GOE 496 AIRFOIL (goe496-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 496 AIRFOIL (goe496-il) Reynolds number: 200,000 Max Cl/Cd: 87.3 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe496-il-200000-n5.txt Download as CSV file: xf-goe496-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 496 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.3456 0.10030 0.09664 -0.0406 1.0000 0.0285
-9.500 -0.3554 0.09640 0.09279 -0.0407 1.0000 0.0293
-9.250 -0.3756 0.09108 0.08755 -0.0413 1.0000 0.0302
-9.000 -0.3627 0.08731 0.08378 -0.0454 0.9968 0.0311
-8.750 -0.3448 0.08454 0.08100 -0.0489 0.9931 0.0318
-8.500 -0.3319 0.08034 0.07680 -0.0537 0.9878 0.0325
-8.000 -0.3457 0.03600 0.03177 -0.1139 0.9560 0.0354
-7.750 -0.3178 0.02943 0.02434 -0.1227 0.9491 0.0366
-7.500 -0.2854 0.02676 0.02112 -0.1265 0.9446 0.0378
-7.250 -0.2517 0.02417 0.01821 -0.1299 0.9420 0.0391
-7.000 -0.2252 0.02276 0.01663 -0.1307 0.9349 0.0399
-6.750 -0.1916 0.02143 0.01509 -0.1327 0.9309 0.0408
-6.500 -0.1606 0.02027 0.01372 -0.1339 0.9255 0.0418
-6.250 -0.1302 0.01931 0.01258 -0.1348 0.9192 0.0431
-6.000 -0.0956 0.01836 0.01144 -0.1365 0.9153 0.0447
-5.750 -0.0679 0.01756 0.01047 -0.1367 0.9073 0.0457
-5.500 -0.0348 0.01676 0.00949 -0.1378 0.9021 0.0465
-5.250 -0.0046 0.01611 0.00871 -0.1384 0.8952 0.0473
-5.000 0.0265 0.01534 0.00785 -0.1391 0.8886 0.0484
-4.750 0.0585 0.01461 0.00706 -0.1401 0.8826 0.0501
-4.500 0.0880 0.01412 0.00651 -0.1405 0.8744 0.0524
-4.250 0.1208 0.01365 0.00596 -0.1415 0.8684 0.0550
-4.000 0.1493 0.01329 0.00551 -0.1415 0.8594 0.0573
-3.500 0.2096 0.01257 0.00469 -0.1423 0.8435 0.0650
-3.250 0.2405 0.01228 0.00440 -0.1428 0.8362 0.0736
-3.000 0.2686 0.01211 0.00425 -0.1427 0.8270 0.0949
-2.750 0.2983 0.01198 0.00407 -0.1429 0.8192 0.1129
-2.500 0.3264 0.01187 0.00393 -0.1428 0.8100 0.1262
-2.250 0.3551 0.01174 0.00377 -0.1429 0.8018 0.1364
-2.000 0.3831 0.01164 0.00364 -0.1428 0.7928 0.1465
-1.750 0.4112 0.01153 0.00354 -0.1427 0.7842 0.1594
-1.500 0.4392 0.01143 0.00344 -0.1426 0.7755 0.1748
-1.250 0.4667 0.01132 0.00339 -0.1425 0.7666 0.1954
-1.000 0.4947 0.01121 0.00335 -0.1424 0.7581 0.2297
-0.750 0.5218 0.01113 0.00337 -0.1422 0.7487 0.2701
-0.500 0.5496 0.01109 0.00335 -0.1421 0.7404 0.3025
-0.250 0.5766 0.01106 0.00337 -0.1418 0.7309 0.3295
0.000 0.6039 0.01105 0.00339 -0.1415 0.7221 0.3556
0.250 0.6310 0.01105 0.00342 -0.1412 0.7130 0.3822
0.500 0.6580 0.01106 0.00348 -0.1409 0.7038 0.4089
0.750 0.6851 0.01108 0.00351 -0.1406 0.6946 0.4365
1.000 0.7114 0.01109 0.00357 -0.1401 0.6833 0.4654
1.250 0.7375 0.01107 0.00363 -0.1396 0.6714 0.5023
1.500 0.7630 0.01102 0.00371 -0.1390 0.6592 0.5528
1.750 0.7871 0.01089 0.00381 -0.1380 0.6472 0.6508
2.000 0.8114 0.01037 0.00380 -0.1366 0.6346 1.0000
2.250 0.8375 0.01052 0.00387 -0.1361 0.6211 1.0000
2.500 0.8634 0.01069 0.00395 -0.1356 0.6072 1.0000
2.750 0.8895 0.01086 0.00406 -0.1351 0.5950 1.0000
3.000 0.9156 0.01105 0.00417 -0.1346 0.5845 1.0000
3.250 0.9415 0.01123 0.00432 -0.1342 0.5729 1.0000
3.500 0.9673 0.01142 0.00448 -0.1337 0.5617 1.0000
3.750 0.9929 0.01163 0.00465 -0.1331 0.5510 1.0000
4.000 1.0183 0.01184 0.00484 -0.1326 0.5397 1.0000
4.250 1.0435 0.01205 0.00504 -0.1320 0.5276 1.0000
4.500 1.0684 0.01229 0.00527 -0.1313 0.5147 1.0000
4.750 1.0929 0.01254 0.00550 -0.1306 0.5017 1.0000
5.000 1.1172 0.01280 0.00574 -0.1298 0.4885 1.0000
5.250 1.1410 0.01307 0.00602 -0.1290 0.4733 1.0000
5.500 1.1642 0.01336 0.00630 -0.1281 0.4558 1.0000
5.750 1.1869 0.01368 0.00660 -0.1271 0.4362 1.0000
6.000 1.2088 0.01403 0.00692 -0.1259 0.4153 1.0000
6.250 1.2292 0.01446 0.00729 -0.1245 0.3888 1.0000
6.500 1.2466 0.01504 0.00772 -0.1227 0.3532 1.0000
6.750 1.2617 0.01577 0.00824 -0.1206 0.3141 1.0000
7.000 1.2766 0.01655 0.00882 -0.1185 0.2812 1.0000
7.250 1.2925 0.01727 0.00944 -0.1165 0.2584 1.0000
7.500 1.3089 0.01795 0.01005 -0.1147 0.2402 1.0000
7.750 1.3249 0.01863 0.01068 -0.1129 0.2217 1.0000
8.000 1.3400 0.01932 0.01131 -0.1109 0.2033 1.0000
8.250 1.3541 0.01999 0.01195 -0.1087 0.1859 1.0000
8.500 1.3681 0.02067 0.01262 -0.1065 0.1687 1.0000
8.750 1.3806 0.02145 0.01334 -0.1043 0.1476 1.0000
9.000 1.3904 0.02242 0.01418 -0.1017 0.1202 1.0000
9.250 1.3957 0.02372 0.01527 -0.0987 0.0894 1.0000
9.500 1.4010 0.02509 0.01651 -0.0958 0.0692 1.0000
9.750 1.4081 0.02637 0.01776 -0.0933 0.0564 1.0000
10.000 1.4150 0.02770 0.01909 -0.0908 0.0468 1.0000
10.250 1.4215 0.02911 0.02052 -0.0885 0.0392 1.0000
10.500 1.4288 0.03049 0.02195 -0.0863 0.0337 1.0000
10.750 1.4346 0.03204 0.02356 -0.0842 0.0300 1.0000
11.000 1.4408 0.03360 0.02521 -0.0823 0.0272 1.0000
11.250 1.4442 0.03546 0.02713 -0.0803 0.0252 1.0000
11.500 1.4488 0.03729 0.02907 -0.0786 0.0236 1.0000
11.750 1.4532 0.03919 0.03110 -0.0771 0.0220 1.0000
12.000 1.4564 0.04129 0.03329 -0.0757 0.0208 1.0000
12.250 1.4568 0.04374 0.03584 -0.0744 0.0198 1.0000
12.500 1.4560 0.04641 0.03862 -0.0732 0.0191 1.0000
12.750 1.4569 0.04902 0.04137 -0.0723 0.0185 1.0000
13.000 1.4568 0.05183 0.04433 -0.0715 0.0179 1.0000
13.250 1.4561 0.05479 0.04742 -0.0709 0.0173 1.0000
13.500 1.4552 0.05790 0.05066 -0.0705 0.0168 1.0000
13.750 1.4538 0.06118 0.05405 -0.0704 0.0163 1.0000
14.000 1.4518 0.06464 0.05763 -0.0704 0.0159 1.0000
14.250 1.4485 0.06839 0.06148 -0.0706 0.0154 1.0000
14.500 1.4430 0.07255 0.06574 -0.0711 0.0150 1.0000
14.750 1.4396 0.07655 0.06988 -0.0716 0.0146 1.0000
15.000 1.4381 0.08038 0.07387 -0.0722 0.0143 1.0000
15.250 1.4359 0.08439 0.07804 -0.0730 0.0140 1.0000
15.500 1.4333 0.08855 0.08235 -0.0739 0.0137 1.0000
15.750 1.4304 0.09286 0.08680 -0.0750 0.0134 1.0000
16.000 1.4272 0.09726 0.09135 -0.0763 0.0131 1.0000
16.250 1.4238 0.10176 0.09599 -0.0777 0.0129 1.0000
16.500 1.4202 0.10640 0.10077 -0.0793 0.0127 1.0000
16.750 1.4165 0.11113 0.10564 -0.0810 0.0125 1.0000
17.000 1.4126 0.11597 0.11062 -0.0830 0.0123 1.0000
17.250 1.4084 0.12092 0.11570 -0.0852 0.0121 1.0000
17.500 1.4040 0.12598 0.12089 -0.0876 0.0120 1.0000
17.750 1.3995 0.13113 0.12616 -0.0902 0.0118 1.0000
18.000 1.3951 0.13632 0.13147 -0.0929 0.0116 1.0000
18.250 1.3907 0.14155 0.13681 -0.0958 0.0115 1.0000
18.500 1.3859 0.14691 0.14230 -0.0988 0.0113 1.0000
18.750 1.3796 0.15268 0.14820 -0.1022 0.0112 1.0000
19.000 1.3711 0.15940 0.15511 -0.1066 0.0111 1.0000
19.250 1.3614 0.16661 0.16251 -0.1114 0.0110 1.0000
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