GOE 54 AIRFOIL (goe54-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 54 AIRFOIL (goe54-il) Reynolds number: 200,000 Max Cl/Cd: 58.66 at α=10.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe54-il-200000.txt Download as CSV file: xf-goe54-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 54 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.4468 0.09961 0.09643 0.0284 1.0000 0.0285
-8.250 -0.4429 0.09597 0.09282 0.0277 1.0000 0.0289
-8.000 -0.5522 0.10343 0.10012 0.0339 1.0000 0.0279
-7.750 -0.5439 0.09948 0.09620 0.0344 1.0000 0.0282
-7.500 -0.5365 0.09592 0.09266 0.0330 1.0000 0.0285
-7.250 -0.5265 0.09224 0.08900 0.0304 1.0000 0.0290
-7.000 -0.5147 0.08845 0.08523 0.0269 1.0000 0.0295
-6.750 -0.5008 0.08453 0.08131 0.0228 1.0000 0.0301
-6.500 -0.4842 0.08048 0.07725 0.0181 1.0000 0.0309
-6.250 -0.4600 0.07620 0.07291 0.0107 1.0000 0.0319
-6.000 -0.4239 0.07119 0.06767 -0.0009 1.0000 0.0325
-5.750 -0.4138 0.06721 0.06378 0.0003 1.0000 0.0328
-5.500 -0.3976 0.06361 0.06019 -0.0007 1.0000 0.0333
-5.250 -0.3767 0.06007 0.05662 -0.0029 1.0000 0.0340
-5.000 -0.3523 0.05654 0.05302 -0.0057 1.0000 0.0349
-4.750 -0.3244 0.05306 0.04942 -0.0088 1.0000 0.0363
-4.500 -0.2798 0.05004 0.04590 -0.0141 1.0000 0.0380
-4.250 -0.2627 0.04613 0.04213 -0.0146 1.0000 0.0385
-4.000 -0.2398 0.04316 0.03916 -0.0157 1.0000 0.0394
-3.750 -0.2126 0.04047 0.03639 -0.0170 1.0000 0.0407
-3.500 -0.1815 0.03808 0.03385 -0.0184 1.0000 0.0428
-3.250 -0.1398 0.03608 0.03110 -0.0204 0.7765 0.0446
-3.000 -0.1226 0.03407 0.02855 -0.0193 0.6557 0.0454
-2.750 -0.0977 0.03232 0.02644 -0.0195 0.6005 0.0472
-2.250 -0.0383 0.02929 0.02255 -0.0200 0.5442 0.0527
-2.000 -0.0115 0.02759 0.02066 -0.0204 0.5250 0.0549
-1.750 0.0213 0.02781 0.02027 -0.0199 0.5086 0.0604
-1.500 0.0470 0.02502 0.01750 -0.0207 0.4941 0.0627
-1.000 0.1039 0.02277 0.01480 -0.0211 0.4663 0.0753
-0.750 0.1320 0.02180 0.01363 -0.0213 0.4524 0.0878
-0.500 0.1601 0.02102 0.01262 -0.0216 0.4377 0.1119
-0.250 0.1873 0.01985 0.01142 -0.0219 0.4224 0.1330
0.000 0.2150 0.01878 0.01026 -0.0222 0.4070 0.1609
0.250 0.2435 0.01809 0.00946 -0.0222 0.3919 0.1830
0.500 0.2725 0.01725 0.00853 -0.0221 0.3780 0.1969
0.750 0.3024 0.01670 0.00783 -0.0217 0.3659 0.1942
1.250 0.3632 0.01619 0.00691 -0.0202 0.3446 0.1460
1.500 0.3930 0.01620 0.00673 -0.0193 0.3350 0.1203
1.750 0.4221 0.01597 0.00635 -0.0186 0.3261 0.1003
2.000 0.4508 0.01579 0.00612 -0.0181 0.3175 0.0894
2.250 0.4793 0.01585 0.00605 -0.0176 0.3104 0.0816
2.500 0.5076 0.01551 0.00576 -0.0174 0.3039 0.0778
2.750 0.5359 0.01535 0.00561 -0.0172 0.2973 0.0754
3.000 0.5640 0.01534 0.00556 -0.0171 0.2915 0.0773
3.250 0.5925 0.01532 0.00556 -0.0170 0.2851 0.0767
3.500 0.6206 0.01542 0.00557 -0.0168 0.2797 0.0765
3.750 0.6488 0.01562 0.00572 -0.0166 0.2744 0.0775
4.000 0.6769 0.01578 0.00588 -0.0164 0.2686 0.0800
4.250 0.7046 0.01603 0.00605 -0.0162 0.2633 0.0906
4.500 0.7277 0.01452 0.00640 -0.0152 0.2583 1.0000
4.750 0.7555 0.01483 0.00667 -0.0150 0.2523 1.0000
5.000 0.7828 0.01533 0.00701 -0.0148 0.2470 1.0000
5.250 0.8105 0.01569 0.00744 -0.0146 0.2410 1.0000
5.500 0.8379 0.01607 0.00778 -0.0144 0.2351 1.0000
5.750 0.8649 0.01671 0.00834 -0.0143 0.2299 1.0000
6.000 0.8923 0.01707 0.00884 -0.0142 0.2236 1.0000
6.250 0.9194 0.01751 0.00922 -0.0140 0.2183 1.0000
6.500 0.9461 0.01823 0.00996 -0.0139 0.2135 1.0000
6.750 0.9731 0.01868 0.01058 -0.0137 0.2082 1.0000
7.000 0.9999 0.01904 0.01091 -0.0135 0.2032 1.0000
7.250 1.0262 0.01960 0.01148 -0.0134 0.1980 1.0000
7.500 1.0529 0.01985 0.01192 -0.0132 0.1921 1.0000
7.750 1.0794 0.02015 0.01222 -0.0130 0.1877 1.0000
8.000 1.1054 0.02074 0.01283 -0.0129 0.1835 1.0000
8.250 1.1317 0.02094 0.01327 -0.0127 0.1778 1.0000
8.500 1.1579 0.02112 0.01347 -0.0125 0.1732 1.0000
8.750 1.1836 0.02159 0.01400 -0.0123 0.1690 1.0000
9.000 1.2095 0.02184 0.01447 -0.0121 0.1633 1.0000
9.250 1.2354 0.02187 0.01451 -0.0118 0.1580 1.0000
9.500 1.2609 0.02215 0.01501 -0.0117 0.1512 1.0000
9.750 1.2863 0.02220 0.01503 -0.0114 0.1439 1.0000
10.000 1.3115 0.02236 0.01543 -0.0113 0.1338 1.0000
10.250 1.3356 0.02277 0.01594 -0.0112 0.1210 1.0000
10.500 1.3578 0.02363 0.01681 -0.0111 0.1056 1.0000
10.750 1.3793 0.02475 0.01801 -0.0110 0.0908 1.0000
11.000 1.4001 0.02593 0.01927 -0.0109 0.0795 1.0000
11.250 1.4189 0.02736 0.02073 -0.0107 0.0715 1.0000
11.500 1.4360 0.02901 0.02251 -0.0104 0.0656 1.0000
11.750 1.4475 0.03126 0.02473 -0.0100 0.0608 1.0000
12.000 1.4606 0.03322 0.02694 -0.0096 0.0572 1.0000
12.250 1.4690 0.03554 0.02938 -0.0094 0.0539 1.0000
12.500 1.4696 0.03858 0.03237 -0.0086 0.0513 1.0000
12.750 1.4709 0.04134 0.03544 -0.0088 0.0496 1.0000
13.000 1.4645 0.04510 0.03941 -0.0103 0.0482 1.0000
13.250 1.4581 0.05015 0.04463 -0.0145 0.0470 1.0000
13.500 1.4514 0.05519 0.04978 -0.0180 0.0458 1.0000
13.750 1.4443 0.05989 0.05453 -0.0204 0.0446 1.0000
14.000 1.4380 0.06368 0.05831 -0.0207 0.0432 1.0000
14.250 1.4265 0.06909 0.06386 -0.0234 0.0424 1.0000
14.500 1.4127 0.07506 0.07002 -0.0269 0.0419 1.0000
14.750 1.3976 0.08121 0.07634 -0.0303 0.0414 1.0000
15.000 1.3813 0.08756 0.08285 -0.0337 0.0410 1.0000
15.250 1.3640 0.09418 0.08963 -0.0373 0.0406 1.0000
15.500 1.3450 0.10121 0.09682 -0.0411 0.0402 1.0000
15.750 1.3246 0.10897 0.10474 -0.0454 0.0400 1.0000
16.000 1.3002 0.11804 0.11397 -0.0507 0.0400 1.0000
16.250 1.2690 0.12916 0.12529 -0.0574 0.0403 1.0000
16.500 1.2197 0.14528 0.14162 -0.0673 0.0414 1.0000
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Polar data table (+)
Polar graphs
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