GOE 514 AIRFOIL (goe514-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 514 AIRFOIL (goe514-il) Reynolds number: 1,000,000 Max Cl/Cd: 84.13 at α=7.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe514-il-1000000.txt Download as CSV file: xf-goe514-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 514 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-18.000 -0.4346 0.12456 0.12236 -0.0843 0.9884 0.0125
-17.750 -0.4547 0.11590 0.11357 -0.0894 0.9876 0.0123
-17.500 -0.4703 0.10868 0.10627 -0.0941 0.9868 0.0125
-17.250 -0.4733 0.10357 0.10111 -0.0978 0.9861 0.0127
-17.000 -0.4783 0.09825 0.09574 -0.1016 0.9853 0.0128
-16.750 -0.4868 0.09232 0.08972 -0.1060 0.9847 0.0128
-16.500 -0.4886 0.08747 0.08482 -0.1099 0.9840 0.0128
-16.250 -0.4899 0.08269 0.08001 -0.1140 0.9835 0.0131
-16.000 -0.4953 0.07742 0.07466 -0.1184 0.9829 0.0130
-15.750 -0.5015 0.07304 0.07024 -0.1211 0.9807 0.0131
-15.500 -0.5129 0.06816 0.06530 -0.1240 0.9775 0.0131
-15.250 -0.5223 0.06270 0.05977 -0.1287 0.9754 0.0133
-15.000 -0.5360 0.05653 0.05352 -0.1346 0.9736 0.0132
-14.750 -0.5652 0.04759 0.04445 -0.1443 0.9716 0.0132
-14.500 -0.6538 0.03375 0.03024 -0.1552 0.9619 0.0129
-14.250 -0.6512 0.03002 0.02634 -0.1570 0.9593 0.0130
-14.000 -0.6347 0.02708 0.02327 -0.1592 0.9577 0.0132
-13.750 -0.6074 0.02485 0.02091 -0.1620 0.9567 0.0133
-13.500 -0.5967 0.02367 0.01964 -0.1603 0.9523 0.0136
-13.250 -0.5806 0.02247 0.01834 -0.1597 0.9488 0.0138
-13.000 -0.5611 0.02134 0.01711 -0.1594 0.9461 0.0140
-12.750 -0.5369 0.02036 0.01603 -0.1599 0.9438 0.0144
-12.500 -0.5095 0.01948 0.01504 -0.1608 0.9416 0.0145
-12.250 -0.5026 0.01902 0.01450 -0.1571 0.9370 0.0148
-12.000 -0.4878 0.01838 0.01379 -0.1551 0.9333 0.0149
-11.750 -0.4749 0.01734 0.01264 -0.1531 0.9299 0.0153
-11.500 -0.4530 0.01653 0.01175 -0.1526 0.9273 0.0159
-11.250 -0.4345 0.01604 0.01120 -0.1511 0.9240 0.0162
-11.000 -0.4234 0.01560 0.01070 -0.1478 0.9193 0.0165
-10.750 -0.4015 0.01513 0.01017 -0.1468 0.9155 0.0169
-10.500 -0.3762 0.01463 0.00959 -0.1465 0.9121 0.0173
-10.250 -0.3504 0.01426 0.00915 -0.1462 0.9084 0.0179
-10.000 -0.3404 0.01375 0.00858 -0.1426 0.9035 0.0186
-9.750 -0.3197 0.01328 0.00806 -0.1412 0.8991 0.0194
-9.500 -0.2945 0.01289 0.00762 -0.1407 0.8959 0.0203
-9.250 -0.2665 0.01257 0.00724 -0.1408 0.8923 0.0212
-9.000 -0.2531 0.01218 0.00682 -0.1377 0.8874 0.0223
-8.750 -0.2317 0.01181 0.00642 -0.1363 0.8827 0.0239
-8.500 -0.2047 0.01147 0.00601 -0.1361 0.8784 0.0257
-8.250 -0.1832 0.01112 0.00565 -0.1347 0.8735 0.0286
-8.000 -0.1648 0.01077 0.00531 -0.1327 0.8675 0.0334
-7.750 -0.1393 0.01039 0.00495 -0.1321 0.8622 0.0419
-7.500 -0.1172 0.01014 0.00473 -0.1308 0.8562 0.0506
-7.250 -0.0967 0.00994 0.00455 -0.1291 0.8485 0.0566
-7.000 -0.0727 0.00982 0.00438 -0.1281 0.8406 0.0610
-6.750 -0.0525 0.00962 0.00418 -0.1264 0.8304 0.0655
-6.500 -0.0314 0.00952 0.00403 -0.1248 0.8201 0.0686
-6.250 -0.0104 0.00939 0.00385 -0.1231 0.8078 0.0715
-6.000 0.0086 0.00924 0.00364 -0.1211 0.7921 0.0755
-5.750 0.0260 0.00917 0.00349 -0.1186 0.7736 0.0782
-5.500 0.0418 0.00916 0.00336 -0.1159 0.7543 0.0809
-5.250 0.0572 0.00907 0.00321 -0.1131 0.7372 0.0858
-5.000 0.0739 0.00901 0.00309 -0.1105 0.7239 0.0903
-4.750 0.0896 0.00891 0.00298 -0.1079 0.7115 0.1013
-4.500 0.1055 0.00880 0.00295 -0.1052 0.7005 0.1265
-4.250 0.1198 0.00879 0.00293 -0.1022 0.6896 0.1372
-4.000 0.1352 0.00886 0.00292 -0.0993 0.6788 0.1433
-3.750 0.1521 0.00881 0.00287 -0.0968 0.6687 0.1499
-3.500 0.1679 0.00884 0.00285 -0.0941 0.6587 0.1544
-3.250 0.1863 0.00886 0.00282 -0.0919 0.6484 0.1571
-3.000 0.2033 0.00892 0.00282 -0.0895 0.6383 0.1590
-2.750 0.2180 0.00891 0.00276 -0.0865 0.6268 0.1624
-2.500 0.2346 0.00892 0.00274 -0.0840 0.6145 0.1657
-2.250 0.2506 0.00897 0.00275 -0.0814 0.6015 0.1690
-2.000 0.2652 0.00906 0.00276 -0.0785 0.5856 0.1713
-1.750 0.2793 0.00916 0.00278 -0.0755 0.5677 0.1731
-1.500 0.2934 0.00929 0.00281 -0.0725 0.5470 0.1745
-1.250 0.3057 0.00948 0.00286 -0.0692 0.5225 0.1755
-1.000 0.3173 0.00963 0.00291 -0.0658 0.4962 0.1794
-0.750 0.3298 0.00982 0.00300 -0.0627 0.4727 0.1824
-0.500 0.3452 0.00998 0.00307 -0.0601 0.4553 0.1851
-0.250 0.3623 0.01011 0.00314 -0.0579 0.4417 0.1882
0.000 0.3798 0.01023 0.00321 -0.0558 0.4310 0.1911
0.250 0.3968 0.01036 0.00328 -0.0535 0.4210 0.1954
0.500 0.4161 0.01042 0.00336 -0.0518 0.4142 0.2022
0.750 0.4352 0.01051 0.00343 -0.0501 0.4076 0.2107
1.000 0.4530 0.01063 0.00355 -0.0481 0.4011 0.2229
1.250 0.4734 0.01068 0.00365 -0.0466 0.3964 0.2383
1.500 0.4930 0.01078 0.00375 -0.0449 0.3913 0.2495
1.750 0.5115 0.01095 0.00389 -0.0432 0.3855 0.2584
2.000 0.5326 0.01103 0.00399 -0.0419 0.3814 0.2666
2.250 0.5540 0.01113 0.00409 -0.0406 0.3773 0.2746
2.500 0.5736 0.01127 0.00421 -0.0391 0.3728 0.2802
2.750 0.5919 0.01144 0.00437 -0.0373 0.3683 0.2861
3.000 0.6128 0.01156 0.00449 -0.0361 0.3651 0.2912
3.250 0.6347 0.01167 0.00460 -0.0350 0.3618 0.2948
3.500 0.6550 0.01178 0.00472 -0.0336 0.3584 0.3001
3.750 0.6743 0.01194 0.00488 -0.0321 0.3548 0.3049
4.000 0.6919 0.01217 0.00508 -0.0303 0.3502 0.3093
4.250 0.7136 0.01229 0.00520 -0.0293 0.3477 0.3128
4.500 0.7347 0.01239 0.00534 -0.0282 0.3450 0.3185
4.750 0.7553 0.01254 0.00550 -0.0270 0.3418 0.3233
5.000 0.7750 0.01272 0.00567 -0.0257 0.3388 0.3275
5.250 0.7929 0.01295 0.00589 -0.0241 0.3352 0.3325
5.500 0.8121 0.01315 0.00611 -0.0227 0.3321 0.3386
5.750 0.8339 0.01328 0.00627 -0.0218 0.3300 0.3444
6.000 0.8550 0.01342 0.00644 -0.0209 0.3269 0.3515
6.250 0.8750 0.01361 0.00665 -0.0197 0.3238 0.3605
6.500 0.8931 0.01385 0.00691 -0.0183 0.3200 0.3734
6.750 0.9103 0.01413 0.00722 -0.0167 0.3164 0.3925
7.000 0.9331 0.01411 0.00745 -0.0163 0.3145 0.4813
7.250 1.1754 0.01412 0.00872 -0.0638 0.3066 0.9971
7.500 1.2274 0.01459 0.00914 -0.0698 0.3018 0.9999
7.750 1.2442 0.01487 0.00943 -0.0682 0.2993 1.0000
8.000 1.2613 0.01508 0.00967 -0.0665 0.2977 1.0000
8.250 1.2781 0.01532 0.00993 -0.0649 0.2958 1.0000
8.500 1.2945 0.01559 0.01021 -0.0632 0.2934 1.0000
8.750 1.3094 0.01593 0.01054 -0.0613 0.2904 1.0000
9.000 1.3233 0.01632 0.01092 -0.0593 0.2872 1.0000
9.250 1.3383 0.01670 0.01130 -0.0575 0.2834 1.0000
9.500 1.3568 0.01694 0.01157 -0.0563 0.2807 1.0000
9.750 1.3731 0.01728 0.01193 -0.0547 0.2776 1.0000
10.000 1.3881 0.01769 0.01233 -0.0531 0.2739 1.0000
10.250 1.4008 0.01822 0.01284 -0.0511 0.2694 1.0000
10.500 1.4178 0.01857 0.01324 -0.0498 0.2671 1.0000
10.750 1.4349 0.01894 0.01362 -0.0485 0.2634 1.0000
11.000 1.4497 0.01942 0.01410 -0.0470 0.2592 1.0000
11.250 1.4626 0.02001 0.01469 -0.0453 0.2549 1.0000
11.500 1.4780 0.02049 0.01520 -0.0439 0.2516 1.0000
11.750 1.4941 0.02096 0.01570 -0.0427 0.2477 1.0000
12.000 1.5071 0.02159 0.01632 -0.0411 0.2424 1.0000
12.250 1.5189 0.02232 0.01706 -0.0395 0.2376 1.0000
12.500 1.5336 0.02291 0.01766 -0.0382 0.2315 1.0000
12.750 1.5425 0.02384 0.01857 -0.0364 0.2244 1.0000
13.000 1.5529 0.02472 0.01942 -0.0347 0.2143 1.0000
13.250 1.5603 0.02579 0.02047 -0.0329 0.2052 1.0000
13.500 1.5639 0.02715 0.02178 -0.0307 0.1920 1.0000
13.750 1.5628 0.02888 0.02342 -0.0282 0.1756 1.0000
14.000 1.5530 0.03129 0.02572 -0.0251 0.1555 1.0000
14.250 1.5470 0.03355 0.02792 -0.0227 0.1407 1.0000
14.500 1.5361 0.03633 0.03063 -0.0201 0.1253 1.0000
14.750 1.5268 0.03912 0.03338 -0.0179 0.1134 1.0000
15.000 1.5201 0.04180 0.03604 -0.0162 0.1052 1.0000
15.250 1.5114 0.04477 0.03900 -0.0146 0.0953 1.0000
15.500 1.4924 0.04884 0.04302 -0.0128 0.0787 1.0000
15.750 1.4529 0.05520 0.04930 -0.0108 0.0559 1.0000
16.000 1.4390 0.05924 0.05339 -0.0100 0.0492 1.0000
16.250 1.3957 0.06680 0.06097 -0.0092 0.0313 1.0000
16.500 1.3693 0.07279 0.06701 -0.0091 0.0218 1.0000
16.750 1.3499 0.07812 0.07242 -0.0093 0.0182 1.0000
17.000 1.3405 0.08225 0.07663 -0.0095 0.0175 1.0000
17.250 1.3255 0.08717 0.08164 -0.0100 0.0157 1.0000
17.500 1.3156 0.09150 0.08606 -0.0105 0.0152 1.0000
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