GOE 140 (MVA H.17) AIRFOIL (goe140-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 140 (MVA H.17) AIRFOIL (goe140-il) Reynolds number: 200,000 Max Cl/Cd: 74.01 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe140-il-200000-n5.txt Download as CSV file: xf-goe140-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 140 (MVA H.17) 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.2938 0.10092 0.09766 -0.0245 1.0000 0.0260
-8.000 -0.2942 0.09859 0.09539 -0.0263 1.0000 0.0262
-7.750 -0.2921 0.09587 0.09273 -0.0285 1.0000 0.0262
-7.500 -0.2882 0.09285 0.08977 -0.0303 1.0000 0.0263
-7.250 -0.2717 0.08859 0.08551 -0.0353 0.9941 0.0263
-7.000 -0.2461 0.08354 0.08042 -0.0425 0.9818 0.0264
-6.750 -0.2353 0.07814 0.07504 -0.0421 0.9721 0.0272
-6.500 -0.2163 0.07535 0.07224 -0.0428 0.9588 0.0289
-6.250 -0.1911 0.07191 0.06876 -0.0480 0.9412 0.0320
-6.000 -0.1434 0.06731 0.06395 -0.0637 0.9195 0.0356
-5.750 -0.1120 0.06296 0.05943 -0.0704 0.8996 0.0358
-5.500 -0.0823 0.05912 0.05540 -0.0751 0.8794 0.0360
-5.250 -0.0671 0.05368 0.04988 -0.0770 0.8608 0.0368
-5.000 -0.0500 0.05091 0.04704 -0.0772 0.8413 0.0376
-4.750 -0.0287 0.04839 0.04439 -0.0783 0.8224 0.0388
-4.500 -0.0038 0.04581 0.04163 -0.0802 0.8040 0.0404
-4.250 0.0434 0.04375 0.03898 -0.0859 0.7864 0.0472
-4.000 0.0720 0.04098 0.03591 -0.0875 0.7692 0.0473
-3.750 0.0996 0.03834 0.03299 -0.0887 0.7515 0.0473
-3.500 0.1272 0.03576 0.03015 -0.0898 0.7332 0.0473
-3.250 0.1516 0.03273 0.02697 -0.0907 0.7147 0.0468
-3.000 0.1757 0.03022 0.02435 -0.0916 0.6956 0.0452
-2.500 0.2360 0.02558 0.01900 -0.0933 0.6586 0.0401
-2.250 0.2678 0.02327 0.01621 -0.0940 0.6407 0.0387
-2.000 0.2980 0.02157 0.01412 -0.0943 0.6224 0.0384
-1.750 0.3273 0.02025 0.01244 -0.0945 0.6046 0.0384
-1.500 0.3552 0.01963 0.01160 -0.0947 0.5866 0.0398
-1.250 0.3837 0.01889 0.01061 -0.0948 0.5688 0.0411
-1.000 0.4128 0.01785 0.00925 -0.0949 0.5518 0.0407
-0.750 0.4417 0.01693 0.00804 -0.0948 0.5352 0.0404
-0.500 0.4700 0.01619 0.00705 -0.0948 0.5190 0.0405
-0.250 0.4981 0.01562 0.00629 -0.0947 0.5037 0.0408
0.000 0.5259 0.01517 0.00567 -0.0946 0.4895 0.0415
0.250 0.5537 0.01482 0.00519 -0.0946 0.4762 0.0425
0.500 0.5813 0.01454 0.00480 -0.0945 0.4643 0.0437
0.750 0.6091 0.01432 0.00451 -0.0945 0.4527 0.0451
1.000 0.6368 0.01422 0.00432 -0.0945 0.4420 0.0472
1.250 0.6643 0.01421 0.00430 -0.0945 0.4318 0.0509
1.500 0.6921 0.01418 0.00423 -0.0945 0.4220 0.0540
1.750 0.7199 0.01416 0.00414 -0.0945 0.4132 0.0578
2.000 0.7475 0.01420 0.00414 -0.0945 0.4050 0.0662
2.250 0.7752 0.01425 0.00415 -0.0945 0.3973 0.0803
2.500 0.8026 0.01433 0.00421 -0.0945 0.3901 0.0955
3.000 0.8505 0.01285 0.00449 -0.0931 0.3770 1.0000
3.250 0.8777 0.01308 0.00462 -0.0931 0.3710 1.0000
3.500 0.9050 0.01329 0.00477 -0.0930 0.3646 1.0000
3.750 0.9318 0.01356 0.00494 -0.0929 0.3588 1.0000
4.000 0.9590 0.01377 0.00515 -0.0928 0.3518 1.0000
4.250 0.9855 0.01403 0.00534 -0.0927 0.3452 1.0000
4.500 1.0124 0.01427 0.00557 -0.0926 0.3388 1.0000
4.750 1.0390 0.01452 0.00582 -0.0925 0.3327 1.0000
5.000 1.0652 0.01481 0.00607 -0.0923 0.3278 1.0000
5.250 1.0918 0.01504 0.00633 -0.0922 0.3205 1.0000
5.500 1.1175 0.01531 0.00658 -0.0920 0.3104 1.0000
5.750 1.1429 0.01560 0.00683 -0.0917 0.2994 1.0000
6.000 1.1689 0.01584 0.00711 -0.0916 0.2896 1.0000
6.250 1.1942 0.01614 0.00742 -0.0913 0.2795 1.0000
6.500 1.2190 0.01647 0.00772 -0.0910 0.2636 1.0000
6.750 1.2431 0.01686 0.00805 -0.0906 0.2449 1.0000
7.000 1.2656 0.01743 0.00846 -0.0901 0.2144 1.0000
7.250 1.2769 0.01936 0.00968 -0.0884 0.1115 1.0000
7.500 1.2937 0.02065 0.01081 -0.0871 0.0711 1.0000
7.750 1.3045 0.02252 0.01239 -0.0852 0.0201 1.0000
8.000 1.3235 0.02334 0.01332 -0.0841 0.0171 1.0000
8.250 1.3426 0.02410 0.01423 -0.0829 0.0162 1.0000
8.500 1.3601 0.02495 0.01524 -0.0816 0.0154 1.0000
8.750 1.3756 0.02592 0.01639 -0.0801 0.0147 1.0000
9.000 1.3881 0.02705 0.01768 -0.0782 0.0140 1.0000
9.250 1.3956 0.02844 0.01925 -0.0758 0.0132 1.0000
9.500 1.3945 0.03016 0.02117 -0.0723 0.0126 1.0000
9.750 1.3961 0.03183 0.02298 -0.0696 0.0122 1.0000
10.000 1.3988 0.03358 0.02489 -0.0675 0.0120 1.0000
10.250 1.3994 0.03571 0.02717 -0.0657 0.0117 1.0000
10.500 1.3982 0.03824 0.02986 -0.0645 0.0116 1.0000
10.750 1.3953 0.04121 0.03300 -0.0637 0.0114 1.0000
11.000 1.3909 0.04463 0.03657 -0.0635 0.0112 1.0000
11.250 1.3853 0.04842 0.04051 -0.0636 0.0111 1.0000
11.500 1.3787 0.05256 0.04478 -0.0641 0.0110 1.0000
11.750 1.3715 0.05687 0.04922 -0.0648 0.0109 1.0000
12.000 1.3639 0.06130 0.05377 -0.0655 0.0108 1.0000
12.250 1.3566 0.06569 0.05827 -0.0662 0.0107 1.0000
12.500 1.3499 0.06997 0.06265 -0.0667 0.0105 1.0000
12.750 1.3440 0.07410 0.06687 -0.0673 0.0103 1.0000
13.000 1.3392 0.07804 0.07088 -0.0677 0.0101 1.0000
13.250 1.3357 0.08177 0.07467 -0.0680 0.0098 1.0000
13.500 1.3335 0.08531 0.07826 -0.0683 0.0096 1.0000
13.750 1.3332 0.08837 0.08133 -0.0681 0.0093 1.0000
14.000 1.3380 0.08993 0.08279 -0.0663 0.0089 1.0000
14.250 1.3459 0.09138 0.08425 -0.0647 0.0088 1.0000
14.500 1.3494 0.09421 0.08720 -0.0647 0.0087 1.0000
14.750 1.3532 0.09699 0.09010 -0.0647 0.0085 1.0000
15.000 1.3573 0.09967 0.09289 -0.0646 0.0084 1.0000
15.250 1.3614 0.10239 0.09572 -0.0646 0.0083 1.0000
15.500 1.3651 0.10522 0.09868 -0.0646 0.0082 1.0000
15.750 1.3676 0.10831 0.10191 -0.0649 0.0082 1.0000
16.000 1.3689 0.11170 0.10544 -0.0655 0.0081 1.0000
16.250 1.3692 0.11529 0.10919 -0.0663 0.0080 1.0000
16.500 1.3685 0.11913 0.11319 -0.0674 0.0080 1.0000
16.750 1.3668 0.12324 0.11746 -0.0688 0.0080 1.0000
17.000 1.3641 0.12764 0.12203 -0.0705 0.0079 1.0000
17.250 1.3602 0.13238 0.12698 -0.0727 0.0079 1.0000
17.500 1.3552 0.13747 0.13225 -0.0753 0.0079 1.0000
17.750 1.3494 0.14286 0.13781 -0.0783 0.0078 1.0000
18.000 1.3429 0.14852 0.14365 -0.0816 0.0077 1.0000
18.250 1.3359 0.15445 0.14975 -0.0853 0.0077 1.0000
18.500 1.3282 0.16075 0.15623 -0.0894 0.0076 1.0000
18.750 1.3206 0.16723 0.16288 -0.0937 0.0076 1.0000
19.000 1.3122 0.17416 0.16998 -0.0985 0.0076 1.0000
19.250 1.3037 0.18138 0.17737 -0.1035 0.0075 1.0000
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