GOE 795 smoothed (goe795sm-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 795 smoothed (goe795sm-il) Reynolds number: 1,000,000 Max Cl/Cd: 96.36 at α=3.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe795sm-il-1000000-n5.txt Download as CSV file: xf-goe795sm-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 795 smoothed
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.750 -0.4969 0.12259 0.12083 -0.0146 1.0000 0.0045
-11.500 -0.5012 0.11678 0.11504 -0.0164 1.0000 0.0049
-10.500 -0.8526 0.03242 0.03015 -0.0519 1.0000 0.0048
-10.250 -0.8417 0.02773 0.02504 -0.0532 0.9984 0.0049
-10.000 -0.8227 0.02451 0.02145 -0.0542 0.9963 0.0050
-9.750 -0.7989 0.02250 0.01918 -0.0551 0.9946 0.0051
-9.500 -0.7757 0.02091 0.01736 -0.0554 0.9928 0.0052
-9.250 -0.7531 0.01924 0.01544 -0.0554 0.9903 0.0053
-9.000 -0.7274 0.01802 0.01401 -0.0558 0.9880 0.0053
-8.750 -0.7004 0.01692 0.01273 -0.0563 0.9860 0.0054
-8.500 -0.6722 0.01596 0.01160 -0.0569 0.9844 0.0055
-8.250 -0.6431 0.01505 0.01054 -0.0577 0.9831 0.0055
-8.000 -0.6209 0.01419 0.00953 -0.0568 0.9790 0.0057
-7.750 -0.5956 0.01317 0.00834 -0.0567 0.9757 0.0060
-7.500 -0.5670 0.01252 0.00760 -0.0571 0.9733 0.0065
-7.250 -0.5371 0.01197 0.00697 -0.0577 0.9714 0.0068
-7.000 -0.5091 0.01148 0.00640 -0.0579 0.9685 0.0071
-6.750 -0.4837 0.01104 0.00588 -0.0575 0.9634 0.0073
-6.500 -0.4538 0.01062 0.00541 -0.0580 0.9601 0.0079
-6.250 -0.4211 0.01022 0.00494 -0.0592 0.9577 0.0083
-6.000 -0.3911 0.00989 0.00454 -0.0597 0.9531 0.0086
-5.750 -0.3592 0.00941 0.00400 -0.0607 0.9483 0.0096
-5.500 -0.3244 0.00906 0.00363 -0.0623 0.9441 0.0109
-5.250 -0.2921 0.00878 0.00331 -0.0634 0.9372 0.0120
-5.000 -0.2575 0.00850 0.00298 -0.0649 0.9300 0.0137
-4.750 -0.2262 0.00825 0.00271 -0.0657 0.9199 0.0165
-4.500 -0.1952 0.00807 0.00249 -0.0664 0.9088 0.0186
-4.250 -0.1662 0.00788 0.00227 -0.0666 0.8963 0.0227
-4.000 -0.1385 0.00774 0.00208 -0.0666 0.8833 0.0255
-3.750 -0.1117 0.00762 0.00190 -0.0663 0.8700 0.0290
-3.500 -0.0856 0.00751 0.00176 -0.0659 0.8569 0.0343
-3.250 -0.0597 0.00743 0.00162 -0.0654 0.8441 0.0383
-3.000 -0.0341 0.00733 0.00150 -0.0648 0.8310 0.0438
-2.750 -0.0084 0.00727 0.00138 -0.0643 0.8175 0.0476
-2.500 0.0168 0.00720 0.00127 -0.0636 0.8030 0.0545
-2.250 0.0421 0.00715 0.00118 -0.0630 0.7870 0.0603
-2.000 0.0673 0.00709 0.00109 -0.0623 0.7721 0.0689
-1.750 0.0924 0.00702 0.00100 -0.0617 0.7583 0.0827
-1.500 0.1174 0.00692 0.00093 -0.0611 0.7454 0.1059
-1.250 0.1418 0.00675 0.00087 -0.0603 0.7324 0.1537
-1.000 0.1667 0.00664 0.00083 -0.0597 0.7193 0.1923
-0.750 0.1923 0.00659 0.00080 -0.0592 0.7070 0.2158
-0.500 0.2179 0.00654 0.00077 -0.0586 0.6947 0.2380
-0.250 0.2430 0.00648 0.00076 -0.0580 0.6816 0.2703
0.000 0.2676 0.00636 0.00075 -0.0574 0.6685 0.3193
0.250 0.2912 0.00617 0.00075 -0.0565 0.6552 0.4020
0.500 0.3115 0.00577 0.00077 -0.0550 0.6414 0.5604
0.750 0.3266 0.00526 0.00080 -0.0523 0.6268 0.7522
1.000 0.3769 0.00490 0.00093 -0.0573 0.6078 0.9319
1.250 0.4394 0.00508 0.00102 -0.0652 0.5813 0.9575
1.750 0.4974 0.00557 0.00119 -0.0658 0.5042 0.9781
2.000 0.5292 0.00585 0.00130 -0.0668 0.4646 0.9879
2.250 0.5675 0.00619 0.00144 -0.0693 0.4194 0.9950
2.750 0.6383 0.00667 0.00164 -0.0731 0.3508 1.0000
3.250 0.6832 0.00709 0.00187 -0.0708 0.3000 1.0000
3.500 0.7051 0.00734 0.00200 -0.0697 0.2706 1.0000
3.750 0.7268 0.00762 0.00217 -0.0684 0.2397 1.0000
4.000 0.7475 0.00798 0.00236 -0.0670 0.2008 1.0000
4.250 0.7675 0.00840 0.00259 -0.0655 0.1593 1.0000
4.500 0.7874 0.00884 0.00284 -0.0640 0.1205 1.0000
4.750 0.8080 0.00923 0.00309 -0.0626 0.0914 1.0000
5.000 0.8297 0.00953 0.00332 -0.0614 0.0739 1.0000
5.250 0.8515 0.00983 0.00356 -0.0603 0.0595 1.0000
5.500 0.8731 0.01015 0.00382 -0.0590 0.0460 1.0000
5.750 0.8945 0.01049 0.00410 -0.0578 0.0345 1.0000
6.000 0.9157 0.01084 0.00440 -0.0566 0.0248 1.0000
6.250 0.9375 0.01115 0.00470 -0.0554 0.0193 1.0000
6.500 0.9589 0.01149 0.00503 -0.0542 0.0148 1.0000
6.750 0.9803 0.01183 0.00536 -0.0529 0.0121 1.0000
7.000 1.0014 0.01219 0.00573 -0.0517 0.0102 1.0000
7.250 1.0231 0.01250 0.00608 -0.0505 0.0095 1.0000
7.500 1.0442 0.01284 0.00646 -0.0493 0.0087 1.0000
7.750 1.0648 0.01323 0.00688 -0.0479 0.0080 1.0000
8.000 1.0848 0.01368 0.00735 -0.0465 0.0071 1.0000
8.250 1.1043 0.01415 0.00789 -0.0450 0.0067 1.0000
8.500 1.1252 0.01450 0.00827 -0.0438 0.0064 1.0000
8.750 1.1450 0.01492 0.00875 -0.0424 0.0061 1.0000
9.000 1.1649 0.01535 0.00921 -0.0410 0.0057 1.0000
9.250 1.1839 0.01583 0.00976 -0.0396 0.0054 1.0000
9.500 1.2023 0.01635 0.01033 -0.0380 0.0052 1.0000
9.750 1.2206 0.01686 0.01089 -0.0364 0.0048 1.0000
10.000 1.2372 0.01749 0.01158 -0.0346 0.0045 1.0000
10.250 1.2496 0.01846 0.01265 -0.0321 0.0042 1.0000
10.500 1.2662 0.01903 0.01330 -0.0303 0.0041 1.0000
10.750 1.2834 0.01954 0.01386 -0.0287 0.0040 1.0000
11.000 1.2977 0.02019 0.01459 -0.0266 0.0039 1.0000
11.250 1.3093 0.02086 0.01535 -0.0240 0.0038 1.0000
11.500 1.3226 0.02142 0.01598 -0.0218 0.0035 1.0000
11.750 1.3333 0.02217 0.01682 -0.0192 0.0034 1.0000
12.000 1.3451 0.02288 0.01760 -0.0170 0.0032 1.0000
12.250 1.3571 0.02359 0.01838 -0.0149 0.0031 1.0000
12.500 1.3673 0.02446 0.01932 -0.0127 0.0030 1.0000
12.750 1.3756 0.02548 0.02043 -0.0104 0.0029 1.0000
13.000 1.3833 0.02656 0.02161 -0.0082 0.0028 1.0000
13.250 1.3883 0.02790 0.02306 -0.0059 0.0028 1.0000
13.500 1.3948 0.02916 0.02441 -0.0041 0.0026 1.0000
13.750 1.3974 0.03081 0.02618 -0.0021 0.0026 1.0000
14.000 1.3902 0.03344 0.02898 0.0002 0.0024 1.0000
14.250 1.3928 0.03529 0.03097 0.0014 0.0024 1.0000
14.500 1.3893 0.03789 0.03370 0.0025 0.0024 1.0000
14.750 1.3765 0.04166 0.03767 0.0034 0.0023 1.0000
15.000 1.3755 0.04439 0.04052 0.0035 0.0023 1.0000
15.250 1.3703 0.04776 0.04403 0.0033 0.0023 1.0000
15.500 1.3623 0.05174 0.04815 0.0025 0.0023 1.0000
15.750 1.3558 0.05573 0.05226 0.0014 0.0023 1.0000
16.000 1.3450 0.06061 0.05730 -0.0003 0.0023 1.0000
16.250 1.3224 0.06775 0.06461 -0.0035 0.0023 1.0000
16.500 1.3063 0.07424 0.07126 -0.0066 0.0023 1.0000
16.750 1.2896 0.08123 0.07839 -0.0102 0.0023 1.0000
17.000 1.2586 0.09118 0.08850 -0.0153 0.0023 1.0000
17.250 1.2331 0.10041 0.09787 -0.0201 0.0023 1.0000
17.500 1.2064 0.11008 0.10768 -0.0249 0.0023 1.0000
17.750 1.1824 0.11940 0.11710 -0.0296 0.0023 1.0000
18.000 1.1317 0.13498 0.13283 -0.0375 0.0023 1.0000
18.250 1.1074 0.14514 0.14309 -0.0426 0.0023 1.0000
18.500 1.0766 0.15740 0.15546 -0.0489 0.0024 1.0000
18.750 1.0603 0.16637 0.16450 -0.0536 0.0024 1.0000
19.000 1.0384 0.17752 0.17574 -0.0594 0.0025 1.0000
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Polar data table (+)
Polar graphs
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