GOE 361 AIRFOIL (goe361-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 361 AIRFOIL (goe361-il) Reynolds number: 100,000 Max Cl/Cd: 59.78 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe361-il-100000-n5.txt Download as CSV file: xf-goe361-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 361 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 -0.2726 0.10004 0.09541 -0.0262 1.0000 0.0349
-7.500 -0.2814 0.09971 0.09521 -0.0262 1.0000 0.0353
-7.250 -0.2823 0.09830 0.09389 -0.0275 1.0000 0.0354
-7.000 -0.2815 0.09675 0.09243 -0.0296 1.0000 0.0356
-6.750 -0.2789 0.09468 0.09042 -0.0311 1.0000 0.0357
-6.500 -0.2805 0.08956 0.08538 -0.0258 1.0000 0.0364
-6.250 -0.2803 0.08655 0.08243 -0.0227 1.0000 0.0372
-6.000 -0.2716 0.08359 0.07950 -0.0233 0.9978 0.0384
-5.750 -0.2426 0.07939 0.07526 -0.0296 0.9900 0.0405
-5.500 -0.1853 0.07542 0.07113 -0.0490 0.9783 0.0465
-5.250 -0.1603 0.07009 0.06580 -0.0533 0.9699 0.0478
-5.000 -0.1380 0.06617 0.06187 -0.0545 0.9622 0.0501
-4.750 -0.1008 0.06219 0.05781 -0.0615 0.9529 0.0546
-4.500 -0.0471 0.05727 0.05268 -0.0749 0.9418 0.0601
-4.250 -0.0226 0.05404 0.04944 -0.0760 0.9333 0.0652
-4.000 0.0401 0.04970 0.04470 -0.0896 0.9240 0.0728
-3.750 0.0618 0.04628 0.04132 -0.0901 0.9131 0.0753
-3.500 0.1157 0.04350 0.03808 -0.0988 0.9027 0.0869
-3.250 0.1396 0.03999 0.03466 -0.0996 0.8929 0.0904
-3.000 0.1738 0.03742 0.03191 -0.1025 0.8798 0.0954
-2.500 0.2551 0.03024 0.02389 -0.1094 0.8534 0.0639
-2.250 0.2938 0.02747 0.02051 -0.1113 0.8394 0.0575
-2.000 0.3245 0.02545 0.01822 -0.1122 0.8243 0.0555
-1.750 0.3559 0.02365 0.01606 -0.1129 0.8086 0.0536
-1.500 0.3870 0.02205 0.01406 -0.1132 0.7927 0.0521
-1.250 0.4175 0.02072 0.01231 -0.1133 0.7762 0.0513
-1.000 0.4464 0.01965 0.01088 -0.1130 0.7576 0.0510
-0.750 0.4744 0.01894 0.00990 -0.1126 0.7368 0.0533
-0.500 0.5023 0.01829 0.00892 -0.1121 0.7162 0.0551
-0.250 0.5293 0.01765 0.00802 -0.1115 0.6950 0.0550
0.000 0.5560 0.01712 0.00727 -0.1108 0.6757 0.0550
0.250 0.5825 0.01670 0.00667 -0.1102 0.6582 0.0552
0.500 0.6090 0.01635 0.00620 -0.1096 0.6416 0.0557
0.750 0.6347 0.01610 0.00583 -0.1089 0.6251 0.0564
1.000 0.6602 0.01592 0.00555 -0.1082 0.6089 0.0574
1.250 0.6869 0.01584 0.00532 -0.1077 0.5927 0.0589
1.500 0.7137 0.01577 0.00516 -0.1073 0.5766 0.0617
1.750 0.7401 0.01579 0.00508 -0.1069 0.5602 0.0688
2.000 0.7666 0.01579 0.00504 -0.1065 0.5434 0.0850
2.250 0.7960 0.01420 0.00515 -0.1070 0.5263 1.0000
2.500 0.8214 0.01445 0.00516 -0.1064 0.5096 1.0000
2.750 0.8467 0.01472 0.00524 -0.1057 0.4932 1.0000
3.000 0.8718 0.01500 0.00538 -0.1051 0.4774 1.0000
3.250 0.8968 0.01531 0.00555 -0.1045 0.4625 1.0000
3.500 0.9217 0.01563 0.00575 -0.1038 0.4484 1.0000
3.750 0.9465 0.01597 0.00600 -0.1032 0.4348 1.0000
4.000 0.9713 0.01632 0.00631 -0.1026 0.4217 1.0000
4.250 0.9961 0.01669 0.00663 -0.1020 0.4095 1.0000
4.500 1.0206 0.01708 0.00697 -0.1015 0.3981 1.0000
4.750 1.0450 0.01749 0.00736 -0.1008 0.3876 1.0000
5.000 1.0694 0.01789 0.00777 -0.1002 0.3770 1.0000
5.250 1.0939 0.01831 0.00821 -0.0997 0.3675 1.0000
5.500 1.1181 0.01877 0.00866 -0.0990 0.3598 1.0000
5.750 1.1428 0.01921 0.00922 -0.0985 0.3518 1.0000
6.000 1.1671 0.01970 0.00973 -0.0979 0.3456 1.0000
6.250 1.1916 0.02019 0.01035 -0.0974 0.3393 1.0000
6.500 1.2153 0.02066 0.01091 -0.0967 0.3316 1.0000
6.750 1.2358 0.02100 0.01129 -0.0956 0.3136 1.0000
7.000 1.2558 0.02136 0.01170 -0.0944 0.2925 1.0000
7.250 1.2763 0.02182 0.01223 -0.0933 0.2757 1.0000
7.500 1.2946 0.02236 0.01277 -0.0919 0.2484 1.0000
7.750 1.3119 0.02308 0.01348 -0.0905 0.2143 1.0000
8.000 1.3088 0.02616 0.01540 -0.0872 0.0543 1.0000
8.250 1.3160 0.02831 0.01741 -0.0847 0.0372 1.0000
8.500 1.3278 0.02979 0.01908 -0.0826 0.0329 1.0000
8.750 1.3381 0.03127 0.02081 -0.0804 0.0304 1.0000
9.000 1.3437 0.03298 0.02274 -0.0778 0.0282 1.0000
9.250 1.3408 0.03500 0.02496 -0.0744 0.0264 1.0000
9.500 1.3372 0.03703 0.02718 -0.0711 0.0253 1.0000
9.750 1.3360 0.03900 0.02939 -0.0686 0.0245 1.0000
10.000 1.3317 0.04137 0.03197 -0.0664 0.0239 1.0000
10.250 1.3263 0.04409 0.03487 -0.0647 0.0234 1.0000
10.500 1.3204 0.04712 0.03809 -0.0635 0.0230 1.0000
10.750 1.3147 0.05040 0.04153 -0.0629 0.0226 1.0000
11.000 1.3100 0.05379 0.04506 -0.0625 0.0220 1.0000
11.250 1.3071 0.05710 0.04849 -0.0622 0.0214 1.0000
11.500 1.3060 0.06026 0.05175 -0.0618 0.0206 1.0000
11.750 1.3066 0.06325 0.05482 -0.0614 0.0197 1.0000
12.000 1.3090 0.06602 0.05764 -0.0608 0.0187 1.0000
12.250 1.3169 0.06814 0.05977 -0.0594 0.0180 1.0000
12.500 1.3332 0.06969 0.06135 -0.0570 0.0174 1.0000
12.750 1.3651 0.07148 0.06314 -0.0535 0.0166 1.0000
13.000 1.3686 0.07476 0.06666 -0.0531 0.0165 1.0000
13.250 1.3673 0.07841 0.07057 -0.0533 0.0164 1.0000
13.500 1.3631 0.08238 0.07479 -0.0538 0.0162 1.0000
13.750 1.3568 0.08666 0.07932 -0.0547 0.0159 1.0000
14.000 1.3490 0.09127 0.08418 -0.0561 0.0157 1.0000
14.250 1.3398 0.09621 0.08938 -0.0579 0.0155 1.0000
14.500 1.3300 0.10144 0.09485 -0.0600 0.0153 1.0000
14.750 1.3192 0.10704 0.10069 -0.0625 0.0152 1.0000
15.000 1.3079 0.11299 0.10686 -0.0656 0.0151 1.0000
15.250 1.2960 0.11931 0.11340 -0.0690 0.0150 1.0000
15.500 1.2838 0.12598 0.12028 -0.0729 0.0150 1.0000
15.750 1.2712 0.13304 0.12754 -0.0773 0.0150 1.0000
16.000 1.2586 0.14045 0.13514 -0.0820 0.0151 1.0000
16.250 1.2457 0.14829 0.14315 -0.0872 0.0151 1.0000
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Polar data table (+)
Polar graphs
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