9.750 -0.8402 0.04575 0.04039 -0.0317 1.0000 0.0525
-9.250 -0.8622 0.04044 0.03460 -0.0217 1.0000 0.0531
-9.000 -0.8590 0.03866 0.03276 -0.0186 1.0000 0.0539
-8.750 -0.8453 0.03834 0.03257 -0.0167 1.0000 0.0551
-8.500 -0.8322 0.03696 0.03105 -0.0152 0.9986 0.0564
-8.250 -0.8059 0.03460 0.02829 -0.0162 0.9939 0.0583
-8.000 -0.7816 0.03229 0.02554 -0.0165 0.9885 0.0598
-7.750 -0.7523 0.03071 0.02345 -0.0174 0.9835 0.0615
-7.500 -0.7235 0.02859 0.02130 -0.0186 0.9792 0.0637
-7.250 -0.6917 0.02749 0.02012 -0.0198 0.9741 0.0657
-7.000 -0.6553 0.02633 0.01877 -0.0218 0.9705 0.0684
-6.750 -0.6269 0.02558 0.01775 -0.0220 0.9642 0.0709
-6.500 -0.5932 0.02386 0.01591 -0.0235 0.9599 0.0736
-6.250 -0.5540 0.02284 0.01490 -0.0260 0.9568 0.0771
-6.000 -0.5236 0.02213 0.01409 -0.0266 0.9507 0.0809
-5.750 -0.4890 0.02107 0.01292 -0.0280 0.9457 0.0851
-5.500 -0.4492 0.02004 0.01198 -0.0306 0.9424 0.0907
-5.250 -0.4065 0.01921 0.01108 -0.0335 0.9401 0.0975
-5.000 -0.3838 0.01846 0.01043 -0.0327 0.9310 0.1038
-4.750 -0.3441 0.01771 0.00967 -0.0350 0.9275 0.1120
-4.500 -0.3009 0.01699 0.00901 -0.0382 0.9251 0.1224
-4.250 -0.2761 0.01648 0.00858 -0.0375 0.9163 0.1317
-4.000 -0.2365 0.01586 0.00804 -0.0399 0.9121 0.1458
-3.750 -0.1948 0.01523 0.00751 -0.0426 0.9090 0.1700
-3.500 -0.1739 0.01465 0.00715 -0.0411 0.8989 0.2075
-3.250 -0.1462 0.01349 0.00655 -0.0413 0.8932 0.3073
-3.000 -0.1337 0.01272 0.00637 -0.0382 0.8821 0.4468
-2.750 -0.1088 0.01195 0.00606 -0.0371 0.8756 0.5616
-2.500 -0.0916 0.01151 0.00599 -0.0344 0.8642 0.6501
-2.250 -0.0491 0.01108 0.00592 -0.0363 0.8586 0.7505
-2.000 -0.0028 0.01112 0.00609 -0.0391 0.8491 0.8162
-1.750 0.0467 0.01121 0.00612 -0.0425 0.8417 0.8531
-1.500 0.0834 0.01142 0.00627 -0.0433 0.8294 0.8769
-1.250 0.1306 0.01172 0.00647 -0.0462 0.8191 0.8941
-1.000 0.1712 0.01195 0.00659 -0.0479 0.8083 0.9077
-0.750 0.2274 0.01231 0.00686 -0.0529 0.7959 0.9149
-0.500 0.2716 0.01259 0.00704 -0.0555 0.7832 0.9267
-0.250 0.3173 0.01282 0.00715 -0.0585 0.7706 0.9375
0.000 0.3670 0.01292 0.00714 -0.0626 0.7575 0.9448
0.250 0.4021 0.01303 0.00716 -0.0638 0.7428 0.9552
0.500 0.4509 0.01299 0.00704 -0.0680 0.7280 0.9614
0.750 0.4896 0.01301 0.00697 -0.0702 0.7130 0.9704
1.000 0.5356 0.01290 0.00676 -0.0739 0.6970 0.9781
1.250 0.5770 0.01277 0.00653 -0.0767 0.6800 0.9854
1.500 0.6157 0.01266 0.00632 -0.0791 0.6644 0.9919
1.750 0.6557 0.01247 0.00606 -0.0818 0.6490 0.9975
2.000 0.6845 0.01243 0.00594 -0.0823 0.6349 1.0000
2.250 0.7037 0.01250 0.00594 -0.0808 0.6218 1.0000
2.500 0.7234 0.01260 0.00595 -0.0794 0.6093 1.0000
2.750 0.7422 0.01268 0.00601 -0.0777 0.5960 1.0000
3.000 0.7613 0.01278 0.00608 -0.0762 0.5833 1.0000
3.250 0.7807 0.01290 0.00616 -0.0746 0.5710 1.0000
3.500 0.8004 0.01303 0.00622 -0.0731 0.5590 1.0000
3.750 0.8187 0.01313 0.00630 -0.0713 0.5449 1.0000
4.000 0.8364 0.01323 0.00638 -0.0694 0.5295 1.0000
4.250 0.8543 0.01335 0.00648 -0.0675 0.5149 1.0000
4.500 0.8722 0.01348 0.00659 -0.0656 0.5006 1.0000
4.750 0.8902 0.01363 0.00671 -0.0637 0.4873 1.0000
5.000 0.9078 0.01378 0.00685 -0.0618 0.4737 1.0000
5.250 0.9252 0.01395 0.00698 -0.0598 0.4604 1.0000
5.500 0.9418 0.01412 0.00714 -0.0577 0.4458 1.0000
5.750 0.9580 0.01429 0.00732 -0.0555 0.4306 1.0000
6.000 0.9735 0.01449 0.00752 -0.0531 0.4149 1.0000
6.250 0.9882 0.01472 0.00772 -0.0506 0.3984 1.0000
6.500 1.0014 0.01498 0.00794 -0.0479 0.3805 1.0000
6.750 1.0138 0.01526 0.00820 -0.0450 0.3601 1.0000
7.000 1.0238 0.01561 0.00850 -0.0417 0.3367 1.0000
7.250 1.0319 0.01603 0.00883 -0.0381 0.3107 1.0000
7.500 1.0372 0.01654 0.00921 -0.0340 0.2816 1.0000
7.750 1.0404 0.01712 0.00964 -0.0296 0.2518 1.0000
8.000 1.0425 0.01776 0.01014 -0.0250 0.2267 1.0000
8.250 1.0427 0.01843 0.01067 -0.0202 0.2091 1.0000
8.500 1.0410 0.01905 0.01119 -0.0149 0.1958 1.0000
8.750 1.0413 0.01970 0.01179 -0.0102 0.1848 1.0000
9.000 1.0418 0.02048 0.01248 -0.0057 0.1755 1.0000
9.250 1.0458 0.02125 0.01321 -0.0019 0.1669 1.0000
9.500 1.0516 0.02210 0.01403 0.0014 0.1594 1.0000
9.750 1.0594 0.02289 0.01482 0.0043 0.1526 1.0000
10.000 1.0686 0.02386 0.01573 0.0069 0.1467 1.0000
10.250 1.0793 0.02457 0.01652 0.0092 0.1412 1.0000
10.500 1.0899 0.02541 0.01734 0.0114 0.1365 1.0000
10.750 1.1036 0.02637 0.01828 0.0131 0.1320 1.0000
11.000 1.1155 0.02713 0.01915 0.0151 0.1282 1.0000
11.250 1.1279 0.02794 0.02001 0.0169 0.1247 1.0000
11.500 1.1412 0.02887 0.02089 0.0184 0.1211 1.0000
11.750 1.1542 0.02983 0.02192 0.0200 0.1177 1.0000
12.000 1.1621 0.03069 0.02292 0.0220 0.1142 1.0000
12.250 1.1700 0.03158 0.02385 0.0239 0.1106 1.0000
12.500 1.1831 0.03262 0.02482 0.0251 0.1071 1.0000
12.750 1.1902 0.03372 0.02607 0.0269 0.1043 1.0000
13.000 1.1963 0.03483 0.02731 0.0285 0.1012 1.0000
13.250 1.2030 0.03595 0.02850 0.0300 0.0983 1.0000
13.500 1.2121 0.03714 0.02965 0.0312 0.0953 1.0000
13.750 1.2213 0.03849 0.03110 0.0324 0.0928 1.0000
14.000 1.2246 0.03998 0.03277 0.0337 0.0902 1.0000
14.250 1.2290 0.04147 0.03436 0.0348 0.0875 1.0000
14.500 1.2336 0.04298 0.03589 0.0357 0.0849 1.0000
14.750 1.2427 0.04450 0.03740 0.0365 0.0818 1.0000
15.000 1.2414 0.04658 0.03970 0.0373 0.0797 1.0000
15.250 1.2403 0.04873 0.04199 0.0378 0.0768 1.0000
15.500 1.2415 0.05077 0.04408 0.0381 0.0741 1.0000
15.750 1.2439 0.05287 0.04618 0.0386 0.0709 1.0000
16.000 1.2381 0.05588 0.04942 0.0384 0.0683 1.0000
16.250 1.2341 0.05880 0.05245 0.0379 0.0651 1.0000
16.500 1.2335 0.06137 0.05493 0.0378 0.0616 1.0000
16.750 1.2226 0.06556 0.05942 0.0366 0.0585 1.0000
17.000 1.2170 0.06914 0.06308 0.0355 0.0555 1.0000
17.250 1.2114 0.07273 0.06665 0.0347 0.0525 1.0000
17.500 1.2012 0.07727 0.07141 0.0331 0.0497 1.0000
17.750 1.1946 0.08137 0.07556 0.0316 0.0473 1.0000
18.000 1.1916 0.08474 0.07888 0.0308 0.0453 1.0000
18.250 1.1786 0.09009 0.08448 0.0287 0.0434 1.0000
18.500 1.1706 0.09466 0.08918 0.0269 0.0418 1.0000
18.750 1.1643 0.09902 0.09359 0.0251 0.0403 1.0000
19.000 1.1618 0.10251 0.09702 0.0239 0.0387 1.0000
19.250 1.1501 0.10798 0.10270 0.0215 0.0380 1.0000
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Polar data table (+)
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