GOE 377 AIRFOIL (goe377-il) Xfoil prediction polar at RE=100,000 Ncrit=5
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Airfoil: GOE 377 AIRFOIL (goe377-il) Reynolds number: 100,000 Max Cl/Cd: 58.13 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe377-il-100000-n5.txt Download as CSV file: xf-goe377-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 377 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
------ -------- --------- --------- -------- -------- --------
-7.500 -0.3553 0.09268 0.08801 -0.0258 1.0000 0.0350
-7.250 -0.3617 0.09087 0.08630 -0.0257 1.0000 0.0357
-7.000 -0.3640 0.08878 0.08429 -0.0272 1.0000 0.0362
-6.750 -0.3641 0.08636 0.08192 -0.0281 1.0000 0.0364
-6.500 -0.3630 0.08387 0.07947 -0.0297 1.0000 0.0366
-6.250 -0.3602 0.08117 0.07679 -0.0302 1.0000 0.0367
-6.000 -0.3558 0.07832 0.07394 -0.0309 1.0000 0.0368
-5.750 -0.3500 0.07531 0.07091 -0.0314 1.0000 0.0368
-5.250 -0.3392 0.06651 0.06204 -0.0309 1.0000 0.0261
-5.000 -0.3165 0.06191 0.05737 -0.0343 0.9961 0.0256
-4.250 -0.2097 0.04662 0.04133 -0.0502 0.9792 0.0263
-4.000 -0.1786 0.04203 0.03647 -0.0532 0.9730 0.0261
-3.750 -0.1430 0.03734 0.03131 -0.0562 0.9679 0.0264
-3.500 -0.1176 0.03537 0.02929 -0.0579 0.9611 0.0296
-3.250 -0.0828 0.03206 0.02556 -0.0599 0.9560 0.0323
-3.000 -0.0508 0.02857 0.02149 -0.0608 0.9501 0.0336
-2.750 -0.0176 0.02564 0.01785 -0.0615 0.9445 0.0384
-2.500 0.0180 0.02385 0.01576 -0.0632 0.9406 0.0424
-2.250 0.0479 0.02261 0.01392 -0.0630 0.9332 0.0492
-2.000 0.0827 0.02089 0.01196 -0.0645 0.9287 0.0535
-1.750 0.1150 0.02007 0.01092 -0.0652 0.9224 0.0600
-1.500 0.1495 0.01917 0.00970 -0.0662 0.9166 0.0628
-1.250 0.1867 0.01817 0.00856 -0.0678 0.9122 0.0639
-1.000 0.2148 0.01739 0.00779 -0.0677 0.9036 0.0661
-0.750 0.2508 0.01671 0.00708 -0.0692 0.8986 0.0702
-0.500 0.2785 0.01630 0.00658 -0.0689 0.8887 0.0757
-0.250 0.3106 0.01584 0.00609 -0.0695 0.8801 0.0847
0.000 0.3473 0.01531 0.00558 -0.0709 0.8709 0.1103
0.500 0.4489 0.01264 0.00492 -0.0800 0.8465 1.0000
0.750 0.4775 0.01259 0.00471 -0.0798 0.8316 1.0000
1.000 0.5057 0.01256 0.00455 -0.0794 0.8161 1.0000
1.250 0.5322 0.01256 0.00444 -0.0788 0.7987 1.0000
1.500 0.5588 0.01257 0.00437 -0.0782 0.7808 1.0000
1.750 0.5859 0.01258 0.00429 -0.0776 0.7623 1.0000
2.000 0.6130 0.01261 0.00423 -0.0771 0.7432 1.0000
2.250 0.6387 0.01269 0.00426 -0.0764 0.7222 1.0000
2.500 0.6651 0.01278 0.00427 -0.0757 0.7014 1.0000
2.750 0.6900 0.01292 0.00434 -0.0749 0.6784 1.0000
3.000 0.7150 0.01308 0.00445 -0.0740 0.6552 1.0000
3.250 0.7394 0.01328 0.00458 -0.0731 0.6311 1.0000
3.500 0.7633 0.01350 0.00475 -0.0721 0.6064 1.0000
3.750 0.7870 0.01376 0.00495 -0.0711 0.5814 1.0000
4.000 0.8102 0.01406 0.00521 -0.0700 0.5561 1.0000
4.250 0.8331 0.01438 0.00549 -0.0689 0.5308 1.0000
4.500 0.8556 0.01472 0.00581 -0.0678 0.5050 1.0000
4.750 0.8776 0.01510 0.00615 -0.0666 0.4775 1.0000
5.000 0.8989 0.01552 0.00655 -0.0653 0.4481 1.0000
5.250 0.9201 0.01595 0.00695 -0.0640 0.4200 1.0000
5.500 0.9414 0.01640 0.00740 -0.0628 0.3961 1.0000
5.750 0.9628 0.01688 0.00790 -0.0616 0.3748 1.0000
6.000 0.9841 0.01738 0.00848 -0.0604 0.3551 1.0000
6.250 1.0020 0.01798 0.00899 -0.0587 0.3194 1.0000
6.500 1.0176 0.01873 0.00951 -0.0568 0.2708 1.0000
6.750 1.0352 0.01943 0.01013 -0.0552 0.2284 1.0000
7.000 1.0493 0.02056 0.01088 -0.0532 0.1464 1.0000
7.250 1.0536 0.02305 0.01251 -0.0502 0.0440 1.0000
7.500 1.0674 0.02449 0.01397 -0.0480 0.0291 1.0000
7.750 1.0810 0.02589 0.01553 -0.0458 0.0247 1.0000
8.000 1.0940 0.02722 0.01708 -0.0436 0.0222 1.0000
8.250 1.1054 0.02858 0.01867 -0.0412 0.0198 1.0000
8.500 1.1145 0.03004 0.02033 -0.0385 0.0186 1.0000
8.750 1.1210 0.03166 0.02215 -0.0356 0.0177 1.0000
9.000 1.1256 0.03336 0.02400 -0.0324 0.0170 1.0000
9.250 1.1304 0.03518 0.02596 -0.0294 0.0165 1.0000
9.500 1.1360 0.03744 0.02833 -0.0267 0.0156 1.0000
9.750 1.1464 0.04095 0.03203 -0.0250 0.0144 1.0000
10.000 1.1563 0.04297 0.03427 -0.0230 0.0139 1.0000
10.250 1.1649 0.04535 0.03694 -0.0209 0.0136 1.0000
10.500 1.1704 0.04813 0.04001 -0.0188 0.0134 1.0000
10.750 1.1717 0.05108 0.04326 -0.0166 0.0132 1.0000
11.000 1.1693 0.05410 0.04667 -0.0145 0.0132 1.0000
11.250 1.1632 0.05737 0.05024 -0.0125 0.0131 1.0000
11.500 1.1540 0.06090 0.05406 -0.0111 0.0131 1.0000
11.750 1.1428 0.06470 0.05812 -0.0102 0.0131 1.0000
12.000 1.1290 0.06896 0.06264 -0.0101 0.0131 1.0000
12.250 1.1156 0.07344 0.06735 -0.0108 0.0132 1.0000
12.500 1.0985 0.07886 0.07300 -0.0125 0.0132 1.0000
12.750 1.0827 0.08446 0.07879 -0.0150 0.0133 1.0000
13.000 1.0661 0.09072 0.08524 -0.0183 0.0133 1.0000
13.250 1.0484 0.09775 0.09245 -0.0224 0.0134 1.0000
13.500 1.0315 0.10522 0.10006 -0.0270 0.0135 1.0000
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Polar data table (+)
Polar graphs
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