GOE 508 AIRFOIL (goe508-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 508 AIRFOIL (goe508-il) Reynolds number: 100,000 Max Cl/Cd: 43.67 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe508-il-100000-n5.txt Download as CSV file: xf-goe508-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 508 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
------ -------- --------- --------- -------- -------- --------
-10.500 -0.0380 0.09416 0.08848 -0.1062 0.8964 0.0590
-10.250 -0.0228 0.09102 0.08529 -0.1085 0.8886 0.0585
-10.000 -0.0148 0.08758 0.08181 -0.1107 0.8798 0.0582
-9.750 -0.0104 0.08366 0.07785 -0.1134 0.8712 0.0582
-9.500 -0.0119 0.07926 0.07342 -0.1164 0.8623 0.0585
-9.250 -0.0117 0.07532 0.06946 -0.1187 0.8536 0.0584
-9.000 -0.0135 0.07120 0.06530 -0.1211 0.8456 0.0582
-8.750 -0.0216 0.06675 0.06085 -0.1234 0.8363 0.0579
-8.500 -0.0401 0.06073 0.05479 -0.1276 0.8275 0.0575
-8.250 -0.0819 0.05397 0.04789 -0.1292 0.8166 0.0568
-8.000 -0.1189 0.04760 0.04116 -0.1286 0.8083 0.0566
-7.750 -0.1374 0.04344 0.03665 -0.1264 0.7997 0.0567
-7.500 -0.1431 0.03968 0.03241 -0.1245 0.7937 0.0571
-7.250 -0.1452 0.03685 0.02911 -0.1219 0.7864 0.0580
-7.000 -0.1421 0.03414 0.02583 -0.1194 0.7795 0.0591
-6.750 -0.1203 0.03316 0.02476 -0.1189 0.7747 0.0600
-6.500 -0.1046 0.03221 0.02369 -0.1173 0.7681 0.0609
-6.250 -0.0877 0.03108 0.02236 -0.1158 0.7617 0.0618
-6.000 -0.0670 0.02976 0.02078 -0.1149 0.7570 0.0629
-5.750 -0.0472 0.02857 0.01932 -0.1138 0.7519 0.0641
-5.500 -0.0298 0.02755 0.01801 -0.1121 0.7450 0.0656
-5.250 -0.0062 0.02684 0.01724 -0.1114 0.7399 0.0673
-5.000 0.0208 0.02621 0.01651 -0.1112 0.7359 0.0693
-4.750 0.0380 0.02573 0.01595 -0.1094 0.7285 0.0713
-4.500 0.0614 0.02497 0.01497 -0.1085 0.7232 0.0736
-4.250 0.0879 0.02441 0.01441 -0.1082 0.7192 0.0756
-4.000 0.1100 0.02407 0.01403 -0.1072 0.7137 0.0783
-3.750 0.1313 0.02370 0.01353 -0.1059 0.7075 0.0822
-3.500 0.1566 0.02330 0.01317 -0.1054 0.7028 0.0857
-3.250 0.1854 0.02281 0.01254 -0.1053 0.6993 0.0908
-3.000 0.2022 0.02269 0.01249 -0.1035 0.6923 0.0950
-2.750 0.2257 0.02243 0.01217 -0.1026 0.6874 0.1020
-2.500 0.2521 0.02205 0.01181 -0.1022 0.6836 0.1096
-2.250 0.2765 0.02176 0.01151 -0.1015 0.6794 0.1195
-2.000 0.2947 0.02171 0.01146 -0.0998 0.6730 0.1300
-1.750 0.3187 0.02146 0.01126 -0.0990 0.6684 0.1431
-1.500 0.3463 0.02117 0.01097 -0.0988 0.6649 0.1584
-1.250 0.3674 0.02111 0.01097 -0.0976 0.6602 0.1737
-1.000 0.3863 0.02112 0.01107 -0.0961 0.6548 0.1902
-0.750 0.4108 0.02098 0.01097 -0.0954 0.6506 0.2145
-0.500 0.4387 0.02067 0.01080 -0.0954 0.6473 0.2554
-0.250 0.4594 0.02051 0.01089 -0.0942 0.6427 0.3123
0.000 0.4769 0.02031 0.01112 -0.0927 0.6375 0.4136
0.250 0.4959 0.01967 0.01128 -0.0907 0.6337 0.6329
0.500 0.5981 0.01927 0.01137 -0.1038 0.6310 0.9342
0.750 0.6615 0.01929 0.01118 -0.1105 0.6278 0.9809
1.000 0.6961 0.01971 0.01155 -0.1125 0.6215 1.0000
1.250 0.7137 0.01987 0.01161 -0.1107 0.6164 1.0000
1.500 0.7394 0.01983 0.01140 -0.1101 0.6122 1.0000
1.750 0.7525 0.02013 0.01164 -0.1075 0.6063 1.0000
2.000 0.7674 0.02035 0.01180 -0.1052 0.6000 1.0000
2.250 0.7935 0.02030 0.01160 -0.1046 0.5952 1.0000
2.500 0.8090 0.02055 0.01179 -0.1024 0.5895 1.0000
2.750 0.8222 0.02083 0.01204 -0.0998 0.5830 1.0000
3.000 0.8486 0.02078 0.01186 -0.0993 0.5778 1.0000
3.250 0.8625 0.02105 0.01208 -0.0968 0.5714 1.0000
3.500 0.8766 0.02129 0.01229 -0.0943 0.5646 1.0000
3.750 0.9039 0.02126 0.01214 -0.0940 0.5597 1.0000
4.000 0.9154 0.02164 0.01253 -0.0912 0.5538 1.0000
4.250 0.9279 0.02200 0.01288 -0.0886 0.5479 1.0000
4.500 0.9530 0.02205 0.01285 -0.0880 0.5429 1.0000
4.750 0.9682 0.02235 0.01313 -0.0858 0.5374 1.0000
5.000 0.9760 0.02281 0.01362 -0.0825 0.5307 1.0000
5.250 0.9997 0.02289 0.01363 -0.0816 0.5255 1.0000
5.500 1.0120 0.02324 0.01397 -0.0790 0.5197 1.0000
5.750 1.0148 0.02378 0.01455 -0.0750 0.5128 1.0000
6.000 1.0389 0.02384 0.01456 -0.0742 0.5073 1.0000
6.250 1.0424 0.02446 0.01521 -0.0705 0.5002 1.0000
6.500 1.0516 0.02495 0.01571 -0.0678 0.4929 1.0000
6.750 1.0735 0.02506 0.01577 -0.0668 0.4865 1.0000
7.000 1.0686 0.02609 0.01688 -0.0624 0.4770 1.0000
7.250 1.0917 0.02612 0.01684 -0.0616 0.4699 1.0000
7.500 1.0844 0.02743 0.01824 -0.0574 0.4591 1.0000
7.750 1.0969 0.02795 0.01875 -0.0555 0.4501 1.0000
8.000 1.1014 0.02891 0.01974 -0.0529 0.4394 1.0000
8.250 1.1036 0.03010 0.02097 -0.0504 0.4281 1.0000
8.500 1.1165 0.03071 0.02153 -0.0488 0.4177 1.0000
8.750 1.1222 0.03179 0.02262 -0.0467 0.4055 1.0000
9.000 1.1269 0.03302 0.02386 -0.0447 0.3928 1.0000
9.250 1.1360 0.03399 0.02478 -0.0430 0.3803 1.0000
9.500 1.1480 0.03477 0.02548 -0.0416 0.3685 1.0000
9.750 1.1577 0.03578 0.02642 -0.0401 0.3567 1.0000
10.000 1.1660 0.03696 0.02758 -0.0386 0.3457 1.0000
10.250 1.1794 0.03777 0.02830 -0.0374 0.3367 1.0000
10.500 1.1888 0.03895 0.02946 -0.0361 0.3277 1.0000
10.750 1.2011 0.03991 0.03035 -0.0350 0.3198 1.0000
11.000 1.2102 0.04117 0.03160 -0.0338 0.3119 1.0000
11.250 1.2243 0.04203 0.03238 -0.0328 0.3052 1.0000
11.500 1.2321 0.04348 0.03388 -0.0317 0.2982 1.0000
11.750 1.2462 0.04437 0.03470 -0.0308 0.2923 1.0000
12.000 1.2582 0.04551 0.03585 -0.0300 0.2870 1.0000
12.250 1.2677 0.04690 0.03731 -0.0291 0.2816 1.0000
12.500 1.2819 0.04785 0.03823 -0.0283 0.2768 1.0000
12.750 1.2983 0.04864 0.03899 -0.0277 0.2724 1.0000
13.000 1.3041 0.05042 0.04088 -0.0268 0.2676 1.0000
13.250 1.3134 0.05186 0.04238 -0.0261 0.2629 1.0000
13.500 1.3301 0.05260 0.04307 -0.0255 0.2584 1.0000
13.750 1.3393 0.05410 0.04463 -0.0248 0.2543 1.0000
14.000 1.3429 0.05616 0.04682 -0.0241 0.2500 1.0000
14.250 1.3499 0.05788 0.04861 -0.0235 0.2455 1.0000
14.500 1.3654 0.05874 0.04945 -0.0230 0.2416 1.0000
14.750 1.3756 0.06021 0.05097 -0.0225 0.2380 1.0000
15.000 1.3734 0.06296 0.05391 -0.0219 0.2341 1.0000
15.250 1.3763 0.06521 0.05627 -0.0215 0.2301 1.0000
15.500 1.3861 0.06671 0.05782 -0.0211 0.2264 1.0000
15.750 1.4083 0.06685 0.05787 -0.0207 0.2228 1.0000
16.000 1.3938 0.07110 0.06239 -0.0205 0.2191 1.0000
16.250 1.3868 0.07461 0.06607 -0.0204 0.2151 1.0000
16.500 1.3888 0.07709 0.06865 -0.0203 0.2113 1.0000
16.750 1.4026 0.07808 0.06963 -0.0200 0.2077 1.0000
17.000 1.3947 0.08185 0.07357 -0.0202 0.2040 1.0000
17.250 1.3718 0.08770 0.07966 -0.0210 0.1995 1.0000
17.500 1.3660 0.09137 0.08345 -0.0215 0.1954 1.0000
17.750 1.3790 0.09244 0.08453 -0.0214 0.1921 1.0000
18.000 1.3540 0.09898 0.09128 -0.0229 0.1880 1.0000
18.250 1.3007 0.11012 0.10271 -0.0261 0.1820 1.0000
18.500 1.3070 0.11224 0.10487 -0.0266 0.1787 1.0000
18.750 1.3350 0.11092 0.10354 -0.0258 0.1764 1.0000
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