GOE 376 AIRFOIL (goe376-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
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Airfoil: GOE 376 AIRFOIL (goe376-il) Reynolds number: 1,000,000 Max Cl/Cd: 121.75 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe376-il-1000000.txt Download as CSV file: xf-goe376-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 376 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.2453 0.08595 0.08449 -0.0225 1.0000 0.0116
-8.250 -0.2461 0.08274 0.08129 -0.0231 1.0000 0.0124
-8.000 -0.2480 0.07991 0.07849 -0.0231 1.0000 0.0124
-7.750 -0.2504 0.07702 0.07563 -0.0233 0.9998 0.0125
-7.500 -0.2380 0.07238 0.07098 -0.0284 0.9975 0.0125
-7.250 -0.2257 0.06780 0.06640 -0.0334 0.9932 0.0125
-6.500 -0.2500 0.07088 0.06938 -0.0409 0.9886 0.0128
-6.250 -0.2227 0.06722 0.06571 -0.0464 0.9848 0.0130
-6.000 -0.1994 0.06422 0.06269 -0.0505 0.9766 0.0135
0.000 0.4690 0.01237 0.00655 -0.0832 0.5756 0.0301
0.250 0.4921 0.01081 0.00475 -0.0822 0.5533 0.0314
0.500 0.5166 0.01042 0.00427 -0.0815 0.5282 0.0324
0.750 0.5415 0.01019 0.00394 -0.0809 0.5060 0.0339
1.000 0.5668 0.01006 0.00370 -0.0802 0.4864 0.0356
1.250 0.5927 0.01045 0.00398 -0.0797 0.4692 0.0377
2.500 0.7173 0.00897 0.00222 -0.0761 0.4071 0.0355
2.750 0.7425 0.00882 0.00204 -0.0754 0.3978 0.0338
3.000 0.7679 0.00879 0.00198 -0.0748 0.3894 0.0341
3.250 0.7935 0.00879 0.00195 -0.0743 0.3804 0.0343
3.500 0.8192 0.00880 0.00195 -0.0738 0.3714 0.0348
3.750 0.8446 0.00886 0.00198 -0.0732 0.3613 0.0357
4.000 0.8702 0.00892 0.00201 -0.0727 0.3502 0.0358
4.250 0.8957 0.00900 0.00207 -0.0722 0.3382 0.0359
4.500 0.9207 0.00914 0.00214 -0.0717 0.3213 0.0367
4.750 0.9450 0.00934 0.00224 -0.0710 0.2988 0.0388
5.000 1.0178 0.00836 0.00282 -0.0824 0.2545 1.0000
5.250 1.0407 0.00867 0.00302 -0.0815 0.2353 1.0000
5.500 1.0640 0.00895 0.00321 -0.0806 0.2203 1.0000
5.750 1.0876 0.00920 0.00341 -0.0798 0.2075 1.0000
6.000 1.1108 0.00948 0.00363 -0.0790 0.1930 1.0000
6.250 1.1335 0.00980 0.00387 -0.0781 0.1765 1.0000
6.500 1.1559 0.01015 0.00412 -0.0771 0.1572 1.0000
6.750 1.1758 0.01071 0.00449 -0.0758 0.1256 1.0000
7.000 1.1922 0.01158 0.00505 -0.0739 0.0798 1.0000
7.250 1.2027 0.01301 0.00610 -0.0710 0.0176 1.0000
7.500 1.2243 0.01341 0.00655 -0.0699 0.0153 1.0000
7.750 1.2452 0.01389 0.00707 -0.0687 0.0136 1.0000
8.000 1.2649 0.01445 0.00772 -0.0672 0.0123 1.0000
8.250 1.2859 0.01487 0.00819 -0.0661 0.0119 1.0000
8.500 1.3060 0.01537 0.00874 -0.0648 0.0113 1.0000
8.750 1.3254 0.01590 0.00932 -0.0634 0.0106 1.0000
9.000 1.3439 0.01649 0.00996 -0.0619 0.0100 1.0000
9.250 1.3606 0.01720 0.01074 -0.0601 0.0096 1.0000
9.500 1.3670 0.01868 0.01240 -0.0567 0.0088 1.0000
9.750 1.3835 0.01930 0.01307 -0.0549 0.0087 1.0000
10.000 1.3985 0.01997 0.01381 -0.0530 0.0085 1.0000
10.250 1.4119 0.02072 0.01463 -0.0508 0.0082 1.0000
10.500 1.4215 0.02150 0.01548 -0.0479 0.0080 1.0000
10.750 1.4299 0.02228 0.01633 -0.0449 0.0077 1.0000
11.000 1.4352 0.02329 0.01743 -0.0417 0.0075 1.0000
11.250 1.4420 0.02429 0.01850 -0.0390 0.0073 1.0000
11.500 1.4477 0.02541 0.01970 -0.0364 0.0071 1.0000
11.750 1.4506 0.02680 0.02118 -0.0337 0.0070 1.0000
12.000 1.4587 0.02791 0.02234 -0.0320 0.0067 1.0000
12.250 1.4591 0.02970 0.02421 -0.0299 0.0065 1.0000
12.500 1.4518 0.03234 0.02695 -0.0278 0.0063 1.0000
12.750 1.4435 0.03536 0.03008 -0.0261 0.0062 1.0000
13.000 1.4266 0.03953 0.03437 -0.0243 0.0061 1.0000
13.250 1.4271 0.04208 0.03701 -0.0238 0.0060 1.0000
13.500 1.4317 0.04435 0.03941 -0.0238 0.0059 1.0000
13.750 1.4336 0.04697 0.04214 -0.0239 0.0058 1.0000
14.000 1.4310 0.05015 0.04542 -0.0239 0.0058 1.0000
14.250 1.4269 0.05359 0.04898 -0.0241 0.0057 1.0000
14.500 1.4245 0.05698 0.05247 -0.0246 0.0056 1.0000
14.750 1.4188 0.06082 0.05642 -0.0251 0.0056 1.0000
15.000 1.4131 0.06474 0.06045 -0.0258 0.0056 1.0000
15.250 1.4080 0.06880 0.06463 -0.0269 0.0054 1.0000
15.500 1.4001 0.07318 0.06913 -0.0277 0.0055 1.0000
15.750 1.3929 0.07767 0.07373 -0.0289 0.0054 1.0000
16.000 1.3856 0.08233 0.07850 -0.0304 0.0054 1.0000
16.250 1.3781 0.08717 0.08346 -0.0322 0.0053 1.0000
16.500 1.3681 0.09235 0.08876 -0.0339 0.0052 1.0000
16.750 1.3586 0.09755 0.09408 -0.0357 0.0053 1.0000
17.000 1.3478 0.10315 0.09980 -0.0379 0.0052 1.0000
17.250 1.3380 0.10873 0.10549 -0.0403 0.0052 1.0000
17.500 1.3290 0.11435 0.11122 -0.0430 0.0050 1.0000
17.750 1.3151 0.12079 0.11780 -0.0458 0.0051 1.0000
18.000 1.3036 0.12707 0.12419 -0.0488 0.0051 1.0000
18.250 1.2931 0.13329 0.13053 -0.0520 0.0051 1.0000
18.500 1.2825 0.13975 0.13709 -0.0555 0.0050 1.0000
18.750 1.2677 0.14720 0.14468 -0.0595 0.0050 1.0000
19.000 1.2533 0.15492 0.15254 -0.0639 0.0051 1.0000
19.250 1.2446 0.16157 0.15927 -0.0679 0.0050 1.0000
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Polar data table (+)
Polar graphs
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