FX 77-W-270S (fx77w270s-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX 77-W-270S (fx77w270s-il) Reynolds number: 100,000 Max Cl/Cd: 9.02 at α=3.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx77w270s-il-100000-n5.txt Download as CSV file: xf-fx77w270s-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: FX 77-W-270S
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
------ -------- --------- --------- -------- -------- --------
-17.250 -0.6323 0.11681 0.10987 -0.0410 0.6237 0.0435
-17.000 -0.6930 0.10205 0.09471 -0.0497 0.6308 0.0432
-16.750 -0.7183 0.09450 0.08683 -0.0535 0.6250 0.0434
-16.500 -0.7349 0.08868 0.08071 -0.0560 0.6169 0.0436
-16.250 -0.7463 0.08385 0.07560 -0.0578 0.6085 0.0439
-16.000 -0.7539 0.07971 0.07118 -0.0590 0.6009 0.0442
-15.750 -0.7584 0.07608 0.06728 -0.0599 0.5935 0.0445
-15.500 -0.7599 0.07288 0.06382 -0.0604 0.5864 0.0448
-15.000 -0.7485 0.06837 0.05904 -0.0608 0.5736 0.0455
-14.750 -0.7414 0.06635 0.05691 -0.0609 0.5679 0.0459
-14.500 -0.7334 0.06443 0.05485 -0.0609 0.5628 0.0463
-14.250 -0.7249 0.06259 0.05286 -0.0608 0.5586 0.0468
-14.000 -0.7155 0.06082 0.05097 -0.0606 0.5547 0.0473
-13.750 -0.7053 0.05914 0.04918 -0.0604 0.5508 0.0479
-13.500 -0.6943 0.05755 0.04745 -0.0602 0.5471 0.0486
-13.250 -0.6826 0.05604 0.04578 -0.0598 0.5437 0.0494
-13.000 -0.6702 0.05467 0.04431 -0.0595 0.5405 0.0502
-12.750 -0.6578 0.05340 0.04297 -0.0591 0.5376 0.0510
-12.500 -0.6450 0.05218 0.04165 -0.0588 0.5351 0.0519
-12.250 -0.6310 0.05098 0.04038 -0.0584 0.5326 0.0529
-12.000 -0.6159 0.04985 0.03915 -0.0580 0.5300 0.0541
-11.750 -0.6006 0.04875 0.03799 -0.0576 0.5273 0.0554
-11.500 -0.5868 0.04765 0.03687 -0.0572 0.5246 0.0566
-11.250 -0.5720 0.04662 0.03579 -0.0568 0.5220 0.0582
-11.000 -0.5561 0.04566 0.03473 -0.0563 0.5194 0.0600
-10.750 -0.5410 0.04469 0.03372 -0.0558 0.5171 0.0618
-10.500 -0.5261 0.04375 0.03273 -0.0553 0.5151 0.0637
-10.250 -0.5099 0.04291 0.03178 -0.0547 0.5132 0.0662
-10.000 -0.4947 0.04203 0.03088 -0.0542 0.5116 0.0684
-9.750 -0.4790 0.04115 0.03001 -0.0536 0.5099 0.0712
-9.500 -0.4629 0.04031 0.02915 -0.0530 0.5081 0.0742
-9.250 -0.4481 0.03942 0.02829 -0.0523 0.5064 0.0775
-9.000 -0.4326 0.03860 0.02745 -0.0516 0.5047 0.0815
-8.750 -0.4181 0.03773 0.02661 -0.0508 0.5031 0.0861
-8.500 -0.4038 0.03687 0.02578 -0.0500 0.5015 0.0918
-8.250 -0.3892 0.03606 0.02498 -0.0492 0.4999 0.0991
-8.000 -0.3748 0.03525 0.02420 -0.0483 0.4983 0.1081
-7.750 -0.3609 0.03443 0.02342 -0.0473 0.4967 0.1190
-7.500 -0.3477 0.03359 0.02266 -0.0462 0.4951 0.1328
-7.250 -0.3349 0.03276 0.02190 -0.0451 0.4936 0.1507
-7.000 -0.3234 0.03190 0.02114 -0.0438 0.4922 0.1733
-6.500 -0.3146 0.02998 0.01951 -0.0393 0.4899 0.2347
-6.250 -0.3229 0.02900 0.01880 -0.0349 0.4889 0.2710
-6.000 -0.3288 0.02804 0.01817 -0.0307 0.4879 0.3236
-5.750 -0.3300 0.02727 0.01793 -0.0266 0.4868 0.3966
-5.500 -0.2764 0.03026 0.02183 -0.0260 0.4849 0.5104
-5.250 -0.2534 0.03121 0.02281 -0.0245 0.4834 0.5481
-5.000 -0.2474 0.03088 0.02238 -0.0221 0.4821 0.5754
-4.500 -0.2185 0.03098 0.02220 -0.0190 0.4790 0.6108
-4.250 -0.1860 0.03194 0.02310 -0.0188 0.4772 0.6175
-4.000 -0.1704 0.03184 0.02284 -0.0176 0.4756 0.6312
-3.750 -0.1347 0.03315 0.02411 -0.0173 0.4740 0.6389
-3.500 -0.1120 0.03383 0.02469 -0.0160 0.4727 0.6536
-3.250 -0.0766 0.03518 0.02599 -0.0155 0.4715 0.6632
-3.000 -0.0583 0.03519 0.02587 -0.0144 0.4704 0.6736
-2.750 -0.0284 0.03560 0.02618 -0.0144 0.4693 0.6770
-2.500 -0.0029 0.03589 0.02642 -0.0142 0.4682 0.6816
-2.250 0.0085 0.03566 0.02613 -0.0131 0.4667 0.6919
-2.000 0.0339 0.03606 0.02658 -0.0127 0.4647 0.6945
-1.750 0.0582 0.03639 0.02693 -0.0124 0.4627 0.6974
-1.500 0.0808 0.03663 0.02716 -0.0120 0.4608 0.7009
-1.250 0.1013 0.03679 0.02729 -0.0116 0.4592 0.7053
-1.000 0.1194 0.03677 0.02720 -0.0113 0.4577 0.7104
-0.750 0.1404 0.03688 0.02726 -0.0111 0.4563 0.7137
-0.500 0.1638 0.03712 0.02747 -0.0108 0.4548 0.7158
-0.250 0.1875 0.03728 0.02758 -0.0107 0.4534 0.7178
0.000 0.2117 0.03738 0.02762 -0.0107 0.4521 0.7200
0.250 0.2365 0.03746 0.02761 -0.0107 0.4508 0.7227
0.500 0.2617 0.03752 0.02757 -0.0109 0.4497 0.7256
0.750 0.2873 0.03761 0.02755 -0.0114 0.4486 0.7282
1.000 0.2981 0.03856 0.02858 -0.0104 0.4464 0.7313
1.250 0.2973 0.04021 0.03043 -0.0084 0.4433 0.7338
1.500 0.2942 0.04199 0.03237 -0.0058 0.4399 0.7356
1.750 0.2981 0.04328 0.03374 -0.0040 0.4369 0.7375
2.000 0.3112 0.04404 0.03449 -0.0030 0.4348 0.7394
2.250 0.3287 0.04457 0.03499 -0.0025 0.4331 0.7410
2.500 0.3471 0.04511 0.03548 -0.0022 0.4317 0.7425
2.750 0.3680 0.04556 0.03588 -0.0021 0.4306 0.7442
3.000 0.3916 0.04592 0.03618 -0.0023 0.4296 0.7461
3.250 0.4173 0.04625 0.03643 -0.0027 0.4288 0.7479
5.750 0.2790 0.08435 0.07510 0.0023 0.3783 0.7605
6.000 0.3017 0.08511 0.07582 0.0019 0.3773 0.7615
6.250 0.3262 0.08568 0.07635 0.0014 0.3765 0.7625
6.750 0.3060 0.09352 0.08429 0.0006 0.3648 0.7644
7.000 0.3254 0.09462 0.08538 0.0001 0.3633 0.7654
7.250 0.3475 0.09544 0.08617 -0.0004 0.3621 0.7668
7.500 0.3719 0.09604 0.08674 -0.0008 0.3611 0.7683
8.000 0.3595 0.10330 0.09410 -0.0020 0.3504 0.7707
8.250 0.3781 0.10456 0.09534 -0.0026 0.3486 0.7719
8.500 0.4001 0.10543 0.09619 -0.0032 0.3472 0.7730
8.750 0.4242 0.10608 0.09681 -0.0037 0.3461 0.7741
9.250 0.4159 0.11301 0.10383 -0.0050 0.3358 0.7758
9.500 0.4337 0.11422 0.10506 -0.0055 0.3338 0.7769
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Polar data table (+)
Polar graphs
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