GOE 167 (V.KARMAN PROP.2) AIRFOIL (goe167-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 167 (V.KARMAN PROP.2) AIRFOIL (goe167-il) Reynolds number: 1,000,000 Max Cl/Cd: 124.29 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe167-il-1000000.txt Download as CSV file: xf-goe167-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 167 (V.KARMAN PROP.2) 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
------ -------- --------- --------- -------- -------- --------
-8.250 -0.3752 0.09064 0.08907 -0.0172 0.9175 0.0152
-8.000 -0.3741 0.08814 0.08631 -0.0173 0.8442 0.0155
-7.750 -0.3703 0.08514 0.08312 -0.0191 0.8008 0.0161
-7.250 -0.3462 0.07349 0.07123 -0.0364 0.7481 0.0178
-7.000 -0.3295 0.06790 0.06550 -0.0428 0.7233 0.0178
-6.750 -0.3176 0.05988 0.05732 -0.0499 0.7023 0.0181
-6.500 -0.3004 0.05755 0.05485 -0.0514 0.6743 0.0184
-6.250 -0.2808 0.05524 0.05239 -0.0532 0.6496 0.0187
-6.000 -0.2593 0.05255 0.04957 -0.0555 0.6291 0.0192
-5.750 -0.2356 0.04941 0.04627 -0.0583 0.6130 0.0202
-5.500 -0.1984 0.04306 0.03957 -0.0631 0.6022 0.0223
-5.250 -0.1764 0.03426 0.03034 -0.0667 0.5939 0.0228
-5.000 -0.1524 0.03274 0.02871 -0.0676 0.5830 0.0232
-4.750 -0.1270 0.03140 0.02726 -0.0684 0.5741 0.0236
-4.000 -0.0394 0.02666 0.02186 -0.0696 0.5534 0.0280
-3.750 -0.0119 0.02063 0.01523 -0.0711 0.5487 0.0289
-3.500 0.0159 0.01952 0.01406 -0.0717 0.5442 0.0295
-3.250 0.0440 0.01890 0.01338 -0.0722 0.5394 0.0303
-3.000 0.0726 0.01816 0.01250 -0.0726 0.5350 0.0315
-2.750 0.1019 0.01742 0.01162 -0.0728 0.5313 0.0337
-2.500 0.1316 0.01818 0.01229 -0.0727 0.5273 0.0355
-2.250 0.1609 0.01731 0.01123 -0.0730 0.5232 0.0356
-2.000 0.1901 0.01411 0.00771 -0.0738 0.5186 0.0378
-1.750 0.2191 0.01351 0.00708 -0.0742 0.5150 0.0388
-1.500 0.2495 0.01185 0.00520 -0.0741 0.5115 0.0321
-1.250 0.2786 0.01128 0.00455 -0.0743 0.5082 0.0321
-1.000 0.3076 0.01089 0.00409 -0.0745 0.5050 0.0322
-0.750 0.3367 0.01053 0.00370 -0.0747 0.5022 0.0323
-0.500 0.3658 0.01020 0.00336 -0.0750 0.4992 0.0324
-0.250 0.3950 0.00994 0.00307 -0.0752 0.4955 0.0326
0.000 0.4241 0.00977 0.00287 -0.0755 0.4920 0.0334
0.250 0.4532 0.00963 0.00269 -0.0758 0.4886 0.0339
0.500 0.4824 0.00948 0.00254 -0.0761 0.4864 0.0346
0.750 0.5117 0.00937 0.00243 -0.0764 0.4839 0.0352
1.000 0.5409 0.00926 0.00231 -0.0767 0.4804 0.0361
1.250 0.5700 0.00917 0.00216 -0.0769 0.4756 0.0376
1.500 0.5991 0.00912 0.00211 -0.0772 0.4717 0.0396
1.750 0.6283 0.00907 0.00208 -0.0775 0.4688 0.0426
2.000 0.6574 0.00902 0.00206 -0.0778 0.4656 0.0550
2.250 0.6806 0.00690 0.00218 -0.0775 0.4621 1.0000
2.500 0.7095 0.00699 0.00222 -0.0777 0.4573 1.0000
2.750 0.7386 0.00702 0.00224 -0.0780 0.4521 1.0000
3.000 0.7675 0.00711 0.00227 -0.0783 0.4460 1.0000
3.250 0.7963 0.00719 0.00233 -0.0786 0.4417 1.0000
3.500 0.8253 0.00724 0.00238 -0.0789 0.4366 1.0000
3.750 0.8540 0.00734 0.00244 -0.0791 0.4302 1.0000
4.000 0.8828 0.00741 0.00251 -0.0794 0.4240 1.0000
4.250 0.9114 0.00752 0.00259 -0.0797 0.4155 1.0000
4.500 0.9400 0.00761 0.00268 -0.0799 0.4059 1.0000
4.750 0.9682 0.00779 0.00277 -0.0802 0.3876 1.0000
5.000 0.9955 0.00811 0.00293 -0.0803 0.3522 1.0000
5.250 1.0193 0.00915 0.00347 -0.0803 0.2579 1.0000
5.500 1.0448 0.00980 0.00390 -0.0803 0.2180 1.0000
5.750 1.0713 0.01023 0.00422 -0.0804 0.1947 1.0000
6.000 1.0933 0.01139 0.00490 -0.0801 0.1081 1.0000
6.250 1.1170 0.01221 0.00552 -0.0798 0.0672 1.0000
6.500 1.1430 0.01258 0.00587 -0.0797 0.0608 1.0000
6.750 1.1695 0.01286 0.00616 -0.0797 0.0571 1.0000
7.000 1.1958 0.01314 0.00646 -0.0797 0.0540 1.0000
7.250 1.2213 0.01353 0.00682 -0.0796 0.0485 1.0000
7.500 1.2473 0.01381 0.00710 -0.0796 0.0423 1.0000
7.750 1.2691 0.01462 0.00770 -0.0790 0.0176 1.0000
8.000 1.2927 0.01517 0.00828 -0.0786 0.0150 1.0000
8.250 1.3162 0.01570 0.00885 -0.0781 0.0137 1.0000
8.500 1.3395 0.01619 0.00940 -0.0777 0.0130 1.0000
8.750 1.3619 0.01675 0.01001 -0.0771 0.0123 1.0000
9.000 1.3831 0.01741 0.01073 -0.0763 0.0116 1.0000
9.250 1.4016 0.01826 0.01165 -0.0752 0.0109 1.0000
9.500 1.4175 0.01928 0.01276 -0.0737 0.0103 1.0000
9.750 1.4373 0.01988 0.01340 -0.0728 0.0100 1.0000
10.000 1.4543 0.02063 0.01422 -0.0715 0.0096 1.0000
10.250 1.4692 0.02146 0.01512 -0.0699 0.0093 1.0000
10.500 1.4814 0.02237 0.01610 -0.0679 0.0090 1.0000
10.750 1.4888 0.02337 0.01717 -0.0652 0.0087 1.0000
11.000 1.4925 0.02459 0.01846 -0.0622 0.0085 1.0000
11.250 1.4952 0.02612 0.02007 -0.0597 0.0083 1.0000
11.500 1.4951 0.02813 0.02216 -0.0575 0.0081 1.0000
11.750 1.4908 0.03085 0.02500 -0.0559 0.0079 1.0000
12.000 1.4809 0.03452 0.02880 -0.0547 0.0077 1.0000
12.250 1.4765 0.03781 0.03219 -0.0540 0.0076 1.0000
12.500 1.4825 0.04008 0.03455 -0.0538 0.0075 1.0000
12.750 1.4862 0.04264 0.03719 -0.0537 0.0075 1.0000
13.000 1.4888 0.04532 0.03996 -0.0535 0.0073 1.0000
13.250 1.4909 0.04809 0.04282 -0.0534 0.0072 1.0000
13.500 1.4924 0.05094 0.04575 -0.0534 0.0071 1.0000
13.750 1.4924 0.05393 0.04883 -0.0533 0.0069 1.0000
14.000 1.4922 0.05698 0.05197 -0.0533 0.0068 1.0000
14.250 1.4909 0.06014 0.05521 -0.0533 0.0066 1.0000
14.500 1.4893 0.06337 0.05853 -0.0534 0.0065 1.0000
14.750 1.4872 0.06672 0.06196 -0.0535 0.0064 1.0000
15.000 1.4854 0.07012 0.06544 -0.0537 0.0063 1.0000
15.250 1.4833 0.07361 0.06901 -0.0540 0.0062 1.0000
15.500 1.4807 0.07720 0.07268 -0.0544 0.0061 1.0000
15.750 1.4784 0.08082 0.07638 -0.0549 0.0060 1.0000
16.000 1.4757 0.08453 0.08017 -0.0555 0.0059 1.0000
16.250 1.4720 0.08840 0.08411 -0.0561 0.0059 1.0000
16.500 1.4682 0.09228 0.08806 -0.0568 0.0058 1.0000
16.750 1.4634 0.09629 0.09215 -0.0574 0.0057 1.0000
17.000 1.4576 0.10038 0.09634 -0.0579 0.0056 1.0000
17.250 1.4504 0.10460 0.10067 -0.0583 0.0055 1.0000
17.750 1.4304 0.11434 0.11070 -0.0600 0.0054 1.0000
18.000 1.4240 0.11939 0.11586 -0.0622 0.0054 1.0000
18.250 1.4167 0.12460 0.12120 -0.0643 0.0054 1.0000
18.500 1.4090 0.12994 0.12667 -0.0668 0.0054 1.0000
18.750 1.4013 0.13550 0.13235 -0.0695 0.0053 1.0000
19.000 1.3923 0.14133 0.13831 -0.0724 0.0053 1.0000
19.250 1.3837 0.14735 0.14445 -0.0756 0.0053 1.0000
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Polar data table (+)
Polar graphs
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