GOE 155 (SSW D.1) AIRFOIL (goe155-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 155 (SSW D.1) AIRFOIL (goe155-il) Reynolds number: 200,000 Max Cl/Cd: 78.57 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe155-il-200000-n5.txt Download as CSV file: xf-goe155-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 155 (SSW D.1) 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
------ -------- --------- --------- -------- -------- --------
-9.000 -0.3266 0.10962 0.10629 -0.0204 1.0000 0.0200
-8.750 -0.3209 0.10687 0.10358 -0.0235 1.0000 0.0201
-8.500 -0.3154 0.10402 0.10077 -0.0265 1.0000 0.0202
-8.000 -0.2950 0.09701 0.09380 -0.0340 0.9762 0.0203
-7.750 -0.2789 0.09286 0.08965 -0.0389 0.9635 0.0203
-7.500 -0.2634 0.08885 0.08561 -0.0432 0.9514 0.0203
-7.250 -0.2541 0.08478 0.08155 -0.0431 0.9413 0.0205
-7.000 -0.2442 0.08175 0.07850 -0.0420 0.9321 0.0211
-6.750 -0.2320 0.07879 0.07551 -0.0439 0.9215 0.0217
-6.500 -0.2177 0.07592 0.07261 -0.0465 0.9105 0.0232
-6.250 -0.1877 0.07215 0.06876 -0.0573 0.8990 0.0261
-6.000 -0.1642 0.06807 0.06459 -0.0628 0.8906 0.0262
-5.750 -0.1404 0.06387 0.06030 -0.0676 0.8817 0.0263
-5.500 -0.0905 0.04235 0.03885 -0.0686 0.8506 0.0264
-5.250 -0.0865 0.03938 0.03593 -0.0653 0.8444 0.0278
-5.000 -0.0679 0.03669 0.03317 -0.0670 0.8371 0.0311
-4.750 -0.0257 0.03164 0.02778 -0.0770 0.8317 0.0342
-4.500 -0.0039 0.02679 0.02279 -0.0799 0.8243 0.0346
-4.250 0.0104 0.02424 0.02021 -0.0794 0.8167 0.0359
-4.000 0.0315 0.02235 0.01824 -0.0801 0.8074 0.0397
-3.750 0.0623 0.01879 0.01440 -0.0836 0.8007 0.0454
-3.250 0.1207 0.03056 0.02534 -0.0919 0.8058 0.0390
-3.000 0.1516 0.02780 0.02225 -0.0931 0.7983 0.0407
-2.750 0.1858 0.02310 0.01688 -0.0943 0.7922 0.0360
-2.500 0.2160 0.02056 0.01379 -0.0946 0.7868 0.0355
-2.250 0.2434 0.01970 0.01284 -0.0950 0.7798 0.0372
-2.000 0.2720 0.01836 0.01116 -0.0950 0.7741 0.0377
-1.750 0.3014 0.01691 0.00932 -0.0951 0.7676 0.0370
-1.500 0.3298 0.01591 0.00804 -0.0950 0.7612 0.0369
-1.250 0.3580 0.01515 0.00707 -0.0949 0.7551 0.0371
-1.000 0.3862 0.01452 0.00629 -0.0949 0.7480 0.0375
-0.750 0.4139 0.01400 0.00564 -0.0947 0.7412 0.0380
-0.500 0.4417 0.01359 0.00517 -0.0946 0.7323 0.0393
-0.250 0.4693 0.01326 0.00476 -0.0944 0.7232 0.0410
0.000 0.4966 0.01291 0.00434 -0.0941 0.7132 0.0413
0.250 0.5242 0.01261 0.00401 -0.0940 0.7017 0.0414
0.500 0.5518 0.01238 0.00374 -0.0938 0.6901 0.0417
0.750 0.5793 0.01221 0.00351 -0.0937 0.6776 0.0421
1.000 0.6068 0.01209 0.00332 -0.0935 0.6647 0.0427
1.250 0.6343 0.01201 0.00318 -0.0934 0.6519 0.0436
1.500 0.6619 0.01194 0.00309 -0.0932 0.6382 0.0458
1.750 0.6893 0.01190 0.00304 -0.0931 0.6230 0.0500
2.000 0.7167 0.01188 0.00304 -0.0930 0.6063 0.0683
2.250 0.7439 0.01178 0.00310 -0.0929 0.5882 0.1603
2.500 0.7704 0.01027 0.00318 -0.0928 0.5686 1.0000
2.750 0.7969 0.01047 0.00323 -0.0925 0.5476 1.0000
3.000 0.8233 0.01069 0.00331 -0.0922 0.5258 1.0000
3.250 0.8494 0.01095 0.00343 -0.0919 0.5042 1.0000
3.500 0.8754 0.01123 0.00358 -0.0917 0.4834 1.0000
3.750 0.9012 0.01153 0.00378 -0.0914 0.4642 1.0000
4.000 0.9270 0.01185 0.00400 -0.0911 0.4471 1.0000
4.250 0.9528 0.01216 0.00424 -0.0909 0.4317 1.0000
4.500 0.9785 0.01246 0.00452 -0.0906 0.4174 1.0000
4.750 1.0041 0.01278 0.00481 -0.0903 0.4029 1.0000
5.000 1.0291 0.01316 0.00512 -0.0900 0.3846 1.0000
5.250 1.0540 0.01352 0.00546 -0.0897 0.3639 1.0000
5.500 1.0788 0.01389 0.00580 -0.0893 0.3450 1.0000
5.750 1.1036 0.01425 0.00616 -0.0890 0.3298 1.0000
6.000 1.1280 0.01464 0.00655 -0.0886 0.3136 1.0000
6.250 1.1512 0.01513 0.00699 -0.0880 0.2913 1.0000
6.500 1.1731 0.01575 0.00747 -0.0874 0.2642 1.0000
6.750 1.1949 0.01637 0.00801 -0.0867 0.2393 1.0000
7.000 1.2162 0.01703 0.00859 -0.0860 0.2137 1.0000
7.250 1.2351 0.01795 0.00928 -0.0850 0.1612 1.0000
7.500 1.2390 0.02060 0.01113 -0.0824 0.0430 1.0000
7.750 1.2568 0.02161 0.01218 -0.0811 0.0330 1.0000
8.000 1.2723 0.02280 0.01350 -0.0795 0.0274 1.0000
8.250 1.2904 0.02361 0.01445 -0.0783 0.0243 1.0000
8.500 1.3057 0.02461 0.01559 -0.0767 0.0215 1.0000
8.750 1.3168 0.02587 0.01700 -0.0747 0.0197 1.0000
9.000 1.3172 0.02767 0.01893 -0.0713 0.0182 1.0000
9.250 1.3262 0.02880 0.02020 -0.0691 0.0172 1.0000
9.500 1.3336 0.03013 0.02165 -0.0669 0.0160 1.0000
9.750 1.3389 0.03171 0.02335 -0.0647 0.0150 1.0000
10.000 1.3428 0.03350 0.02526 -0.0627 0.0143 1.0000
10.250 1.3462 0.03543 0.02729 -0.0608 0.0138 1.0000
10.500 1.3490 0.03751 0.02946 -0.0591 0.0132 1.0000
10.750 1.3505 0.03980 0.03185 -0.0574 0.0128 1.0000
11.000 1.3498 0.04243 0.03459 -0.0557 0.0123 1.0000
11.250 1.3507 0.04504 0.03730 -0.0540 0.0118 1.0000
11.500 1.3569 0.04708 0.03950 -0.0529 0.0113 1.0000
11.750 1.3618 0.04930 0.04187 -0.0517 0.0107 1.0000
12.000 1.3658 0.05171 0.04443 -0.0505 0.0103 1.0000
12.250 1.3695 0.05425 0.04712 -0.0493 0.0100 1.0000
12.500 1.3724 0.05692 0.04994 -0.0482 0.0097 1.0000
12.750 1.3742 0.05974 0.05293 -0.0473 0.0094 1.0000
13.000 1.3749 0.06275 0.05612 -0.0465 0.0092 1.0000
13.250 1.3740 0.06597 0.05951 -0.0460 0.0090 1.0000
13.500 1.3715 0.06944 0.06318 -0.0456 0.0089 1.0000
13.750 1.3675 0.07317 0.06709 -0.0455 0.0088 1.0000
14.000 1.3618 0.07718 0.07129 -0.0457 0.0087 1.0000
14.250 1.3548 0.08149 0.07578 -0.0462 0.0086 1.0000
14.500 1.3468 0.08609 0.08056 -0.0471 0.0085 1.0000
14.750 1.3376 0.09103 0.08568 -0.0483 0.0084 1.0000
15.000 1.3268 0.09643 0.09126 -0.0500 0.0083 1.0000
15.250 1.3143 0.10235 0.09736 -0.0521 0.0082 1.0000
15.750 1.2866 0.11556 0.11097 -0.0582 0.0081 1.0000
16.000 1.2726 0.12270 0.11831 -0.0621 0.0081 1.0000
16.250 1.2587 0.13017 0.12597 -0.0664 0.0080 1.0000
16.500 1.2447 0.13797 0.13396 -0.0711 0.0080 1.0000
16.750 1.2312 0.14605 0.14219 -0.0761 0.0081 1.0000
17.000 1.2176 0.15457 0.15087 -0.0816 0.0081 1.0000
17.250 1.2046 0.16352 0.15999 -0.0875 0.0081 1.0000
17.500 1.1822 0.17721 0.17390 -0.0965 0.0084 1.0000
17.750 0.8735 0.16893 0.16593 -0.0699 0.0106 1.0000
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