GOE 494 AIRFOIL (goe494-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 494 AIRFOIL (goe494-il) Reynolds number: 100,000 Max Cl/Cd: 69.64 at α=4° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe494-il-100000-n5.txt Download as CSV file: xf-goe494-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 494 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
------ -------- --------- --------- -------- -------- --------
-7.750 -0.3432 0.10130 0.09654 -0.0304 1.0000 0.0328
-7.500 -0.3520 0.10014 0.09548 -0.0287 1.0000 0.0330
-7.250 -0.3607 0.09890 0.09434 -0.0271 1.0000 0.0331
-7.000 -0.3649 0.09711 0.09263 -0.0268 1.0000 0.0333
-6.750 -0.3672 0.09518 0.09077 -0.0274 1.0000 0.0334
-6.500 -0.3620 0.09248 0.08812 -0.0297 0.9991 0.0335
-6.000 -0.3295 0.08308 0.07872 -0.0328 0.9913 0.0363
-5.750 -0.3039 0.07887 0.07448 -0.0389 0.9863 0.0383
-5.500 -0.2753 0.07443 0.07000 -0.0467 0.9800 0.0408
-5.250 -0.2114 0.06797 0.06335 -0.0693 0.9725 0.0444
-5.000 -0.2039 0.06392 0.05936 -0.0666 0.9686 0.0466
-4.500 -0.1236 0.05281 0.04793 -0.0846 0.9582 0.0422
-4.250 -0.0767 0.04644 0.04135 -0.0947 0.9553 0.0389
-4.000 -0.0185 0.03889 0.03330 -0.1076 0.9519 0.0427
-3.750 0.0298 0.03282 0.02661 -0.1158 0.9484 0.0425
-3.500 0.0723 0.02894 0.02218 -0.1213 0.9454 0.0472
-3.250 0.1133 0.02609 0.01878 -0.1252 0.9429 0.0489
-3.000 0.1541 0.02375 0.01582 -0.1285 0.9409 0.0499
-2.750 0.1846 0.02262 0.01429 -0.1295 0.9351 0.0540
-2.500 0.2196 0.02139 0.01264 -0.1311 0.9314 0.0551
-2.250 0.2560 0.02022 0.01117 -0.1329 0.9287 0.0544
-2.000 0.2892 0.01934 0.01005 -0.1341 0.9249 0.0540
-1.750 0.3194 0.01865 0.00924 -0.1346 0.9195 0.0537
-1.500 0.3536 0.01802 0.00851 -0.1359 0.9161 0.0537
-1.250 0.3893 0.01747 0.00787 -0.1375 0.9134 0.0538
-1.000 0.4157 0.01718 0.00752 -0.1373 0.9060 0.0545
-0.750 0.4503 0.01681 0.00706 -0.1385 0.9017 0.0556
-0.250 0.5125 0.01627 0.00642 -0.1397 0.8895 0.0628
0.000 0.5478 0.01594 0.00610 -0.1410 0.8859 0.0826
0.250 0.5755 0.01533 0.00634 -0.1415 0.8790 0.3538
0.500 0.6061 0.01480 0.00642 -0.1421 0.8744 0.5441
0.750 0.6321 0.01410 0.00635 -0.1413 0.8687 1.0000
1.000 0.6603 0.01423 0.00641 -0.1413 0.8622 1.0000
1.250 0.6929 0.01426 0.00641 -0.1421 0.8581 1.0000
1.500 0.7173 0.01449 0.00662 -0.1414 0.8500 1.0000
1.750 0.7487 0.01454 0.00668 -0.1419 0.8453 1.0000
2.250 0.8042 0.01483 0.00709 -0.1417 0.8321 1.0000
2.500 0.8299 0.01500 0.00733 -0.1412 0.8234 1.0000
2.750 0.8593 0.01494 0.00737 -0.1410 0.8137 1.0000
3.000 0.8881 0.01482 0.00739 -0.1404 0.8007 1.0000
3.250 0.9157 0.01473 0.00741 -0.1397 0.7857 1.0000
3.500 0.9437 0.01450 0.00726 -0.1386 0.7630 1.0000
3.750 0.9700 0.01428 0.00705 -0.1369 0.7274 1.0000
4.000 0.9930 0.01426 0.00703 -0.1347 0.6772 1.0000
4.250 1.0102 0.01452 0.00688 -0.1313 0.5512 1.0000
4.500 1.0102 0.01707 0.00760 -0.1262 0.2674 1.0000
4.750 1.0141 0.02008 0.00911 -0.1228 0.0584 1.0000
5.000 1.0311 0.02159 0.01062 -0.1208 0.0412 1.0000
5.250 1.0498 0.02281 0.01206 -0.1191 0.0338 1.0000
5.500 1.0672 0.02418 0.01359 -0.1172 0.0294 1.0000
5.750 1.0845 0.02563 0.01520 -0.1152 0.0269 1.0000
6.000 1.1018 0.02721 0.01683 -0.1134 0.0238 1.0000
6.250 1.1201 0.02945 0.01906 -0.1119 0.0213 1.0000
6.500 1.1446 0.03146 0.02123 -0.1109 0.0204 1.0000
6.750 1.1714 0.03386 0.02386 -0.1101 0.0196 1.0000
7.000 1.1970 0.03634 0.02673 -0.1092 0.0184 1.0000
7.250 1.2196 0.03877 0.02951 -0.1079 0.0166 1.0000
7.500 1.2401 0.04169 0.03284 -0.1064 0.0159 1.0000
7.750 1.2575 0.04504 0.03666 -0.1045 0.0157 1.0000
8.000 1.2709 0.04865 0.04076 -0.1022 0.0156 1.0000
8.250 1.2804 0.05249 0.04510 -0.0995 0.0157 1.0000
8.500 1.2858 0.05654 0.04963 -0.0967 0.0159 1.0000
8.750 1.2870 0.06072 0.05425 -0.0937 0.0161 1.0000
9.000 1.2839 0.06495 0.05888 -0.0906 0.0163 1.0000
9.250 1.2764 0.06918 0.06346 -0.0875 0.0165 1.0000
9.500 1.2638 0.07314 0.06771 -0.0842 0.0168 1.0000
9.750 1.2469 0.07691 0.07172 -0.0809 0.0169 1.0000
10.000 1.2284 0.08100 0.07603 -0.0787 0.0171 1.0000
10.250 1.2090 0.08562 0.08084 -0.0777 0.0172 1.0000
10.500 1.1889 0.09084 0.08625 -0.0781 0.0174 1.0000
10.750 1.1686 0.09681 0.09238 -0.0799 0.0175 1.0000
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Polar data table (+)
Polar graphs
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