GOE 599 AIRFOIL (goe599-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 599 AIRFOIL (goe599-il) Reynolds number: 500,000 Max Cl/Cd: 72.82 at α=2.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe599-il-500000.txt Download as CSV file: xf-goe599-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 599 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.000 -0.6751 0.06941 0.06701 -0.0408 1.0000 0.0153
-10.750 -0.6993 0.05910 0.05661 -0.0507 1.0000 0.0149
-10.500 -0.7230 0.05229 0.04966 -0.0571 1.0000 0.0146
-10.250 -0.7493 0.04856 0.04578 -0.0559 1.0000 0.0145
-10.000 -0.7724 0.04450 0.04149 -0.0532 1.0000 0.0144
-9.750 -0.7896 0.04036 0.03704 -0.0500 1.0000 0.0144
-9.500 -0.7992 0.03649 0.03281 -0.0468 1.0000 0.0146
-9.250 -0.8011 0.03311 0.02905 -0.0438 1.0000 0.0149
-9.000 -0.7967 0.03023 0.02579 -0.0411 1.0000 0.0152
-8.750 -0.7871 0.02792 0.02314 -0.0388 1.0000 0.0154
-8.500 -0.7754 0.02574 0.02062 -0.0368 1.0000 0.0157
-8.250 -0.7645 0.02247 0.01703 -0.0348 1.0000 0.0162
-8.000 -0.7465 0.02127 0.01573 -0.0335 1.0000 0.0167
-7.750 -0.7272 0.02041 0.01478 -0.0323 1.0000 0.0174
-7.500 -0.7073 0.01953 0.01379 -0.0311 1.0000 0.0181
-7.250 -0.6868 0.01879 0.01294 -0.0300 1.0000 0.0191
-7.000 -0.6656 0.01827 0.01230 -0.0289 1.0000 0.0201
-6.750 -0.6453 0.01701 0.01089 -0.0277 1.0000 0.0210
-6.500 -0.6204 0.01584 0.00968 -0.0277 0.9994 0.0223
-6.250 -0.5860 0.01522 0.00901 -0.0294 0.9976 0.0239
-6.000 -0.5508 0.01468 0.00840 -0.0312 0.9957 0.0259
-5.750 -0.5164 0.01381 0.00743 -0.0330 0.9943 0.0283
-5.500 -0.4835 0.01308 0.00669 -0.0344 0.9916 0.0311
-5.250 -0.4487 0.01262 0.00618 -0.0361 0.9889 0.0341
-5.000 -0.4137 0.01195 0.00545 -0.0379 0.9867 0.0383
-4.750 -0.3772 0.01148 0.00495 -0.0400 0.9848 0.0432
-4.500 -0.3399 0.01106 0.00449 -0.0422 0.9834 0.0493
-4.250 -0.3085 0.01060 0.00407 -0.0432 0.9787 0.0617
-4.000 -0.2737 0.01007 0.00379 -0.0449 0.9756 0.1135
-3.750 -0.2375 0.00962 0.00350 -0.0471 0.9734 0.1487
-3.500 -0.2007 0.00908 0.00329 -0.0494 0.9717 0.2319
-3.250 -0.1627 0.00868 0.00310 -0.0520 0.9704 0.2924
-3.000 -0.1329 0.00836 0.00293 -0.0525 0.9640 0.3355
-2.750 -0.0982 0.00797 0.00276 -0.0542 0.9606 0.3986
-2.500 -0.0633 0.00758 0.00261 -0.0558 0.9577 0.4649
-2.250 -0.0342 0.00725 0.00247 -0.0560 0.9496 0.5234
-2.000 -0.0020 0.00692 0.00228 -0.0568 0.9425 0.5767
-1.750 0.0245 0.00667 0.00214 -0.0562 0.9304 0.6152
-1.500 0.0520 0.00648 0.00204 -0.0560 0.9202 0.6472
-1.250 0.0802 0.00630 0.00195 -0.0559 0.9111 0.6810
-1.000 0.1076 0.00613 0.00188 -0.0556 0.9005 0.7162
-0.750 0.1342 0.00597 0.00183 -0.0551 0.8887 0.7549
-0.500 0.1604 0.00583 0.00176 -0.0543 0.8736 0.7929
-0.250 0.1859 0.00574 0.00172 -0.0534 0.8566 0.8316
0.000 0.2107 0.00570 0.00173 -0.0523 0.8414 0.8701
0.250 0.2356 0.00571 0.00175 -0.0512 0.8260 0.9074
0.500 0.2629 0.00576 0.00179 -0.0507 0.8088 0.9392
0.750 0.2956 0.00584 0.00181 -0.0515 0.7919 0.9612
1.000 0.3318 0.00592 0.00184 -0.0532 0.7755 0.9778
1.250 0.3712 0.00603 0.00187 -0.0556 0.7532 0.9899
1.500 0.4152 0.00612 0.00191 -0.0591 0.7285 0.9990
1.750 0.4415 0.00622 0.00190 -0.0588 0.6991 1.0000
2.000 0.4643 0.00638 0.00191 -0.0577 0.6578 1.0000
2.250 0.4857 0.00667 0.00194 -0.0564 0.5992 1.0000
2.500 0.5058 0.00711 0.00204 -0.0549 0.5242 1.0000
2.750 0.5247 0.00772 0.00222 -0.0533 0.4308 1.0000
3.000 0.5447 0.00833 0.00245 -0.0519 0.3467 1.0000
3.250 0.5589 0.00967 0.00290 -0.0499 0.1563 1.0000
3.500 0.5797 0.01041 0.00327 -0.0487 0.0816 1.0000
3.750 0.6041 0.01075 0.00355 -0.0481 0.0722 1.0000
4.000 0.6293 0.01101 0.00385 -0.0476 0.0695 1.0000
4.250 0.6542 0.01132 0.00417 -0.0471 0.0665 1.0000
4.500 0.6787 0.01169 0.00454 -0.0465 0.0638 1.0000
4.750 0.7024 0.01215 0.00502 -0.0457 0.0613 1.0000
5.000 0.7248 0.01277 0.00571 -0.0447 0.0592 1.0000
5.250 0.7495 0.01313 0.00610 -0.0442 0.0584 1.0000
5.500 0.7742 0.01345 0.00646 -0.0437 0.0563 1.0000
5.750 0.7986 0.01383 0.00686 -0.0431 0.0536 1.0000
6.000 0.8222 0.01429 0.00735 -0.0425 0.0511 1.0000
6.250 0.8428 0.01514 0.00821 -0.0413 0.0481 1.0000
6.500 0.8651 0.01584 0.00897 -0.0405 0.0461 1.0000
6.750 0.8908 0.01599 0.00917 -0.0402 0.0438 1.0000
7.000 0.9160 0.01619 0.00942 -0.0398 0.0407 1.0000
7.250 0.9389 0.01669 0.00989 -0.0392 0.0375 1.0000
7.500 0.9625 0.01711 0.01039 -0.0386 0.0344 1.0000
7.750 0.9895 0.01705 0.01034 -0.0385 0.0308 1.0000
8.000 1.0124 0.01750 0.01078 -0.0378 0.0274 1.0000
8.250 1.0376 0.01768 0.01101 -0.0375 0.0246 1.0000
8.500 1.0600 0.01817 0.01146 -0.0367 0.0222 1.0000
8.750 1.0797 0.01900 0.01239 -0.0354 0.0206 1.0000
9.000 1.1010 0.01960 0.01306 -0.0344 0.0191 1.0000
9.250 1.1223 0.02014 0.01364 -0.0335 0.0178 1.0000
9.500 1.1365 0.02156 0.01513 -0.0316 0.0165 1.0000
9.750 1.1558 0.02237 0.01607 -0.0303 0.0158 1.0000
10.000 1.1733 0.02337 0.01719 -0.0289 0.0151 1.0000
10.250 1.1901 0.02438 0.01832 -0.0274 0.0144 1.0000
10.500 1.2061 0.02540 0.01942 -0.0258 0.0138 1.0000
10.750 1.2199 0.02659 0.02071 -0.0240 0.0133 1.0000
11.000 1.2278 0.02852 0.02282 -0.0215 0.0128 1.0000
11.250 1.2293 0.03141 0.02600 -0.0182 0.0125 1.0000
11.500 1.2363 0.03291 0.02771 -0.0156 0.0123 1.0000
11.750 1.2408 0.03463 0.02965 -0.0129 0.0121 1.0000
12.000 1.2429 0.03654 0.03178 -0.0102 0.0118 1.0000
12.250 1.2425 0.03867 0.03413 -0.0077 0.0115 1.0000
12.500 1.2391 0.04111 0.03679 -0.0053 0.0112 1.0000
12.750 1.2347 0.04370 0.03957 -0.0034 0.0110 1.0000
13.000 1.2270 0.04679 0.04287 -0.0019 0.0109 1.0000
13.250 1.2165 0.05042 0.04670 -0.0011 0.0107 1.0000
13.500 1.2016 0.05487 0.05138 -0.0010 0.0107 1.0000
13.750 1.1820 0.06042 0.05717 -0.0021 0.0106 1.0000
14.000 1.1574 0.06733 0.06433 -0.0048 0.0107 1.0000
14.250 1.1196 0.07762 0.07492 -0.0103 0.0108 1.0000
14.500 1.0708 0.09212 0.08973 -0.0196 0.0112 1.0000
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