GOE 601 AIRFOIL (goe601-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 601 AIRFOIL (goe601-il) Reynolds number: 200,000 Max Cl/Cd: 69.85 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe601-il-200000.txt Download as CSV file: xf-goe601-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 601 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
------ -------- --------- --------- -------- -------- --------
-14.500 -0.5895 0.09504 0.09091 -0.0707 1.0000 0.0543
-14.250 -0.6383 0.08309 0.07890 -0.0770 1.0000 0.0533
-14.000 -0.7040 0.07084 0.06644 -0.0840 1.0000 0.0522
-13.750 -0.7542 0.06282 0.05820 -0.0874 1.0000 0.0516
-13.500 -0.7955 0.05709 0.05225 -0.0882 1.0000 0.0511
-13.250 -0.8310 0.05283 0.04778 -0.0871 1.0000 0.0508
-13.000 -0.8582 0.04995 0.04474 -0.0844 1.0000 0.0509
-12.750 -0.8838 0.04772 0.04236 -0.0806 1.0000 0.0509
-12.500 -0.9092 0.04600 0.04051 -0.0755 1.0000 0.0510
-12.250 -0.9375 0.04476 0.03916 -0.0690 1.0000 0.0510
-12.000 -0.9670 0.04402 0.03834 -0.0614 1.0000 0.0510
-11.750 -0.9884 0.04297 0.03717 -0.0553 1.0000 0.0512
-11.500 -0.9752 0.04054 0.03443 -0.0558 0.9956 0.0520
-11.250 -0.9563 0.03819 0.03174 -0.0568 0.9902 0.0530
-11.000 -0.9357 0.03636 0.02952 -0.0577 0.9846 0.0542
-10.750 -0.9076 0.03410 0.02712 -0.0595 0.9818 0.0555
-10.500 -0.8838 0.03277 0.02576 -0.0599 0.9760 0.0566
-10.250 -0.8539 0.03151 0.02440 -0.0615 0.9720 0.0581
-10.000 -0.8213 0.03034 0.02307 -0.0634 0.9694 0.0600
-9.750 -0.8032 0.02936 0.02191 -0.0624 0.9622 0.0614
-9.500 -0.7731 0.02800 0.02044 -0.0637 0.9587 0.0630
-9.250 -0.7388 0.02695 0.01944 -0.0657 0.9562 0.0650
-9.000 -0.7199 0.02628 0.01873 -0.0646 0.9495 0.0670
-8.750 -0.6924 0.02554 0.01788 -0.0651 0.9450 0.0696
-8.500 -0.6603 0.02453 0.01685 -0.0666 0.9422 0.0724
-8.250 -0.6249 0.02381 0.01615 -0.0687 0.9401 0.0761
-8.000 -0.6155 0.02341 0.01568 -0.0655 0.9311 0.0789
-7.750 -0.5856 0.02269 0.01498 -0.0664 0.9278 0.0838
-7.500 -0.5502 0.02217 0.01437 -0.0682 0.9255 0.0915
-7.250 -0.5402 0.02163 0.01392 -0.0652 0.9176 0.0982
-7.000 -0.5158 0.02086 0.01317 -0.0651 0.9133 0.1118
-6.750 -0.4856 0.02001 0.01234 -0.0661 0.9106 0.1289
-6.500 -0.4512 0.01923 0.01159 -0.0678 0.9089 0.1446
-6.250 -0.4482 0.01904 0.01141 -0.0633 0.8993 0.1523
-6.000 -0.4173 0.01849 0.01090 -0.0642 0.8963 0.1655
-5.750 -0.3824 0.01789 0.01038 -0.0659 0.8944 0.1821
-5.500 -0.3462 0.01728 0.00990 -0.0679 0.8929 0.2088
-5.250 -0.3453 0.01720 0.00994 -0.0628 0.8830 0.2319
-5.000 -0.3149 0.01664 0.00959 -0.0636 0.8802 0.2858
-4.750 -0.2817 0.01610 0.00923 -0.0648 0.8781 0.3339
-4.500 -0.2475 0.01566 0.00893 -0.0661 0.8765 0.3773
-4.250 -0.2449 0.01583 0.00919 -0.0613 0.8667 0.4009
-4.000 -0.2126 0.01563 0.00904 -0.0620 0.8639 0.4347
-3.750 -0.1771 0.01544 0.00884 -0.0633 0.8619 0.4612
-3.500 -0.1399 0.01523 0.00859 -0.0650 0.8602 0.4835
-3.250 -0.1344 0.01550 0.00888 -0.0607 0.8508 0.4982
-3.000 -0.1023 0.01533 0.00869 -0.0613 0.8477 0.5179
-2.750 -0.0672 0.01511 0.00848 -0.0625 0.8455 0.5374
-2.500 -0.0299 0.01486 0.00825 -0.0642 0.8436 0.5563
-2.250 -0.0219 0.01507 0.00852 -0.0603 0.8343 0.5692
-2.000 0.0132 0.01479 0.00826 -0.0614 0.8306 0.5850
-1.750 0.0540 0.01441 0.00788 -0.0635 0.8276 0.6023
-1.500 0.0718 0.01446 0.00798 -0.0614 0.8198 0.6166
-1.250 0.1021 0.01428 0.00781 -0.0615 0.8143 0.6321
-1.000 0.1387 0.01404 0.00757 -0.0629 0.8108 0.6480
-0.500 0.1861 0.01397 0.00758 -0.0608 0.7974 0.6801
-0.250 0.2206 0.01376 0.00739 -0.0618 0.7932 0.6996
0.000 0.2424 0.01375 0.00746 -0.0603 0.7862 0.7176
0.250 0.2682 0.01363 0.00741 -0.0596 0.7793 0.7368
0.500 0.3040 0.01339 0.00723 -0.0607 0.7747 0.7587
0.750 0.3226 0.01339 0.00736 -0.0585 0.7663 0.7823
1.000 0.3534 0.01320 0.00723 -0.0586 0.7596 0.8100
1.250 0.3883 0.01309 0.00719 -0.0595 0.7536 0.8365
1.500 0.4151 0.01311 0.00731 -0.0589 0.7455 0.8655
1.750 0.4625 0.01305 0.00726 -0.0622 0.7400 0.8890
2.000 0.5017 0.01316 0.00743 -0.0642 0.7316 0.9112
2.250 0.5501 0.01316 0.00740 -0.0678 0.7241 0.9271
2.500 0.5947 0.01323 0.00748 -0.0709 0.7153 0.9402
2.750 0.6402 0.01318 0.00740 -0.0742 0.7062 0.9509
3.000 0.6860 0.01318 0.00742 -0.0777 0.6946 0.9592
3.250 0.7298 0.01312 0.00734 -0.0808 0.6834 0.9696
3.500 0.7764 0.01303 0.00722 -0.0845 0.6701 0.9782
3.750 0.8206 0.01295 0.00713 -0.0878 0.6526 0.9870
4.000 0.8642 0.01287 0.00706 -0.0912 0.6307 0.9960
4.250 0.8917 0.01281 0.00692 -0.0914 0.6068 1.0000
4.500 0.8976 0.01285 0.00686 -0.0872 0.5811 1.0000
4.750 0.9012 0.01299 0.00683 -0.0825 0.5484 1.0000
5.000 0.9014 0.01325 0.00689 -0.0772 0.5104 1.0000
5.250 0.8986 0.01364 0.00703 -0.0713 0.4719 1.0000
5.500 0.8965 0.01408 0.00724 -0.0655 0.4397 1.0000
5.750 0.8962 0.01454 0.00750 -0.0602 0.4144 1.0000
6.000 0.8977 0.01496 0.00777 -0.0552 0.3958 1.0000
6.250 0.9011 0.01538 0.00805 -0.0506 0.3806 1.0000
6.500 0.9082 0.01583 0.00837 -0.0468 0.3684 1.0000
6.750 0.9187 0.01623 0.00872 -0.0437 0.3570 1.0000
7.000 0.9308 0.01666 0.00909 -0.0409 0.3467 1.0000
7.250 0.9442 0.01713 0.00947 -0.0385 0.3373 1.0000
7.500 0.9589 0.01753 0.00989 -0.0362 0.3288 1.0000
7.750 0.9743 0.01800 0.01029 -0.0342 0.3206 1.0000
8.000 0.9895 0.01842 0.01073 -0.0322 0.3128 1.0000
8.250 1.0038 0.01886 0.01116 -0.0300 0.3047 1.0000
8.500 1.0202 0.01931 0.01162 -0.0282 0.2977 1.0000
8.750 1.0332 0.01972 0.01207 -0.0259 0.2901 1.0000
9.000 1.0480 0.02022 0.01254 -0.0240 0.2825 1.0000
9.250 1.0584 0.02062 0.01305 -0.0214 0.2742 1.0000
9.500 1.0679 0.02115 0.01356 -0.0188 0.2647 1.0000
9.750 1.0765 0.02164 0.01412 -0.0161 0.2545 1.0000
10.000 1.0868 0.02218 0.01473 -0.0138 0.2446 1.0000
10.250 1.0948 0.02285 0.01540 -0.0113 0.2332 1.0000
10.500 1.1022 0.02357 0.01617 -0.0089 0.2170 1.0000
10.750 1.1069 0.02454 0.01710 -0.0064 0.1903 1.0000
11.000 1.1039 0.02618 0.01846 -0.0034 0.1402 1.0000
11.250 1.0910 0.02873 0.02054 0.0002 0.0878 1.0000
11.500 1.0888 0.03071 0.02241 0.0027 0.0741 1.0000
11.750 1.0903 0.03248 0.02417 0.0047 0.0682 1.0000
12.000 1.0926 0.03423 0.02597 0.0065 0.0648 1.0000
12.250 1.0962 0.03592 0.02775 0.0081 0.0623 1.0000
12.500 1.0974 0.03787 0.02975 0.0096 0.0602 1.0000
12.750 1.0955 0.04014 0.03205 0.0111 0.0585 1.0000
13.000 1.0957 0.04230 0.03427 0.0124 0.0571 1.0000
13.250 1.0993 0.04425 0.03631 0.0135 0.0559 1.0000
13.500 1.1022 0.04632 0.03845 0.0144 0.0546 1.0000
13.750 1.1048 0.04845 0.04064 0.0152 0.0534 1.0000
14.000 1.1074 0.05063 0.04285 0.0160 0.0524 1.0000
14.250 1.1104 0.05277 0.04500 0.0168 0.0515 1.0000
14.500 1.1156 0.05469 0.04688 0.0178 0.0505 1.0000
14.750 1.1231 0.05648 0.04873 0.0185 0.0496 1.0000
15.000 1.1312 0.05825 0.05059 0.0191 0.0488 1.0000
15.250 1.1397 0.05999 0.05241 0.0197 0.0480 1.0000
15.500 1.1479 0.06180 0.05427 0.0202 0.0469 1.0000
15.750 1.1583 0.06338 0.05589 0.0208 0.0461 1.0000
16.000 1.1699 0.06484 0.05737 0.0214 0.0453 1.0000
16.250 1.1840 0.06608 0.05861 0.0222 0.0446 1.0000
16.500 1.2088 0.06662 0.05909 0.0235 0.0433 1.0000
16.750 1.2130 0.06894 0.06157 0.0237 0.0430 1.0000
17.000 1.2146 0.07161 0.06442 0.0238 0.0425 1.0000
17.250 1.2156 0.07438 0.06735 0.0238 0.0420 1.0000
17.500 1.2171 0.07720 0.07034 0.0237 0.0415 1.0000
17.750 1.2184 0.08012 0.07343 0.0236 0.0412 1.0000
18.000 1.2166 0.08341 0.07688 0.0233 0.0407 1.0000
18.250 1.2140 0.08688 0.08051 0.0227 0.0404 1.0000
18.500 1.2105 0.09046 0.08424 0.0219 0.0400 1.0000
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