GOE 630 AIRFOIL (goe630-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 630 AIRFOIL (goe630-il) Reynolds number: 500,000 Max Cl/Cd: 99.2 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe630-il-500000-n5.txt Download as CSV file: xf-goe630-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 630 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 0.0555 0.09761 0.09445 -0.1146 0.8439 0.0180
-11.000 0.0688 0.09633 0.09309 -0.1151 0.8295 0.0183
-10.750 0.0737 0.09340 0.09010 -0.1160 0.8166 0.0182
-10.500 0.0838 0.09170 0.08834 -0.1165 0.8048 0.0185
-10.250 0.0914 0.08961 0.08618 -0.1171 0.7936 0.0188
-10.000 0.0989 0.08753 0.08405 -0.1176 0.7822 0.0193
-9.750 0.1046 0.08507 0.08154 -0.1183 0.7729 0.0196
-9.500 0.1061 0.08196 0.07838 -0.1192 0.7630 0.0209
-9.250 0.1045 0.07838 0.07478 -0.1205 0.7557 0.0213
-9.000 0.1176 0.07739 0.07375 -0.1204 0.7473 0.0216
-8.750 0.1252 0.07545 0.07179 -0.1208 0.7410 0.0218
-8.500 0.1311 0.07326 0.06959 -0.1213 0.7344 0.0219
-8.250 0.1393 0.07165 0.06795 -0.1215 0.7280 0.0226
-8.000 0.1443 0.06946 0.06576 -0.1219 0.7221 0.0230
-7.750 0.1463 0.06707 0.06336 -0.1223 0.7160 0.0237
-7.250 0.1440 0.06249 0.05878 -0.1223 0.7051 0.0239
-7.000 0.1460 0.05938 0.05567 -0.1243 0.6996 0.0242
-6.750 0.1435 0.05379 0.05002 -0.1296 0.6941 0.0250
-6.500 0.1592 0.05243 0.04866 -0.1305 0.6887 0.0252
-6.250 0.1757 0.05106 0.04727 -0.1314 0.6829 0.0256
-6.000 0.1908 0.04868 0.04482 -0.1335 0.6773 0.0259
-5.750 0.2068 0.04530 0.04139 -0.1367 0.6720 0.0261
-5.500 0.2247 0.04177 0.03776 -0.1399 0.6657 0.0263
-5.250 0.2441 0.03788 0.03373 -0.1431 0.6602 0.0266
-5.000 0.2408 0.01728 0.01138 -0.1502 0.6586 0.0289
-4.750 0.2643 0.01620 0.01012 -0.1498 0.6522 0.0293
-4.500 0.2893 0.01577 0.00958 -0.1493 0.6456 0.0296
-4.250 0.3147 0.01535 0.00905 -0.1490 0.6394 0.0300
-4.000 0.3401 0.01491 0.00849 -0.1485 0.6321 0.0305
-3.750 0.3649 0.01433 0.00774 -0.1480 0.6250 0.0309
-3.500 0.3902 0.01378 0.00703 -0.1475 0.6170 0.0313
-3.250 0.4152 0.01331 0.00639 -0.1469 0.6094 0.0318
-3.000 0.4408 0.01289 0.00584 -0.1464 0.6010 0.0323
-2.750 0.4658 0.01255 0.00536 -0.1457 0.5922 0.0328
-2.500 0.4911 0.01227 0.00495 -0.1451 0.5820 0.0332
-2.250 0.5162 0.01205 0.00463 -0.1445 0.5723 0.0336
-2.000 0.5406 0.01179 0.00429 -0.1438 0.5623 0.0342
-1.750 0.5661 0.01169 0.00416 -0.1433 0.5525 0.0350
-1.500 0.5908 0.01163 0.00403 -0.1426 0.5425 0.0358
-1.250 0.6155 0.01155 0.00388 -0.1419 0.5317 0.0366
-1.000 0.6400 0.01146 0.00372 -0.1412 0.5209 0.0373
-0.750 0.6642 0.01142 0.00360 -0.1404 0.5107 0.0381
-0.500 0.6887 0.01139 0.00350 -0.1397 0.5006 0.0389
-0.250 0.7128 0.01132 0.00340 -0.1389 0.4919 0.0400
0.000 0.7370 0.01133 0.00336 -0.1381 0.4827 0.0412
0.250 0.7614 0.01134 0.00335 -0.1374 0.4744 0.0428
0.500 0.7851 0.01141 0.00335 -0.1366 0.4654 0.0447
0.750 0.8092 0.01141 0.00333 -0.1359 0.4574 0.0467
1.000 0.8324 0.01148 0.00336 -0.1349 0.4488 0.0490
1.250 0.8565 0.01153 0.00338 -0.1342 0.4418 0.0517
1.500 0.8799 0.01159 0.00341 -0.1333 0.4347 0.0548
1.750 0.9031 0.01167 0.00348 -0.1324 0.4286 0.0597
2.000 0.9268 0.01173 0.00354 -0.1317 0.4225 0.0661
2.250 0.9493 0.01182 0.00364 -0.1307 0.4165 0.0780
2.500 0.9721 0.01186 0.00375 -0.1297 0.4111 0.1146
2.750 0.9944 0.01185 0.00390 -0.1288 0.4054 0.1865
3.000 1.0152 0.01189 0.00408 -0.1275 0.3999 0.2641
3.250 1.0346 0.01168 0.00431 -0.1262 0.3950 0.4735
3.750 1.1171 0.01133 0.00483 -0.1327 0.3837 1.0000
4.000 1.1389 0.01153 0.00499 -0.1315 0.3799 1.0000
4.250 1.1604 0.01170 0.00514 -0.1304 0.3757 1.0000
4.500 1.1805 0.01190 0.00531 -0.1290 0.3717 1.0000
4.750 1.1994 0.01213 0.00550 -0.1274 0.3677 1.0000
5.000 1.2189 0.01236 0.00571 -0.1259 0.3641 1.0000
5.250 1.2398 0.01256 0.00590 -0.1247 0.3606 1.0000
5.500 1.2597 0.01279 0.00612 -0.1233 0.3566 1.0000
5.750 1.2787 0.01305 0.00636 -0.1219 0.3528 1.0000
6.000 1.2972 0.01335 0.00663 -0.1203 0.3496 1.0000
6.250 1.3179 0.01358 0.00688 -0.1192 0.3469 1.0000
6.500 1.3383 0.01383 0.00714 -0.1181 0.3440 1.0000
6.750 1.3578 0.01411 0.00744 -0.1169 0.3409 1.0000
7.000 1.3767 0.01443 0.00775 -0.1155 0.3380 1.0000
7.250 1.3948 0.01478 0.00810 -0.1142 0.3353 1.0000
7.500 1.4131 0.01515 0.00847 -0.1128 0.3326 1.0000
7.750 1.4331 0.01544 0.00881 -0.1118 0.3302 1.0000
8.000 1.4524 0.01578 0.00917 -0.1107 0.3274 1.0000
8.250 1.4709 0.01615 0.00957 -0.1095 0.3247 1.0000
8.500 1.4887 0.01657 0.01002 -0.1083 0.3221 1.0000
8.750 1.5057 0.01703 0.01049 -0.1069 0.3197 1.0000
9.000 1.5220 0.01755 0.01102 -0.1056 0.3172 1.0000
9.250 1.5412 0.01793 0.01146 -0.1046 0.3144 1.0000
9.500 1.5588 0.01839 0.01198 -0.1035 0.3104 1.0000
9.750 1.5739 0.01899 0.01258 -0.1021 0.3059 1.0000
10.000 1.5873 0.01970 0.01329 -0.1006 0.3011 1.0000
10.250 1.6045 0.02022 0.01387 -0.0996 0.2955 1.0000
10.500 1.6191 0.02091 0.01459 -0.0983 0.2910 1.0000
10.750 1.6309 0.02177 0.01545 -0.0968 0.2857 1.0000
11.000 1.6466 0.02243 0.01617 -0.0958 0.2798 1.0000
11.250 1.6587 0.02333 0.01709 -0.0945 0.2740 1.0000
11.500 1.6711 0.02424 0.01804 -0.0932 0.2687 1.0000
11.750 1.6832 0.02519 0.01903 -0.0920 0.2614 1.0000
12.000 1.6924 0.02637 0.02022 -0.0906 0.2551 1.0000
12.250 1.7030 0.02748 0.02136 -0.0893 0.2466 1.0000
12.500 1.7080 0.02903 0.02291 -0.0877 0.2344 1.0000
12.750 1.7104 0.03084 0.02469 -0.0861 0.2205 1.0000
13.000 1.7056 0.03330 0.02707 -0.0840 0.2015 1.0000
13.250 1.6952 0.03634 0.03001 -0.0818 0.1795 1.0000
13.500 1.6824 0.03974 0.03332 -0.0798 0.1602 1.0000
13.750 1.6668 0.04354 0.03705 -0.0778 0.1394 1.0000
14.000 1.6530 0.04738 0.04085 -0.0762 0.1224 1.0000
14.250 1.6254 0.05281 0.04617 -0.0745 0.0972 1.0000
14.500 1.6045 0.05783 0.05116 -0.0734 0.0816 1.0000
14.750 1.5900 0.06229 0.05564 -0.0727 0.0709 1.0000
15.000 1.5694 0.06767 0.06102 -0.0722 0.0569 1.0000
15.250 1.5414 0.07418 0.06749 -0.0719 0.0395 1.0000
15.500 1.5236 0.07957 0.07291 -0.0720 0.0315 1.0000
15.750 1.5070 0.08491 0.07831 -0.0722 0.0255 1.0000
16.000 1.4960 0.08960 0.08307 -0.0725 0.0225 1.0000
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Polar data table (+)
Polar graphs
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