GOE 101 AIRFOIL (goe101-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 101 AIRFOIL (goe101-il) Reynolds number: 200,000 Max Cl/Cd: 77.17 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe101-il-200000-n5.txt Download as CSV file: xf-goe101-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 101 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
------ -------- --------- --------- -------- -------- --------
-8.000 -0.3515 0.09491 0.09151 -0.0204 1.0000 0.0210
-7.750 -0.3489 0.09221 0.08886 -0.0214 1.0000 0.0211
-7.500 -0.3486 0.08961 0.08632 -0.0223 1.0000 0.0211
-7.000 -0.3411 0.08356 0.08037 -0.0263 1.0000 0.0213
-6.750 -0.3342 0.08029 0.07713 -0.0287 1.0000 0.0213
-6.500 -0.3259 0.07692 0.07378 -0.0313 1.0000 0.0214
-6.250 -0.3164 0.07346 0.07031 -0.0338 1.0000 0.0215
-6.000 -0.3082 0.06991 0.06677 -0.0352 1.0000 0.0214
-5.750 -0.2967 0.06508 0.06197 -0.0357 0.9938 0.0192
-5.500 -0.2640 0.05910 0.05590 -0.0441 0.9843 0.0170
-5.250 -0.2266 0.05255 0.04919 -0.0530 0.9746 0.0158
-5.000 -0.1899 0.04689 0.04334 -0.0600 0.9645 0.0157
-4.750 -0.1551 0.04271 0.03899 -0.0649 0.9540 0.0168
-4.500 -0.1184 0.03831 0.03432 -0.0695 0.9423 0.0189
-4.250 -0.0825 0.03333 0.02898 -0.0731 0.9297 0.0193
-4.000 -0.0472 0.02838 0.02351 -0.0755 0.9160 0.0203
-3.750 -0.0158 0.02545 0.02017 -0.0769 0.9006 0.0234
-3.500 0.0141 0.02345 0.01788 -0.0778 0.8834 0.0251
-3.250 0.0435 0.02128 0.01528 -0.0780 0.8637 0.0273
-3.000 0.0731 0.01960 0.01308 -0.0777 0.8425 0.0307
-2.750 0.1009 0.01808 0.01105 -0.0773 0.8199 0.0321
-2.250 0.1530 0.01593 0.00840 -0.0765 0.7749 0.0370
-1.750 0.2059 0.01443 0.00633 -0.0753 0.7329 0.0389
-1.500 0.2320 0.01403 0.00571 -0.0747 0.7127 0.0408
-1.250 0.2582 0.01364 0.00513 -0.0742 0.6937 0.0417
-1.000 0.2843 0.01315 0.00451 -0.0737 0.6755 0.0415
-0.750 0.3103 0.01275 0.00398 -0.0732 0.6584 0.0414
-0.500 0.3363 0.01242 0.00356 -0.0727 0.6418 0.0413
-0.250 0.3624 0.01217 0.00321 -0.0722 0.6256 0.0414
0.000 0.3885 0.01198 0.00292 -0.0718 0.6100 0.0416
0.250 0.4148 0.01185 0.00269 -0.0714 0.5955 0.0421
0.500 0.4413 0.01178 0.00250 -0.0711 0.5823 0.0428
0.750 0.4679 0.01171 0.00234 -0.0708 0.5706 0.0449
1.000 0.4945 0.01169 0.00225 -0.0705 0.5598 0.0495
1.500 0.5527 0.00961 0.00235 -0.0713 0.5395 1.0000
1.750 0.5791 0.00977 0.00238 -0.0709 0.5305 1.0000
2.000 0.6055 0.00994 0.00244 -0.0706 0.5213 1.0000
2.250 0.6319 0.01010 0.00252 -0.0703 0.5109 1.0000
2.500 0.6580 0.01028 0.00262 -0.0699 0.4998 1.0000
2.750 0.6841 0.01047 0.00272 -0.0695 0.4889 1.0000
3.000 0.7103 0.01063 0.00285 -0.0692 0.4778 1.0000
3.250 0.7366 0.01081 0.00301 -0.0689 0.4684 1.0000
3.500 0.7627 0.01101 0.00317 -0.0686 0.4597 1.0000
3.750 0.7890 0.01117 0.00335 -0.0683 0.4500 1.0000
4.000 0.8152 0.01136 0.00355 -0.0680 0.4425 1.0000
4.250 0.8415 0.01154 0.00379 -0.0677 0.4346 1.0000
4.500 0.8676 0.01173 0.00402 -0.0674 0.4258 1.0000
5.000 0.9192 0.01213 0.00451 -0.0666 0.4037 1.0000
5.250 0.9451 0.01233 0.00482 -0.0663 0.3930 1.0000
5.500 0.9700 0.01257 0.00507 -0.0658 0.3722 1.0000
5.750 0.9934 0.01289 0.00530 -0.0651 0.3250 1.0000
6.000 1.0130 0.01371 0.00571 -0.0640 0.2437 1.0000
6.250 1.0320 0.01475 0.00645 -0.0630 0.1840 1.0000
6.500 1.0501 0.01593 0.00727 -0.0620 0.1136 1.0000
6.750 1.0671 0.01724 0.00827 -0.0607 0.0569 1.0000
7.000 1.0828 0.01873 0.00950 -0.0592 0.0210 1.0000
7.250 1.1035 0.01955 0.01049 -0.0581 0.0181 1.0000
7.500 1.1230 0.02049 0.01164 -0.0569 0.0159 1.0000
7.750 1.1392 0.02177 0.01309 -0.0554 0.0133 1.0000
8.000 1.1511 0.02342 0.01495 -0.0533 0.0121 1.0000
8.250 1.1661 0.02463 0.01631 -0.0516 0.0116 1.0000
8.500 1.1792 0.02601 0.01783 -0.0497 0.0112 1.0000
8.750 1.1910 0.02750 0.01945 -0.0477 0.0107 1.0000
9.000 1.2029 0.02894 0.02101 -0.0458 0.0100 1.0000
9.250 1.2146 0.03033 0.02251 -0.0440 0.0093 1.0000
9.500 1.2236 0.03171 0.02397 -0.0419 0.0085 1.0000
9.750 1.2302 0.03348 0.02584 -0.0396 0.0082 1.0000
10.000 1.2370 0.03552 0.02802 -0.0376 0.0080 1.0000
10.250 1.2446 0.03809 0.03072 -0.0357 0.0077 1.0000
10.500 1.2526 0.04113 0.03393 -0.0341 0.0075 1.0000
10.750 1.2576 0.04346 0.03649 -0.0323 0.0075 1.0000
11.000 1.2596 0.04594 0.03922 -0.0305 0.0074 1.0000
11.250 1.2590 0.04874 0.04228 -0.0290 0.0073 1.0000
11.500 1.2559 0.05183 0.04563 -0.0278 0.0072 1.0000
11.750 1.2505 0.05525 0.04930 -0.0271 0.0072 1.0000
12.000 1.2424 0.05906 0.05336 -0.0269 0.0072 1.0000
12.250 1.2329 0.06323 0.05778 -0.0273 0.0072 1.0000
12.500 1.2220 0.06781 0.06259 -0.0283 0.0071 1.0000
12.750 1.2098 0.07283 0.06783 -0.0300 0.0072 1.0000
13.000 1.1961 0.07834 0.07356 -0.0323 0.0071 1.0000
13.250 1.1826 0.08415 0.07956 -0.0350 0.0072 1.0000
13.500 1.1674 0.09057 0.08618 -0.0384 0.0071 1.0000
13.750 1.1522 0.09732 0.09310 -0.0421 0.0072 1.0000
14.000 1.1373 0.10444 0.10038 -0.0463 0.0072 1.0000
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Polar data table (+)
Polar graphs
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